National Advisory Committee for Aeronautics (NACA) - 14 Matching Results

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Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

Description: Report presenting an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.
Date: December 17, 1951
Creator: Frank, Joseph L. & Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design and Evaluation of a Turbojet Exhaust Simulator, Utilizing a Solid-Propellant Rocket Motor, for Use in Free-Flight Aerodynamic Research Models

Description: A method has been developed for modifying a rocket motor so that its exhaust characteristics simulate those of a turbojet engine. The analysis necessary to the design is presented along with tests from which the designs are evaluated. Simulation was found to be best if the exhaust characteristics to be duplicated were those of a turbojet engine at high altitudes and with the afterburner operative.
Date: December 17, 1954
Creator: de Moraes, Carlos A.; Hagginbothom, William K., Jr. & Falanga, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Description: Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of rigid spoilers on the two-dimensional flutter derivatives of airfoils oscillating in pitch at high subsonic speeds

Description: Report presenting a study of the effects of spoilers with fixed heights equal to 2.5 to 4 percent of the airfoil chord on the aerodynamic lift and moment flutter derivatives of oscillating two-dimensional airfoils. Results regarding the typical effects of spoiler deflection, effects of Mach number, and aerodynamic torsional instability boundaries for fixed spoiler heights as affected by airfoil profile are provided.
Date: December 17, 1954
Creator: Monfort, James C. & Wyss, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-scale investigation of cooling shroud and ejector nozzle for a turbojet engine: afterburner installation

Description: From Summary: "A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to… more
Date: December 17, 1951
Creator: Wallner, Lewis E. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution

Description: Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.
Date: December 17, 1954
Creator: Bromm, August F., Jr. & O'Donnell, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of a Series of Cone-Cylinder Configurations at a Mach Number of 6.86

Description: Report presenting the results of pressure-distribution and force tests of two cone-cylinder configurations and a comparison with theoretical calculations. The first series was made up of three configurations with 20 degree conical noses and cylindrical afterbodies with 0, 2, and 4 diameter lengths and the second was made up of cylindrical afterbodies with a diameter length and conical noses with apex angles of 10 to 180 degrees. Results regarding the pressure distributions, aerodynamic forces, … more
Date: December 17, 1951
Creator: Cooper, Ralph D. & Robinson, Raymond A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Motions Encountered with the Douglas D-558-II All-Rocket Research Airplane During Exploratory Flights to a Mach Number of 2.0

Description: Memorandum presenting flight tests performed with the Douglas D-558-II research airplane in order to determine the lateral handling characteristics in straight flight at supersonic speeds. It primarily describes the lateral motions obtained at moderate and low angles of attack during a preliminary survey in pushovers and straight flight at supersonic Mach numbers up to about 2.0 at altitudes between 50,000 and 70,000 feet.
Date: December 17, 1954
Creator: Ankenbruck, Herman O. & Wolowicz, Chester H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Use of Conical Flow Separation for Efficient Supersonic Diffusion

Description: Use of flow separation on a rod projecting upstream of a blunt body to decelerate the supersonic stream ahead of an annular nose inlet was investigated at Mach numbers of 1.76, 1.93, and 2.10. Maximum pressure recoveries were obtained with rod tip projections about 1.5 times the radius of the spherical nose and were higher than those obtained with single-shock solid cones. Subcritical operation was similar to that observed with solid-cone inlets, but the effect of angle of attack on maximum pre… more
Date: December 17, 1951
Creator: Moeckel, W. E. & Evans, P. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of horizontal tails 3: unswept and 35 degrees swept-back plan forms of aspect ratio 6

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. Test results are provided for models with and without standard roughness on their leading edges and with sealed and unsealed radius-nose elevators. Results regarding effectiveness and hinge-moment parameters, static longitudinal stability, effect of standard roughness, and effect of removing the elevator nose … more
Date: December 17, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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