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 Collection: National Advisory Committee for Aeronautics Collection
Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Effects of combinations of aspect ratio and sweepback at high subsonic Mach numbers

Date: June 4, 1947
Creator: Adler, Alfred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation with Mach Number of Static and Total Pressures Through Various Screens

Variation with Mach Number of Static and Total Pressures Through Various Screens

Date: February 1, 1946
Creator: Adler, Alfred A
Description: Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is.
Contributing Partner: UNT Libraries Government Documents Department
The Magnus effect in theory and in reality

The Magnus effect in theory and in reality

Date: May 1, 1930
Creator: Ahlborn, F
Description: A discussion of the Flettner rotor is presented from a nautical and economic viewpoint, and although it was a failure, the experimental and theoretical inventions cannot be disregarded. The following critical and experimental investigation will show the relations and applicability of the theories and practical applications. The Magnus effect is described in detail and a discussion and critical review of the Magnus effect is included.
Contributing Partner: UNT Libraries Government Documents Department
Turbulence and mechanism of resistance on spheres and cylinders

Turbulence and mechanism of resistance on spheres and cylinders

Date: January 1, 1932
Creator: Ahlborn, FR
Description: The nature of turbulent flow through pipes and around obstacles is analyzed and illustrated by photographs of turbulence on screens and straighteners. It is shown that the reversal of flow and of the resistance law on spheres is not explainable by Prandtl's turbulence in the boundary layer. The investigation of the analogous phenomena on the cylinder yields a reversal of the total field of flow. The very pronounced changes in pressure distribution connected with it were affirmed by manometric measurements on spheres by Professor O. Krell. The reversal in a homogenous nonvortical flow is brought about by the advance of the stable arrangement of Karman's dead air vortices toward the test object and by the substitution of an alternatingly one-sided or rotating but stable vortex formation in place of the initially symmetrical formation. This also explains the marked variations of the models.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of the horizontal-tail loads measured in flight on a multiengine jet bomber

Analysis of the horizontal-tail loads measured in flight on a multiengine jet bomber

Date: September 1, 1955
Creator: Aiken, William S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Comparison of Wing Loads Measured in Flight on a Fighter-Type Airplane by Strain-Gage and Pressure Distribution Methods

A Comparison of Wing Loads Measured in Flight on a Fighter-Type Airplane by Strain-Gage and Pressure Distribution Methods

Date: November 1, 1949
Creator: Aiken, William S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed

Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed

Date: September 1, 1946
Creator: Aiken, William S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Date: December 1, 1957
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed

Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed

Date: December 1, 1944
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight determination of wing and tail loads on a fighter-type airplane by means of strain-gage measurements

Flight determination of wing and tail loads on a fighter-type airplane by means of strain-gage measurements

Date: October 1, 1948
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department