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Use of a stanton tube for skin-friction measurements
492
LITERATURE
AND
23-59L, March
rg5g. 13 pp., diagrs., photos. Results of the tire-to-surface friction measurements in braking on runways under varions surface conditions are presented and compared for a C-123B airplane and a friction cart. Comparisons of wet-surface friction studies with a rz-inch-diameter tire, an automobile tire, and an extra-high-pressure aircraft tire are also given.
Low Tire Friction and Cornering Forces on a Wet Surface. Eziaslav N. Harrin. NACA TN 4406, September 1958. 27 pp., diagrs., photos. An investigation was made by the National Advisory Committee for Aeronautics to study typical tire behavior on wet runways. A specially constructed tire treadmill served as a tire test vehicle whereas force measurements were made by means of a straingage balance. Values of maximum braking, full-skid braking, and rolling friction coefficients were obtained at yaw angles of o” and 4’ while operating two tire types (smooth and diamond treaded) in water depths from 0.02 to 0.09 inch and at speeds up to g4 feet per second including tire planing. Cornering-force coefficients were measured at the free-roll and maximum braking conditions. Study of Taxiing Problems Associated with Runway Roughness. Benjamin Milwitzky. NASA Memorandum z-ZI-59L, March rg5g. 12 pp., diagrs. This paper briefly summarizes available statistical data on airplane taxi operations, examines the profiles and power spectra of four selected runways and taxiways covering a wide range of surface roughness, considers (on the basis of theoretical and experimental results) the loads resulting from taxiing on such runways over a range of speeds and, by synthesis of the aforementioned results, proposes new criteria for runway and taxiway smoothness which are applicable to new construction and may also be used as a guide for determining when repairs are necessary. Investigation of the Maximum Spin-up Coefficients of Friction obtained during Tests of a Landing Gear having a Static-Load Rating of 20,000 Pounds. Sidney A. Batterson. NASA Memorandum IZ-20.58L, January rg5g. 24 pp. diagrs., photos., tab. An experimental investigation was made at the Langley landing loads track to obtain data on the maximum wheel spin-up coefficients of friction developed during landing. The forward speeds ranged from o to approximately 180 feet per second and the sinking speeds, from 2.7 to 9.4 feet per second. The results indicated the variation of the maximum spin-up coefficient of friction with forward speed and vertical load.
CURRENT
EVENTS
VOL.
2
(1958/59)
2.3. Skin friction Measurements of Skin Friction in a Plane Turbulent Wall Jet. A. Sigalla. Royal Aeronautical Society, Journal, v. 62, Dec. 1958, p. 873-877. Considers the inner layer of fluid between the wall and the position where the velocity is a maximum as a boundary layer with an outer uniform free stream of velocity equal to the local maximum velocity. Preliminary Investigations of Spiked Bodies at Hypersonic Speeds. Seymour M. Bogdonoff and Irwin E. Vas. Journal of the Aero/Space Sciences, v. 26, Feb. rg59, pp.2 65-74. An examination of the flow over blunt bodies equipped with a spike to minimize heattransfer rates. The use of a spike protruding from a hemispherical-nosed cylinder at M = 14 decreased the pressure level by an order of magnitude and the heat transfer to a fraction of that measured on a hemisphere without a spike. The general technique appears to hold considerable promise for hypersonic flight.
Use of a Stanton Tube for Skin-Friction Measurements. S. S. Abarbanel, R. J. Hakkinen, and L. Trilling. NASA Memorandum z-17-59 W, March rg5g. 48 pp., diagrs., photos. An experimental program is presented in which a Stanton tube is used as a direct measure of the local surface shearing stress. Calibration of the tube was made by means of a floating-element type of skin-friction balance. Calibration conditions range in Reynolds number based on free-stream conditions from 70,000 to 875,000. Supersonic Airfoil Performance With Small Heat Addition. Artur Mager. Journal of the Aero/Space Sciences, v. 26, Feb. 1959, p. gg-ro7. An analytical method is presented which permits a very rapid evaluation of the aerodynamic effects arising from the addition of small amounts of heat near supersonic two-dimensional air-foils. It is shown that even small amounts of heat generate a substantial pressure rise and thus cause appreciable changes in the aerodynamic coefficients.
of Uniformly Distributed Roughness on Turbulent Skin-Friction Drag at Supersonic Speeds. Frank E. Goddard, Jr. ,Journal of the Aero/ Space Sciences, v. 26, Jan. 1959, p. I + r5 pp. Effect
An experimental program was carried out in the r&in. by zo-in. supersonic wind tunnel of the Jet Propulsion Laboratory to determine the effect of uniformly distributed sand-grain roughness on the skin-friction drag of a body of revolution for the case of a turbulent
LITERATURE
AND
23-59L, March
rg5g. 13 pp., diagrs., photos. Results of the tire-to-surface friction measurements in braking on runways under varions surface conditions are presented and compared for a C-123B airplane and a friction cart. Comparisons of wet-surface friction studies with a rz-inch-diameter tire, an automobile tire, and an extra-high-pressure aircraft tire are also given.
Low Tire Friction and Cornering Forces on a Wet Surface. Eziaslav N. Harrin. NACA TN 4406, September 1958. 27 pp., diagrs., photos. An investigation was made by the National Advisory Committee for Aeronautics to study typical tire behavior on wet runways. A specially constructed tire treadmill served as a tire test vehicle whereas force measurements were made by means of a straingage balance. Values of maximum braking, full-skid braking, and rolling friction coefficients were obtained at yaw angles of o” and 4’ while operating two tire types (smooth and diamond treaded) in water depths from 0.02 to 0.09 inch and at speeds up to g4 feet per second including tire planing. Cornering-force coefficients were measured at the free-roll and maximum braking conditions. Study of Taxiing Problems Associated with Runway Roughness. Benjamin Milwitzky. NASA Memorandum z-ZI-59L, March rg5g. 12 pp., diagrs. This paper briefly summarizes available statistical data on airplane taxi operations, examines the profiles and power spectra of four selected runways and taxiways covering a wide range of surface roughness, considers (on the basis of theoretical and experimental results) the loads resulting from taxiing on such runways over a range of speeds and, by synthesis of the aforementioned results, proposes new criteria for runway and taxiway smoothness which are applicable to new construction and may also be used as a guide for determining when repairs are necessary. Investigation of the Maximum Spin-up Coefficients of Friction obtained during Tests of a Landing Gear having a Static-Load Rating of 20,000 Pounds. Sidney A. Batterson. NASA Memorandum IZ-20.58L, January rg5g. 24 pp. diagrs., photos., tab. An experimental investigation was made at the Langley landing loads track to obtain data on the maximum wheel spin-up coefficients of friction developed during landing. The forward speeds ranged from o to approximately 180 feet per second and the sinking speeds, from 2.7 to 9.4 feet per second. The results indicated the variation of the maximum spin-up coefficient of friction with forward speed and vertical load.
CURRENT
EVENTS
VOL.
2
(1958/59)
2.3. Skin friction Measurements of Skin Friction in a Plane Turbulent Wall Jet. A. Sigalla. Royal Aeronautical Society, Journal, v. 62, Dec. 1958, p. 873-877. Considers the inner layer of fluid between the wall and the position where the velocity is a maximum as a boundary layer with an outer uniform free stream of velocity equal to the local maximum velocity. Preliminary Investigations of Spiked Bodies at Hypersonic Speeds. Seymour M. Bogdonoff and Irwin E. Vas. Journal of the Aero/Space Sciences, v. 26, Feb. rg59, pp.2 65-74. An examination of the flow over blunt bodies equipped with a spike to minimize heattransfer rates. The use of a spike protruding from a hemispherical-nosed cylinder at M = 14 decreased the pressure level by an order of magnitude and the heat transfer to a fraction of that measured on a hemisphere without a spike. The general technique appears to hold considerable promise for hypersonic flight.
Use of a Stanton Tube for Skin-Friction Measurements. S. S. Abarbanel, R. J. Hakkinen, and L. Trilling. NASA Memorandum z-17-59 W, March rg5g. 48 pp., diagrs., photos. An experimental program is presented in which a Stanton tube is used as a direct measure of the local surface shearing stress. Calibration of the tube was made by means of a floating-element type of skin-friction balance. Calibration conditions range in Reynolds number based on free-stream conditions from 70,000 to 875,000. Supersonic Airfoil Performance With Small Heat Addition. Artur Mager. Journal of the Aero/Space Sciences, v. 26, Feb. 1959, p. gg-ro7. An analytical method is presented which permits a very rapid evaluation of the aerodynamic effects arising from the addition of small amounts of heat near supersonic two-dimensional air-foils. It is shown that even small amounts of heat generate a substantial pressure rise and thus cause appreciable changes in the aerodynamic coefficients.
of Uniformly Distributed Roughness on Turbulent Skin-Friction Drag at Supersonic Speeds. Frank E. Goddard, Jr. ,Journal of the Aero/ Space Sciences, v. 26, Jan. 1959, p. I + r5 pp. Effect
An experimental program was carried out in the r&in. by zo-in. supersonic wind tunnel of the Jet Propulsion Laboratory to determine the effect of uniformly distributed sand-grain roughness on the skin-friction drag of a body of revolution for the case of a turbulent