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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
Use of source distributions for evaluating theoretical aerodynamics of thin finite wings at supersonic speeds

Use of source distributions for evaluating theoretical aerodynamics of thin finite wings at supersonic speeds

Date: January 1, 1950
Creator: Evvard, John C
Description: A series of publications on the source-distribution methods for evaluating the aerodynamics of thin wings at supersonic speeds is summarized, extended, and unified. Included in the first part are the deviations of: (a) the linearized partial-differential equation for unsteady flow at a substantially constant Mach number. b) The source-distribution solution for the perturbation-velocity potential that satisfies the boundary conditions of tangential flow at the surface and in the plane of the wing; and (c) the integral equation for determining the strength and the location of sources to describe the interaction effects (as represented by upwash) of the bottom and top wing surfaces through the region between the finite wing boundary and the foremost Mach wave. The second part deals with steady-state thin-wing problems. The third part of the report approximates the integral equation for unsteady upwash and includes a solution of approximate equation. Expressions are then derived to evaluate the load distributions for time-dependent finite-wing motions.
Contributing Partner: UNT Libraries Government Documents Department
The use of suction to prevent shock-induced separation in a nozzle

The use of suction to prevent shock-induced separation in a nozzle

Date: January 30, 1951
Creator: Sterrett, James R; Dunning, Robert W & Brevoort, Maurice J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the boundary layer of a cone to measure supersonic flow inclination

Use of the boundary layer of a cone to measure supersonic flow inclination

Date: June 1, 1952
Creator: Moore, Franklin K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the Coanda effect for jet deflection and vertical lift with multiple-flat-plate and curved-plate deflection surfaces

Use of the Coanda effect for jet deflection and vertical lift with multiple-flat-plate and curved-plate deflection surfaces

Date: September 1, 1958
Creator: Von Glahn, Uwe H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the Coanda effect for obtaining jet deflection and lift with a single flat-plate deflection surface

Use of the Coanda effect for obtaining jet deflection and lift with a single flat-plate deflection surface

Date: June 1, 1958
Creator: Von Glahn, Uwe H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model

Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model

Date: September 1, 1958
Creator: Woolston, Donald S & Sewall, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of the rolled-up vortex concept for predicting wing-tail interference and comparison with experiment at Mach number of 1.62 for a series of missile configurations having tandem cruciform lifting surfaces

The use of the rolled-up vortex concept for predicting wing-tail interference and comparison with experiment at Mach number of 1.62 for a series of missile configurations having tandem cruciform lifting surfaces

Date: September 24, 1952
Creator: Grigsby, Carl E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Date: July 24, 1956
Creator: vonGlahn, Uwe H.
Description: In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing 'tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. A 6-foot-chord airfoil was cut successively at the 50- and 30-percent-chord stations to produce the truncated airfoil sections, which were equipped with trailing-edge flaps that were used to alter the flow field about the truncated sections. The study was conducted at geometric angles of attack of 00 and 40, an airspeed of about 156 knots, and volume-median droplet sizes of 11.5 and 18.6 microns. A dye-tracer technique was used in the impingement studies. With the trailing-edge flap on the truncated airfoil deflected so that the local velocity distribution in the impingement region was substantially the same as that for the full-chord airfoil, the local impingement rates and the limits of impingement for the truncated and full-chord airfoils were the same. In general, truncating the airfoils with flaps undeflected resulted in a subs'tantially altered ...
Contributing Partner: UNT Libraries Government Documents Department
Use of two-dimensional data in estimating loads on a 45 degree sweptback wing with slats and partial-span flaps

Use of two-dimensional data in estimating loads on a 45 degree sweptback wing with slats and partial-span flaps

Date: November 1, 1953
Creator: Hunton, Lynn W & James, Harry A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of two-dimensional section data to estimate the low-speed wing lift coefficient at which section stall first appears on a swept wing

The use of two-dimensional section data to estimate the low-speed wing lift coefficient at which section stall first appears on a swept wing

Date: July 27, 1951
Creator: Maki, Ralph L
Description: None
Contributing Partner: UNT Libraries Government Documents Department