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Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Description: From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Date: March 24, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Analysis of a flight investigation at supersonic speeds of a simple homing system

Description: From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."
Date: January 10, 1956
Creator: Gardiner, Robert A.; Gillis, Clarence L. & Graves, G. B., Jr.
Partner: UNT Libraries Government Documents Department

Aircraft configurations developing high lift-drag ratios at high supersonic speeds

Description: From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."
Date: March 5, 1956
Creator: Eggers, A. J., Jr. & Syverton, Clarence A.
Partner: UNT Libraries Government Documents Department

Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Description: Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Date: September 1956
Creator: Love, Eugene S.
Partner: UNT Libraries Government Documents Department

An analysis of shock-wave cancellation and reflection for porous walls which obey an exponential mass-flow pressure-difference relation

Description: From Introduction: "In the present report a generalized exponential relation between pressure difference and normal flow is assumed which adequately describes porous-wall calibrations obtained experimentally at the Ames Laboratory and those presented in references 1 and 3."
Date: August 1954
Creator: Spiegel, Joseph M. & Tunnell, Phillips J.
Partner: UNT Libraries Government Documents Department

An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds

Description: From Introduction: "The present paper introduces the approximate method by means of which it is possible to calculate the pressures in the tip region of a rectangular with a symmetrical circular-arc section to a higher degree of accuracy than is possible with the usual linear methods."
Date: October 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department

Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Description: From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."
Date: July 1955
Creator: Martin, John C. & Malvestuto, Frank S., Jr.
Partner: UNT Libraries Government Documents Department

An analysis of supersonic aerodynamic heating with continuous fluid injection

Description: From Introduction: "The aerodynamic heating problem assumes considerable importance at high-supersonic speeds. Sanger and Bredt (reference 1) have calculated the high-speed aerodynamic forces and equilibrium surface temperature at extremely high altitudes where the molecular mean free path is large (free-molecule-flow region) compared with a characteristic body dimension. The theoretical investigation of Lees (reference 2) on the stability of the laminar boundary layer in compressible flow indicates that the laminar boundary layer is completely stable at all Reynolds numbers at supersonic speeds for a sufficiently low ratio of surface temperature to stream temperature."
Date: September 29, 1949
Creator: Klunker, E. G. & Ivey, H. Reese
Partner: UNT Libraries Government Documents Department

Investigation at supersonic speeds of some of the factors affecting the flow over a rectangular wing with symmetrical circular-arc section and 30-percent-chord trailing-edge flap

Description: Report presenting an investigation at supersonic speeds of some of the factors affecting the flow over a rectangular wing with a symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. The main purpose is to obtain more information on which to base the design of supersonic controls. Results regarding the effect of Mach number, effect of wing thickness, effect of fixing transition, effect of sealing the hinge gap, effect of model surface condition and asymmetry, and shock boundary-layer interaction are provided.
Date: January 2, 1951
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department

An investigation of the maximum lift of wings at supersonic speeds

Description: This report presents the results of an exploratory investigation carried out in the Langley 9-inch supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of random thickness distributions were tested at Mach numbers of 1.55, 1.90, and 2.32 and at Reynolds numbers varying between 0.74 x 10(6) and 0.27 x 10(6) at angles of attack ranging from zero up through the angle at which maximum lift occurred. Subsequent pressure-distribution tests on wings of triangular and rectangular plan forms were made at a Mach number of 2.40. The results of these tests substantiated the values of maximum lift obtained during the force tests and further showed no appreciable center-of-pressure shift over the entire angle-of-attack range.
Date: 1955
Creator: Gallagher, James J. & Mueller, James N.
Partner: UNT Libraries Government Documents Department

Investigation at Mach number 1.62 of the pressure distribution over a rectangular wing with symmetrical circular-arc section and 30-percent-chord trailing-edge flap

Description: Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.
Date: January 25, 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department