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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

Estimated lift-drag ratios at supersonic speed

Description: Report presenting recent developments in supersonic flow theory that are applied to obtain estimates of the lift-drag ratios that may be achieved by aircraft employing sweptback wings. As the speed increases in the supersonic range, the attainable lift-drag ratios decrease and the gain due to sweepback also diminishes. Results regarding the airplane with constant chord sweptback wing, airplane with tapered wing, effect of plan form, airfoil section, friction drag, and optimum wing loading and altitude are provided.
Date: July 1947
Creator: Jones, Robert T.
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

Optimum Lifting Bodies at High Supersonic Airspeeds

Description: Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.
Date: May 7, 1954
Creator: Rosnikoff, Meyer M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Experimental Lift-Drag Ratios for Two Families of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting experimental force and moment characteristics, including lift-drag ratios, which have been measured and briefly studied for two families of wing-body combinations. One family consisted of essentially arrow wings with half conical bodies. The other consisted of a fineness-ratio-12 body of revolution alone and with flat-plate triangular wings of aspect ratios ranging from 0.375 to 1.8.
Date: March 10, 1958
Creator: Jorgensen, Leland H.
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