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in subjects: "lift-drag ratios"  
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Idealized wings and wing-bodies at a Mach number of 3

Description: Report presenting the theoretical possibilities for obtaining high lift-drag ratios at M = 3 and to describe some experiments designed to exploit the theory. Relatively high lift-drag ratios calculated were partly realized at low wind-tunnel Reynolds numbers. The rate of increase in maximum lift-drag ratio with increased Reynolds number was greater than expected, which indicated a need for more experiments at conditions closer to actual flight.
Date: July 1958
Creator: Katzen, Elliott D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Investigation of the effects of profile shape on the aerodynamic and structural characteristics of thin, two-dimensional airfoils at supersonic speeds

Description: Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.
Date: May 7, 1954
Creator: Katzen, Elliott D.; Kuehn, Donald M. & Hill, William A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Investigation of the effects of profile shape on the aerodynamic and structural characteristics of thin, two-dimensional airfoils at supersonic speeds

Description: Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.
Date: September 1957
Creator: Katzen, Elliott D.; Kuehn, Donald M. & Hill, William A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Some properties of wing and half-body arrangements at supersonic speeds

Description: Report presenting an investigation of the certain wing-body combinations as measured by the lift-drag ratio for two arrangements: a half-cone mounted under a triangular wing and a half Newtonian ogive similarly mounted. The configurations were tested for a range of Mach numbers from 1.5 to 5.0. Results regarding the comparison of a half-cone versus a full cone and calculated maximum lift-drag ratio are provided.
Date: July 22, 1957
Creator: Migotsky, Eugene & Adams, Gaynor J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Investigation of the effects of leading-edge flaps on the aerodynamic characteristics in pitch at Mach numbers from 0.40 to 0.93 of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4

Description: Report presenting an investigation to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45 degree sweptback wing. All of the flaps were found to reduce the drag in the medium lift range , but there were no significantly large effects on the lift characteristics for any of the arrangements studied.
Date: August 20, 1953
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4

Description: Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date: July 1958
Creator: Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department