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Experimental effects of propulsive jets and afterbody configurations on the zero-lift drag of bodies of revolution at a Mach number of 1.59

Description: The present investigation was made at a free-stream Mach number of 1.59 to compare the afterbody drags to a series of conical boattailed models at zero angle of attack. Afterbody drags were obtained for both the power-off and the power-on conditions. Power-on drags were obtained as a function of afterbody fineness ratio, jet pressure ratio and divergence, and jet Mach number.
Date: April 22, 1954
Creator: de Moraes, Carlos A. & Nowitzky, Albin M.
Partner: UNT Libraries Government Documents Department

Collection of zero-lift drag data on bodies of revolution from free-flight investigations

Description: Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.
Date: September 3, 1957
Creator: Stoney, William E., Jr.
Partner: UNT Libraries Government Documents Department

Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-Lift Drag of Sweptback Low-Aspect-Ratio Wings

Description: Note presenting an investigation using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The linearized theory compared very favorably with the experimental results over most of the test range.
Date: June 1956
Creator: Pittel, Murray
Partner: UNT Libraries Government Documents Department

Summary of rocket-model tests at zero lift of an arrow-wing missile configuration from Mach numbers of 0.9 to 1.8

Description: Report presenting flight tests conducted between Mach numbers of 0.9 to 1.8 over a range of Reynolds numbers to determine the zero-lift drag and some rolling-effectiveness characteristics of a proposed long-range, supersonic, ground-to-ground missile. Results regarding the longitudinal trim, drag, rolling effectiveness, and instability due to roll are provided.
Date: January 14, 1954
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department

Experimental determination of the range of applicability of the transonic area rule for wings of triangular plan form

Description: From Summary: "Experimental measurements have been made of the zero-lift drag rise at transonic speeds of a family of triangular plan form wings of varying thickness and aspect ratio mounted on a cylindrical body. Together with the transonic similarity parameters, the results of the tests are used to define the range of applicability of the transonic area rule for wings of triangular plan form. The significance of the test results is discussed."
Date: December 1956
Creator: Page, William A.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the zero-lift drag of several wings at supersonic Mach numbers extending to 2.6

Description: Report presenting testing of the zero-lift drag of several wings at supersonic Mach numbers. The delta wings had the lowest drag over the entire Mach number range. Results regarding the variation of Reynolds number with Mach number, total drag coefficient, wing-plus-interference drag coefficients, and skin friction drag are provided.
Date: December 2, 1952
Creator: Hopko, Russell N. & Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10

Description: Report presenting free-flight measurements of the zero-lift drag of a cruciform-finned body at a range of Mach and Reynolds numbers. Results regarding experimental total drag, comparison of theory with experiment, comparison of experiment with NOL results, boundary-layer transition, Reynolds number effects, and fin leading-edge shape are provided.
Date: June 11, 1953
Creator: James, Carlton S. & Carros, Robert J.
Partner: UNT Libraries Government Documents Department

Flutter experiences with thin pointed-tip wings during flight tests of rocket-propelled models at Mach numbers from 0.8 to 1.95

Description: Report presenting flutter data over a range of Mach numbers in free-flight testing of several wing-body combinations as part of a general zero-lift drag investigation. The wings all had the same streamwise airfoil sections and the plan-form variations consisted of delta wings, diamond wings, and an arrow wing. Time histories of model speed, Mach number, and air density are provided for each model as well as flutter frequency, amplitude, and reduced-frequency parameter plotted as functions of model speed.
Date: April 4, 1955
Creator: Wallskog, Harvey A.
Partner: UNT Libraries Government Documents Department