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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
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
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 & Howard, Donald A
Description: None
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 & Wiener, Bernard
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
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: 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
Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber

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 & Fisher, Raymond A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

Date: March 19, 1951
Creator: Aiken, William S., Jr. & See, John A.
Description: Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.
Contributing Partner: UNT Libraries Government Documents Department
Extension of pack method for compressive tests

Extension of pack method for compressive tests

Date: December 1, 1940
Creator: Aitchison, C S
Description: The pack method for determining compressive stress-strain graphs described in NACA Report No. 649 has been modified to extend it's application to thinner gages and stronger materials. The principal modifications consisted in the provision of additional support against instability cementing the specimens of the pack together with fused shellac and the provision of special clamps to hold the specimens together while the test is in progress. The shellac was found to increase the buckling load of the pack without any appreciable effect on the compressive stress-strain graph of the material. The extended pack method described in this note has made possible the application of stresses in excess of 220 kips per square inch to sheet material having a thickness of only 0.02 inch.
Contributing Partner: UNT Libraries Government Documents Department
A subpress for compressive tests

A subpress for compressive tests

Date: December 1, 1943
Creator: Aitchison, C S & Miller, James A
Description: A subpress for compressive tests is described. The subpress was designed primarily for use in developing and investigating methods for testing thin sheet metal in compression. Provision was made for testing fixed-end and flat-end specimens with or without various types of lateral support against buckling. Compressive stress-strain data for a sheet of 0.032-inch 24S-RT aluminum alloy were obtained with the subpress by the pack method and by the single-thickness method. The data showed small scatter and the stress-strain curves obtained by the two methods were in close agreement.
Contributing Partner: UNT Libraries Government Documents Department
Tensile and compressive tests of magnesium alloy J-1 sheet

Tensile and compressive tests of magnesium alloy J-1 sheet

Date: December 1, 1943
Creator: Aitchison, C S & Miller, James A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The pack method for compressive tests of thin specimens of materials used in thin-wall structures

The pack method for compressive tests of thin specimens of materials used in thin-wall structures

Date: January 1, 1939
Creator: Aitchison, C S & Tuckerman, L B
Description: The strength of modern lightweight thin-wall structures is generally limited by the strength of the compression members. An adequate design of these members requires a knowledge of the compressive stress-strain graph of the thin-wall material. The "pack" method was developed at the National Bureau of Standards with the support of the National Advisory Committee for Aeronautics to make possible a determination of compressive stress-strain graphs for such material. In the pack test an odd number of specimens are assembled into a relatively stable pack, like a "pack of cards." Additional lateral stability is obtained from lateral supports between the external sheet faces of the pack and outside reactions. The tests seems adequate for many problems in structural research.
Contributing Partner: UNT Libraries Government Documents Department
Experimental determination of local and mean coefficients of heat transfer for turbulent flow in pipes

Experimental determination of local and mean coefficients of heat transfer for turbulent flow in pipes

Date: February 1, 1954
Creator: Aladyev, I T
Description: An extensive investigation of the changes of the local and mean heat-transfer coefficients along the pipe length, and some results.
Contributing Partner: UNT Libraries Government Documents Department
Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Date: May 1, 1927
Creator: Alcock, J F
Description: In this report is described an experimental method which the writer has evolved for dealing with air-cooled engines, and some of the data obtained by its means. Methods of temperature measurement and cooling are provided.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers

Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers

Date: April 1, 1944
Creator: Alexander, S R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of a 34 degree swept-forward and swept-back NACA 65-009 airfoil of aspect ratio 2.7 as determined by flight tests at supersonic speeds

Drag measurements of a 34 degree swept-forward and swept-back NACA 65-009 airfoil of aspect ratio 2.7 as determined by flight tests at supersonic speeds

Date: February 20, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Date: April 8, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of symmetrical circular-arc and NACA 65-009 rectangular airfoils having an aspect ratio of 2.7 as determined by flight tests at supersonic speeds

Drag measurements of symmetrical circular-arc and NACA 65-009 rectangular airfoils having an aspect ratio of 2.7 as determined by flight tests at supersonic speeds

Date: March 7, 1947
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Flight investigations at low supersonic speeds to determine the effectiveness of cones and a wedge in reducing the drag of round-nose bodies and airfoils

Date: March 3, 1949
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department