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Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a 1/4-scale Bell X-5 airplane model

Description: From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general."
Date: December 4, 1951
Creator: Kemp, William B., Jr. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Description: Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provided.
Date: January 4, 1951
Creator: Evans, Albert J. & Liner, George
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Body of revolution

Description: From Summary: "The lift, drag, and pitching moment of a body of revolution are presented for Mach numbers from 0.60 to 0.92 and from 1.20 to 1.70. These data were obtained at test Reynolds numbers of 0.64 million, 1.02 million, and 1.59 million."
Date: October 4, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Altitude-wind-tunnel investigation of performance characteristics of a J47D prototype (RX1-1) turbojet engine with fixed-area exhaust nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
Partner: UNT Libraries Government Documents Department

Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4

Description: Report presenting an experimental investigation of the downwash and sidewash flow angles in a transverse plane behind a cruciform-wing and body combination. The wing-body combination had a cruciform arrangement of two identical triangular wings of aspect ratio 2.31 corresponding to a leading-edge sweep angle of 60 degrees placed on a body of fineness ratio of 16. The investigation was conducted at a specified Mach and Reynolds number and a range of angles of bank and attack.
Date: April 4, 1951
Creator: Wetzel, Benton E. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination

Description: Report presenting measurements made at a Mach number of 0.25 of the aerodynamic characteristics of a wing with an aspect ratio of 3 combined separately with three geometrically similar bodies of revolution with the same fineness ratio but differing sizes. Results regarding wings, bodies of revolution, wing in the presence of the bodies, wing combined with the bodies of revolution, and effect of wing incidence changes are provided.
Date: October 4, 1951
Creator: Hopkins, Edward J. & Carel, Hubert C.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a tip-to-tip bomber-fighter coupled airplane configuration

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with freedom in roll and pitch, and with freedom in roll, pitch, and yaw are provided.
Date: April 4, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Partner: UNT Libraries Government Documents Department