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Measurements in flight of the pressure distribution on the right wing of a P-39N-1 airplane at several values of Mach number

Description: Report presenting pressure-distribution measurements made on the right wing of a P-39N-1 airplane at values of Mach number up to 0.80. A considerable portion of the lift was carried by components of the airplane other than the wings, and the proportion carried by the wing varies considerably with Mach number. Results regarding the variation of wing loads and moments with Mach number, internal wing pressure, and airplane lift-curve slope are provided.
Date: April 1945
Creator: Clousing, Lawrence A.; Turner, William N. & Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department

Measurements of the pressure distribution on the horizontal-tail surface of a typical propeller-driven pursuit airplane in flight I: effects of compressibility in steady straight and accelerated flight

Description: Report presenting pressure-distribution measurements made in steady straight and accelerated flight over a horizontal tail surface of a typical pursuit airplane. Results regarding the variation of horizontal-tail loads with Mach number, variation of root bending moments and fuselage torsional moments with Mach number, and variation of section loads with Mach number are provided.
Date: July 1947
Creator: Sadoff, Melvin; Turner, William N. & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Measurements in flight of the pressure distribution on the right wing of a pursuit-type airplane at several values of Mach number

Description: Pressure-distribution measurements were made on the right wing of a pursuit-type airplane at values of Mach number up to 0.80. The results showed that a considerable portion of the lift was carried by components of the airplane other than the wings, and that the proportion of lift carried by the wings may vary considerably with Mach number, thus changing the bending moment at the wing root whether or not there is a shift in the lateral position of the center of pressure. It was also shown that the center of pressure does not necessarily move outward at high Mach numbers, even though the wing-thickness ratio decreases toward the wing tip. The wing pitching-moment coefficient increased sharply in a negative direction at a Mach lift-curve slope increased with Mach number up to values of above the critical value. Pressures inside the wing were small and negative.
Date: 1946
Creator: Clousing, Lawrence A.; Turner, William N. & Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department

Compressibility effects on the longitudinal stability and control of a pursuit-type airplane as measured in flight

Description: Measurements of the longitudinal stability and control of a pursuit-type airplane were made in flight up to a Mach number of 0.78. The data are presented in the form of curves showing the variation, with center-of-gravity position, dynamic pressure, and Mach number, of the stick-fixed and stick-free stability, control, and balance of the airplane.
Date: 1946
Creator: Turner, William N.; Steffen, Paul J. & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Flight measurements of horizontal tail loads on a typical propeller-driven pursuit airplane during stalled pull-outs at high speed

Description: Report presenting flight measurements of the pressures on the horizontal tail surfaces of a typical propeller-driven pursuit airplane during stalled pull-outs at high Mach number. Unit loads measured on the stabilizer at safe maneuvering limits were not only considerably in excess of the design unit loads, but also occurred in a direction opposite to the design loads. Revision of the tail-load design requirements and manner of specifying safe maneuverability limits to pilots appears necessary.
Date: April 25, 1944
Creator: Clousing, Lawrence A. & Turner, William N.
Partner: UNT Libraries Government Documents Department