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Investigation of the Aerodynamic Characteristics of an Aerofoil Shaped Fuselage UAV Model
Available online at www.sciencedirect.com
ScienceDirect Procedia Engineering 90 (2014) 225 – 231
10th International Conference on Mechanical Engineering, ICME 2013
Investigation of the aerodynamic characteristics of an aerofoil shaped fuselage UAV model G.M. Jahangir Alama*, Md. Mamunb, Md. Abu. Taher Alib, Md. Quamrul Islamb, A. K. M. Sadrul Islamc a
Department of Mechanical Engineering, Military Institute of Science & Engineering (MIST), Dhaka, Bangladesh b
c
Department of Mechanical Engineering, BUET, Dhaka, Bangladesh,
Department of Mechanical and Chemical Engineering, Islamic University of Technology (IUT), Gazipur, Bangladesh
Abstract This paper explains the fabrication of an UAV having aerofoil shaped fuselage using NACA 4416 profile and compare the result between the aerodynamic characteristics with that of the same model obtained from CFD investigation. Open circuit subsonic wind tunnel has been used to test the fabricated UAV model and collection of data. The wind tunnel is associated with Versatile Data Acquisition System (VDAS) to measure the lift & drag force coefficients and point surface pressures. This paper explains the design parameters and investigation of the aerodynamic characteristics of the fabricated ‘Aerofoil Shaped Fuselage’ UAV model. This type of model might be used for many military and civil applications like scientific data gathering, surveillance for law enforcement & homeland security, precision agriculture, forest fire monitoring, geological survey etc. The aerodynamic characteristics of Aerofoil Shaped Fuselage UAV model have been carried out at two different Reynolds Number (1.37 x 105 and 2.74 x 105 respectively) with different angles of attack from -3o to 18o. The stalling angle of this design is found at about 14o during experimental investigation. The aerofoil shaped fuselage UAV model might be used for designing the future UAV. © Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license © 2014 2014The The Authors. Published by Elsevier Ltd. (http://creativecommons.org/licenses/by-nc-nd/3.0/). Selection and peer-review under responsibility of the Department of Mechanical Engineering, Bangladesh University of Selection and peer-review under responsibility Engineering and Technology (BUET). of the Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
Keywords: Unmanned air vehicles (UAV); aerofoil shaped fuselage; aerodynamic characteristics; lift coefficient; drag coefficient; angle of attack; stalling angle.
1. Introduction An air vehicle having no onboard pilot and capable of pre-programmed operation as well as reception of
* Corresponding author. Tel.: +88-0171-2030061. E-mail address: [email protected]
1877-7058 © 2014 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license
(http://creativecommons.org/licenses/by-nc-nd/3.0/). Selection and peer-review under responsibility of the Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET) doi:10.1016/j.proeng.2014.11.841
226
G.M. Jahangir Alam et al. / Procedia Engineering 90 (2014) 225 – 231
intermittent commands either independently or from a human operator at a distance from the ground is called unmanned air vehicle (UAV). UAVs can carry out both military and civil applications like scientific data gathering, surveillance for law enforcement and homeland security, precision agriculture, forest fire monitoring, geological survey etc [1 & 2]. UAVs mostly fly under low speed conditions. The aerodynamic characteristics of the UAVs have many similarities than that of the monoplane configuration. Due to the UAV’s potential for carrying out so many tasks without direct risk to the crew or humans in general, they are ideal for testing new concepts which have been put forward as a means to further increase the vehicle’s capability [3]. This paper explains about the detail parameters for fabrication of an UAV having ‘Aerofoil Shaped Fuselage’ using NACA 4416 profile. The wings of a conventional UAV are producing the lift and it’s fuselage has very little or no contribution on producing lift. But UAV requires higher lifting force with a smaller size. As such, in order to maximize the efficiency of an UAV, it is assumed that the basic design of UAV could be changed and it should be such that all components of an UAV should contribute to the total lift. In such case, the concept of development of all lifting vehicle technology would bring good result for research on design of future UAV. Hence, this paper explains the aerodynamic characteristics of aerofoil shaped fuselage UAV model at different angles of attack and compare the result between the aerodynamic characteristics with that of the same model obtained from CFD investigation [1]. 2. Experimental Design Four major parts of the aerofoil shaped fuselage UAV model are wing, fuselage, horizontal stabilizer and vertical stabilizer. Up wing type model has been selected for fabrication. NACA 4416 cambered aerofoil has been used for fabrication of wing, fuselage, horizontal stabilizer and vertical stabilizer of said model. Important features of experimental design are shown in Table 1. 3. Subsonic Wind Tunnel Open circuit subsonic wind tunnel has been used to test the fabricated aerofoil shaped fuselage UAV model. The dimensions of the working section of said wind tunnel are 60 cm (length) x 32 cm (width) x 30 cm (height). Air enters the wind tunnel through an aerodynamically designed diffuser (cone) and a control knob could be rotated to control the air speed from 0 to 40 m/s. The ‘3-Component Balance’ is fitted with the working section of the wind tunnel to measure the lift, drag, pitching moment and their coefficients. Photograph of subsonic wind tunnel and aerofoil shaped fuselage UAV model fitted with the working section of the subsonic wind tunnel are shown in Figs. 1 and 2 respectively. Table 1. Important Features of Experimental Design
Nomenclature Wing Design (Chord length, span and maximum thickness of each wing) Fuselage Design (Chord length, span and maximum thickness of fuselage) Horizontal and Vertical Stabilizer Air speed (v) Reynold’s Number (Re) Angles of attack (α)
Type 55 mm, 114 mm (either left or right) and 7 mm at 16% chord length from the root 108 mm, 45 mm (left + right) and 15 mm at 16% chord length from the root As suitable for this design by maintaining the scale factor 20 m/s and 40 m/s 1.37 x 105 and 2.74 x 105 -3° to 18°
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Fig. 2. Photograph of Aerofoil Shaped Fuselage UAV Model Fitted with the Working Section of Wind Tunnel
Fig. 1. Photograph of Subsonic Wind tunnel
4. Aerodynamic Characteristics for Experimental Design 4.1 Aerodynamic characteristics of aerofoil shaped fuselage model at 20 m/s The variation of lift coefficient with angle of attack at 20 m/s for aerofoil shaped fuselage UAV model at different angle of attack is shown in Figure 3. The zero lift angles have been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 14o. Afterwards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 14˚. The maximum lift coefficient, CLmax for this type of model is found approximately 0.78. The variation of drag coefficient with angle of attack at 20 m/s for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 4. The shape of the drag coefficient vs angle of attack curve is found parabolic nature. As such, the drag coefficient increases with the increase of angle of attack. The value of drag coefficient for this type of model at 14o angle of attack is found approximately 0.089. 㻜㻚㻝㻢
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Angle of Attack (AOA) in Degree
Fig. 3. Variation of Lift Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Fig. 4. Variation of Drag Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 20 m/s
The lift drag ratio curve of aerofoil shaped fuselage UAV model at 20 m/s is shown in Fig. 5. The aerofoil shaped wing and fuselage tips experienced induced drag due to tip vortices and trailing edge vortices. A significant amount of drag is also produced due to shape and skin friction effects of the aerofoil shaped fuselage UAV model which are termed as profile drag. So, both induced and profile drags have been experienced by this type of model. But it is assumed that said model has also increased a significant amount of extra lift from it’s fuselage due to it’s aerofoil shape. From Figure 5, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack
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i.e. 14º angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs for this type of model at the stall angle due to flow separation. The lift drag ratio at the stall angle for this model is found 8.76. 4.2 Aerodynamic characteristics of aerofoil shaped fuselage model at 40 m/s The variation of lift coefficient with angle of attack at 40 m/sec for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 6. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 14o. After wards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 14˚. The maximum lift coefficient, CLmax for this type of model is approximately 0.81. 㻝
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Lift Coefficient
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Fig. 5. Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 20 m/s
Fig. 6. Variation of Lift Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 40 m/s
The variation of drag coefficient with angle of attack at 40 m/s for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 7. The shape of the drag coefficient vs angle of attack curve is found parabolic nature. As such, the drag coefficient increases with the increase of angle of attack. The value of drag coefficient for this type of model at 14o angle of attack is found 0.086.
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Drag Coefficient
The lift drag ratio curve of aerofoil shaped fuselage UAV model at 40 m/s is shown in Fig. 8. The aerofoil shaped wing and fuselage tips experienced induced drag due to tip vortices and trailing edge vortices. A significant amount of drag is also produced due to shape and skin friction effects of the aerofoil shaped fuselage UAV model which are termed as profile drag. So, both induced and profile drags have been experienced by this type of model. But it is assumed that said model has also increased a significant amount of extra lift from it’s fuselage due to it’s aerofoil shape. From Figure 8, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack i.e. 14º angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs for this type of model at the stall angle due to flow separation. The lift drag ratio at the stall angle for this model is found 9.42.
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Angle of Attack (AOA) in Degree
Fig. 7. Variation of Drag Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 40
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Fig. 8. Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 40 m/s
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5. Comparison of Aerodynamic Characteristics between Experimental and Computational Design 5.1 Aerodynamic characteristics of aerofoil shaped fuselage model at 20 m/s The maximum lift coefficient, CLmax for aerofoil shaped fuselage UAV model is found approximately 1.20 during computational design. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 15o. Afterwards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 15˚ during computational design [1 and 4]. The value of drag coefficient for this model at 15o angle of attack is found 0.166. The shape of the drag coefficient vs angle of attack curve is found parabolic nature and the drag coefficient increases with the increase of angle of attack during computational design [1 and 4]. The variation of lift and drag coefficient with angle of attack between computational and experimental data of aerofoil shaped fuselage UAV models is shown in Figure 9 and 10 respectively. It is seen that the lift and drag force coefficients obtained from computational result is more than that of the experimental result for both the configurations. 5.2 Aerodynamic characteristics of aerofoil shaped fuselage model at 40 m/s The maximum lift coefficient, CLmax for aerofoil shaped fuselage UAV model is found approximately 1.221 during computational design. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 15o. After wards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 15˚ during computational design [1 & 4]. The value of drag coefficient for this model at 15o angle of attack is found 0.145. The shape of the drag coefficient vs angle of attack curve is found parabolic nature and the drag coefficient increases with the increase of angle of attack during computational design [1 and 4]. The variation of lift and drag coefficient with angle of attack between computational and experimental data of aerofoil shaped fuselage UAV models is shown in Figures 11 and 12 respectively. It is seen that ‘Aerofoil shaped fuselage configuration at 40 m/s’ provides more lift and drag coefficients than other configurations for both computational and experimental design. It is also seen that the lift and drag force coefficients obtained from computational result is more than the experimental result for all configurations. Among the two configurations (Fig. 9 and 11), ‘Aerofoil shaped fuselage configuration at 40 m/s’ provides maximum lift than other configurations at about 15o angle of attack. During drag analysis, it is seen from Fig. 10 and 12 that among the two different types of configurations, “Aerofoil shaped fuselage configuration at 20 m/s” provides maximum drag than other configurations. 㻝㻚㻠
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Fig. 9. Comparison of Lift Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Fig. 10. Comparison of Drag Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Angle of Attack (AOA) in Degree
Fig. 12. Comparison of Drag Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 40 m/s
Fig. 11. Comparison of Lift Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 40 m/s
5.3 Lift to drag ratio curve of aerofoil shaped fuselage model The lift drag ratio curve of aerofoil shaped fuselage UAV model at 20 m/s for both experimental & computational design is shown in Fig. 13. The lift to drag coefficient is found less for aerofoil shaped fuselage UAV model of computational design than that of experimental design. From Figure 13, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs at the stall angle due to flow separation. The lift drag ratio curve of aerofoil shaped fuselage UAV model at 40 m/s for both experimental and computational design is shown in Fig. 14. The lift to drag coefficient is found less for aerofoil shaped fuselage UAV model of computational design than that of experimental design. From Figure 14, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs at the stall angle due to flow separation. 㻜㻚㻟
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㻜㻚㻞㻡 Theoretical Design
Theoretical Design Experimental Design
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Fig. 13. Comparison of Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 20 m/s
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Fig. 14. Comparison of Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 40 m/s
6. Conclusions Operation of UAV proved to be easy and adaptable for versatile tasks including military as well as many civil applications in the recent years. But UAV requires higher lifting force with a smaller size. In order to maximize the
G.M. Jahangir Alam et al. / Procedia Engineering 90 (2014) 225 – 231
efficiency of an UAV - the concept of development of all lifting vehicle technology might bring good result for designing of the future UAV. For this reason, the aerofoil shaped fuselage of an UAV might be a good source of lifting force. This paper explains about the fabrication of an UAV having aerofoil shaped fuselage using NACA 4416 profile and compare between the aerodynamic characteristics with that of the same model obtained from CFD investigation. The experimental data have been obtained by using subsonic wind tunnel and the investigation has been carried out at 20 m/sec and 40 m/s respectively. The angle of attack has been varied from -3° to 18°. The stalling angle has been found at about 14° for experimental design. The L/D Ratio of ‘Aerofoil shaped fuselage configuration’ at the stalling angle (14° AOA) at 20 & 40 m/s are 6.84 & 8.02 respectively for experimental design and for theoretical design the L/D Ratio of same model at the stalling angle (15° AOA) at 20 and 40 m/s are 5.13 & 7.40 respectively. The aerofoil shaped fuselage has produced a significant amount of extra lift from it’s fuselage due to aerofoil shape. But said model has also produced some extra drag due to tip vortices and trailing edge vortices. However, ways for reduction of the tip and trailing edge vortices from aerofoil shaped fuselage might be investigated in future to enhance the efficiency further-more. At the end, it is felt that the aerofoil shaped fuselage might be a very good option for designing the future UAV. References [1] G.M. Jahangir Alam, Md. Mamun, Md. Abu Taher Ali and A. K. M. Sadrul Islam, “Development of Design of Aerofoil Shaped Fuselage and CFD Investigation of its Aerodynamic Characteristics”, ISSN: 2224-2007, MIST Journal of Science and Technology, 2(2013), No. 1, 43-50. [2] Randal Beard, Derek Kingston, Morgan Quigley, Deryl Snyder, Reed Christiansen, Walt Johnson, Timothy McLain and Michael A. Goodrich, “Autonomous Vehicle Technologies for Small Fixed-Wing UAVs”, Journal of Aerospace Computing, Information and Communication,, January 2005, 92-94. [3] M. Secanell, A. Suleman and P. Gamboa “Design of a Morphing Airfoil for a Light Unmanned Aerial Vehicle using High-Fidelity Aerodynamic Shape Optimization” Journal of American Institute of Aeronautics and Astronautics (AIAA 2005-1891), April 2005, 1-20. [4] G.M. Jahangir Alam, Md Mamun and A. K. M. Sadrul Islam, “Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped Fuselage”, International Journal of Scientific & Engineering Research, 4 (2013), Issue 1.
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ScienceDirect Procedia Engineering 90 (2014) 225 – 231
10th International Conference on Mechanical Engineering, ICME 2013
Investigation of the aerodynamic characteristics of an aerofoil shaped fuselage UAV model G.M. Jahangir Alama*, Md. Mamunb, Md. Abu. Taher Alib, Md. Quamrul Islamb, A. K. M. Sadrul Islamc a
Department of Mechanical Engineering, Military Institute of Science & Engineering (MIST), Dhaka, Bangladesh b
c
Department of Mechanical Engineering, BUET, Dhaka, Bangladesh,
Department of Mechanical and Chemical Engineering, Islamic University of Technology (IUT), Gazipur, Bangladesh
Abstract This paper explains the fabrication of an UAV having aerofoil shaped fuselage using NACA 4416 profile and compare the result between the aerodynamic characteristics with that of the same model obtained from CFD investigation. Open circuit subsonic wind tunnel has been used to test the fabricated UAV model and collection of data. The wind tunnel is associated with Versatile Data Acquisition System (VDAS) to measure the lift & drag force coefficients and point surface pressures. This paper explains the design parameters and investigation of the aerodynamic characteristics of the fabricated ‘Aerofoil Shaped Fuselage’ UAV model. This type of model might be used for many military and civil applications like scientific data gathering, surveillance for law enforcement & homeland security, precision agriculture, forest fire monitoring, geological survey etc. The aerodynamic characteristics of Aerofoil Shaped Fuselage UAV model have been carried out at two different Reynolds Number (1.37 x 105 and 2.74 x 105 respectively) with different angles of attack from -3o to 18o. The stalling angle of this design is found at about 14o during experimental investigation. The aerofoil shaped fuselage UAV model might be used for designing the future UAV. © Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license © 2014 2014The The Authors. Published by Elsevier Ltd. (http://creativecommons.org/licenses/by-nc-nd/3.0/). Selection and peer-review under responsibility of the Department of Mechanical Engineering, Bangladesh University of Selection and peer-review under responsibility Engineering and Technology (BUET). of the Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET)
Keywords: Unmanned air vehicles (UAV); aerofoil shaped fuselage; aerodynamic characteristics; lift coefficient; drag coefficient; angle of attack; stalling angle.
1. Introduction An air vehicle having no onboard pilot and capable of pre-programmed operation as well as reception of
* Corresponding author. Tel.: +88-0171-2030061. E-mail address: [email protected]
1877-7058 © 2014 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license
(http://creativecommons.org/licenses/by-nc-nd/3.0/). Selection and peer-review under responsibility of the Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET) doi:10.1016/j.proeng.2014.11.841
226
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intermittent commands either independently or from a human operator at a distance from the ground is called unmanned air vehicle (UAV). UAVs can carry out both military and civil applications like scientific data gathering, surveillance for law enforcement and homeland security, precision agriculture, forest fire monitoring, geological survey etc [1 & 2]. UAVs mostly fly under low speed conditions. The aerodynamic characteristics of the UAVs have many similarities than that of the monoplane configuration. Due to the UAV’s potential for carrying out so many tasks without direct risk to the crew or humans in general, they are ideal for testing new concepts which have been put forward as a means to further increase the vehicle’s capability [3]. This paper explains about the detail parameters for fabrication of an UAV having ‘Aerofoil Shaped Fuselage’ using NACA 4416 profile. The wings of a conventional UAV are producing the lift and it’s fuselage has very little or no contribution on producing lift. But UAV requires higher lifting force with a smaller size. As such, in order to maximize the efficiency of an UAV, it is assumed that the basic design of UAV could be changed and it should be such that all components of an UAV should contribute to the total lift. In such case, the concept of development of all lifting vehicle technology would bring good result for research on design of future UAV. Hence, this paper explains the aerodynamic characteristics of aerofoil shaped fuselage UAV model at different angles of attack and compare the result between the aerodynamic characteristics with that of the same model obtained from CFD investigation [1]. 2. Experimental Design Four major parts of the aerofoil shaped fuselage UAV model are wing, fuselage, horizontal stabilizer and vertical stabilizer. Up wing type model has been selected for fabrication. NACA 4416 cambered aerofoil has been used for fabrication of wing, fuselage, horizontal stabilizer and vertical stabilizer of said model. Important features of experimental design are shown in Table 1. 3. Subsonic Wind Tunnel Open circuit subsonic wind tunnel has been used to test the fabricated aerofoil shaped fuselage UAV model. The dimensions of the working section of said wind tunnel are 60 cm (length) x 32 cm (width) x 30 cm (height). Air enters the wind tunnel through an aerodynamically designed diffuser (cone) and a control knob could be rotated to control the air speed from 0 to 40 m/s. The ‘3-Component Balance’ is fitted with the working section of the wind tunnel to measure the lift, drag, pitching moment and their coefficients. Photograph of subsonic wind tunnel and aerofoil shaped fuselage UAV model fitted with the working section of the subsonic wind tunnel are shown in Figs. 1 and 2 respectively. Table 1. Important Features of Experimental Design
Nomenclature Wing Design (Chord length, span and maximum thickness of each wing) Fuselage Design (Chord length, span and maximum thickness of fuselage) Horizontal and Vertical Stabilizer Air speed (v) Reynold’s Number (Re) Angles of attack (α)
Type 55 mm, 114 mm (either left or right) and 7 mm at 16% chord length from the root 108 mm, 45 mm (left + right) and 15 mm at 16% chord length from the root As suitable for this design by maintaining the scale factor 20 m/s and 40 m/s 1.37 x 105 and 2.74 x 105 -3° to 18°
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Fig. 2. Photograph of Aerofoil Shaped Fuselage UAV Model Fitted with the Working Section of Wind Tunnel
Fig. 1. Photograph of Subsonic Wind tunnel
4. Aerodynamic Characteristics for Experimental Design 4.1 Aerodynamic characteristics of aerofoil shaped fuselage model at 20 m/s The variation of lift coefficient with angle of attack at 20 m/s for aerofoil shaped fuselage UAV model at different angle of attack is shown in Figure 3. The zero lift angles have been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 14o. Afterwards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 14˚. The maximum lift coefficient, CLmax for this type of model is found approximately 0.78. The variation of drag coefficient with angle of attack at 20 m/s for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 4. The shape of the drag coefficient vs angle of attack curve is found parabolic nature. As such, the drag coefficient increases with the increase of angle of attack. The value of drag coefficient for this type of model at 14o angle of attack is found approximately 0.089. 㻜㻚㻝㻢
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Fig. 3. Variation of Lift Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Fig. 4. Variation of Drag Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 20 m/s
The lift drag ratio curve of aerofoil shaped fuselage UAV model at 20 m/s is shown in Fig. 5. The aerofoil shaped wing and fuselage tips experienced induced drag due to tip vortices and trailing edge vortices. A significant amount of drag is also produced due to shape and skin friction effects of the aerofoil shaped fuselage UAV model which are termed as profile drag. So, both induced and profile drags have been experienced by this type of model. But it is assumed that said model has also increased a significant amount of extra lift from it’s fuselage due to it’s aerofoil shape. From Figure 5, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack
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i.e. 14º angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs for this type of model at the stall angle due to flow separation. The lift drag ratio at the stall angle for this model is found 8.76. 4.2 Aerodynamic characteristics of aerofoil shaped fuselage model at 40 m/s The variation of lift coefficient with angle of attack at 40 m/sec for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 6. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 14o. After wards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 14˚. The maximum lift coefficient, CLmax for this type of model is approximately 0.81. 㻝
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Fig. 5. Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 20 m/s
Fig. 6. Variation of Lift Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 40 m/s
The variation of drag coefficient with angle of attack at 40 m/s for aerofoil shaped fuselage model at different angle of attack is shown in Fig. 7. The shape of the drag coefficient vs angle of attack curve is found parabolic nature. As such, the drag coefficient increases with the increase of angle of attack. The value of drag coefficient for this type of model at 14o angle of attack is found 0.086.
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The lift drag ratio curve of aerofoil shaped fuselage UAV model at 40 m/s is shown in Fig. 8. The aerofoil shaped wing and fuselage tips experienced induced drag due to tip vortices and trailing edge vortices. A significant amount of drag is also produced due to shape and skin friction effects of the aerofoil shaped fuselage UAV model which are termed as profile drag. So, both induced and profile drags have been experienced by this type of model. But it is assumed that said model has also increased a significant amount of extra lift from it’s fuselage due to it’s aerofoil shape. From Figure 8, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack i.e. 14º angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs for this type of model at the stall angle due to flow separation. The lift drag ratio at the stall angle for this model is found 9.42.
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Fig. 7. Variation of Drag Coefficient with Angle of Attack for Aerofoil Shaped Fuselage UAV Model at 40
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Fig. 8. Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 40 m/s
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5. Comparison of Aerodynamic Characteristics between Experimental and Computational Design 5.1 Aerodynamic characteristics of aerofoil shaped fuselage model at 20 m/s The maximum lift coefficient, CLmax for aerofoil shaped fuselage UAV model is found approximately 1.20 during computational design. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 15o. Afterwards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 15˚ during computational design [1 and 4]. The value of drag coefficient for this model at 15o angle of attack is found 0.166. The shape of the drag coefficient vs angle of attack curve is found parabolic nature and the drag coefficient increases with the increase of angle of attack during computational design [1 and 4]. The variation of lift and drag coefficient with angle of attack between computational and experimental data of aerofoil shaped fuselage UAV models is shown in Figure 9 and 10 respectively. It is seen that the lift and drag force coefficients obtained from computational result is more than that of the experimental result for both the configurations. 5.2 Aerodynamic characteristics of aerofoil shaped fuselage model at 40 m/s The maximum lift coefficient, CLmax for aerofoil shaped fuselage UAV model is found approximately 1.221 during computational design. The zero lift angle has been found at -3º angle of attack. Then the lift coefficient increases almost linearly with the increase of angle of attack up to approximately 15o. After wards, the lift coefficient decreases with the further increase of angle of attack. As such, the stalling angle of this model is found at about 15˚ during computational design [1 & 4]. The value of drag coefficient for this model at 15o angle of attack is found 0.145. The shape of the drag coefficient vs angle of attack curve is found parabolic nature and the drag coefficient increases with the increase of angle of attack during computational design [1 and 4]. The variation of lift and drag coefficient with angle of attack between computational and experimental data of aerofoil shaped fuselage UAV models is shown in Figures 11 and 12 respectively. It is seen that ‘Aerofoil shaped fuselage configuration at 40 m/s’ provides more lift and drag coefficients than other configurations for both computational and experimental design. It is also seen that the lift and drag force coefficients obtained from computational result is more than the experimental result for all configurations. Among the two configurations (Fig. 9 and 11), ‘Aerofoil shaped fuselage configuration at 40 m/s’ provides maximum lift than other configurations at about 15o angle of attack. During drag analysis, it is seen from Fig. 10 and 12 that among the two different types of configurations, “Aerofoil shaped fuselage configuration at 20 m/s” provides maximum drag than other configurations. 㻝㻚㻠
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Fig. 9. Comparison of Lift Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Fig. 10. Comparison of Drag Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 20 m/s
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Fig. 12. Comparison of Drag Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 40 m/s
Fig. 11. Comparison of Lift Coefficient VS Angle of Attack between Computational and Experimental Data of Aerofoil Shaped Fuselage UAV Model at 40 m/s
5.3 Lift to drag ratio curve of aerofoil shaped fuselage model The lift drag ratio curve of aerofoil shaped fuselage UAV model at 20 m/s for both experimental & computational design is shown in Fig. 13. The lift to drag coefficient is found less for aerofoil shaped fuselage UAV model of computational design than that of experimental design. From Figure 13, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs at the stall angle due to flow separation. The lift drag ratio curve of aerofoil shaped fuselage UAV model at 40 m/s for both experimental and computational design is shown in Fig. 14. The lift to drag coefficient is found less for aerofoil shaped fuselage UAV model of computational design than that of experimental design. From Figure 14, it is found that at low and moderate lift coefficients, there is no appreciable flow separation. As the lift coefficient increases, drag coefficient also increases exponentially up to stall angle of attack. Afterwards, a sharp increase of drag coefficient with reduction of lift coefficient occurs at the stall angle due to flow separation. 㻜㻚㻟
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Fig. 13. Comparison of Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 20 m/s
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Fig. 14. Comparison of Lift Drag Ratio Curve of Aerofoil Shaped Fuselage UAV model at 40 m/s
6. Conclusions Operation of UAV proved to be easy and adaptable for versatile tasks including military as well as many civil applications in the recent years. But UAV requires higher lifting force with a smaller size. In order to maximize the
G.M. Jahangir Alam et al. / Procedia Engineering 90 (2014) 225 – 231
efficiency of an UAV - the concept of development of all lifting vehicle technology might bring good result for designing of the future UAV. For this reason, the aerofoil shaped fuselage of an UAV might be a good source of lifting force. This paper explains about the fabrication of an UAV having aerofoil shaped fuselage using NACA 4416 profile and compare between the aerodynamic characteristics with that of the same model obtained from CFD investigation. The experimental data have been obtained by using subsonic wind tunnel and the investigation has been carried out at 20 m/sec and 40 m/s respectively. The angle of attack has been varied from -3° to 18°. The stalling angle has been found at about 14° for experimental design. The L/D Ratio of ‘Aerofoil shaped fuselage configuration’ at the stalling angle (14° AOA) at 20 & 40 m/s are 6.84 & 8.02 respectively for experimental design and for theoretical design the L/D Ratio of same model at the stalling angle (15° AOA) at 20 and 40 m/s are 5.13 & 7.40 respectively. The aerofoil shaped fuselage has produced a significant amount of extra lift from it’s fuselage due to aerofoil shape. But said model has also produced some extra drag due to tip vortices and trailing edge vortices. However, ways for reduction of the tip and trailing edge vortices from aerofoil shaped fuselage might be investigated in future to enhance the efficiency further-more. At the end, it is felt that the aerofoil shaped fuselage might be a very good option for designing the future UAV. References [1] G.M. Jahangir Alam, Md. Mamun, Md. Abu Taher Ali and A. K. M. Sadrul Islam, “Development of Design of Aerofoil Shaped Fuselage and CFD Investigation of its Aerodynamic Characteristics”, ISSN: 2224-2007, MIST Journal of Science and Technology, 2(2013), No. 1, 43-50. [2] Randal Beard, Derek Kingston, Morgan Quigley, Deryl Snyder, Reed Christiansen, Walt Johnson, Timothy McLain and Michael A. Goodrich, “Autonomous Vehicle Technologies for Small Fixed-Wing UAVs”, Journal of Aerospace Computing, Information and Communication,, January 2005, 92-94. [3] M. Secanell, A. Suleman and P. Gamboa “Design of a Morphing Airfoil for a Light Unmanned Aerial Vehicle using High-Fidelity Aerodynamic Shape Optimization” Journal of American Institute of Aeronautics and Astronautics (AIAA 2005-1891), April 2005, 1-20. [4] G.M. Jahangir Alam, Md Mamun and A. K. M. Sadrul Islam, “Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped Fuselage”, International Journal of Scientific & Engineering Research, 4 (2013), Issue 1.
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