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National Advisory Committee for Aeronautics Collection
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
Permallink:digital.library.unt.edu/ark:/67531/metadc62531/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc63663/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc57748/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc55259/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc54944/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc57198/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc61277/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc54985/
Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber
Date: January 17, 1957
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62879/
Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed
Date: January 1, 1946
Creator: Aiken, William S , Jr
Description: Symbols and definition of various airspeed terms that have been adopted as standard by the NACA subcommittee on aircraft structural design are presented. The equations, charts, and tables required in the evaluation of true airspeed, calibrated airspeed, equivalent airspeed, impact and dynamic pressures, and Mach and Reynolds numbers have been compiled. Tables of the standard atmosphere to an altitude of 65,000 feet and a tentative extension to an altitude of 100,000 feet are given along with the basic equations and constants on which both the standard atmosphere and the tentative extension are based.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60128/