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 Collection: National Advisory Committee for Aeronautics Collection
Theoretical damping in roll and rolling moment due to differential wing incidence for slender cruciform wings and wing-body combinations

Theoretical damping in roll and rolling moment due to differential wing incidence for slender cruciform wings and wing-body combinations

Date: January 1, 1952
Creator: Adams, Gaynor J & DUGAN DUANE W
Description: A method of analysis based on slender-wing theory is developed to investigate the characteristics in roll of slender cruciform wings and wing-body combinations. The method makes use of the conformal mapping processes of classical hydrodynamics which transform the region outside a circle and the region outside an arbitrary arrangement of line segments intersecting at the origin. The method of analysis may be utilized to solve other slender cruciform wing-body problems involving arbitrarily assigned boundary conditions. (author).
Contributing Partner: UNT Libraries Government Documents Department
Flying qualities of a high-performance personal-owner airplane

Flying qualities of a high-performance personal-owner airplane

Date: November 8, 1951
Creator: Adams, James J & Lhitten, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Date: March 1, 1956
Creator: Adams, James J & Mathews, Charles, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane

Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane

Date: September 12, 1952
Creator: Adams, James J & Whitten, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Date: November 1, 1951
Creator: Adams, Mac C.
Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, ...
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of the effect of a local change in wing contour on chordwise pressure distribution at high speeds

Flight investigation of the effect of a local change in wing contour on chordwise pressure distribution at high speeds

Date: September 1, 1946
Creator: Adams, Richard E & Silsby, Norman S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method

Date: April 11, 1947
Creator: Adams, Richard E. & Silsby, Norman S.
Description: A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Downwash, Sidewash, and Mach Number Distribution behind a Rectangular Wing at a Mach Number of 2.41

Investigation of Downwash, Sidewash, and Mach Number Distribution behind a Rectangular Wing at a Mach Number of 2.41

Date: September 14, 1950
Creator: Adamson, D. & Boatright, William B.
Description: An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made. In addition the effect of the wing thickness on the sidewash with the wing at 0 angle of attack has been evaluated. Near an angle of attack of 0, agreement between theory and experiment is good, particularly for the downwash results, except in the plane of the wing, inboard of the tip. In this region the proximity of the shed vortex sheet and the departure of the spanwise distribution of vorticity from theory would account for the disagreement. At higher angles of attack prediction of downwash depends on a knowledge of the location of the trailing vortex sheet, in order that the downwash may be corrected for its displacement and distortion. The theoretical location of the trailing ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Date: January 1, 1957
Creator: Adamson, David & Boatright, William B
Description: An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight. In addition, the effect of wing thickness on the sidewash with the wing at 0 degree angle of attack has been evaluated.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests

Characteristics of the BMW 801D2 automatic engine control as determined from bench tests

Date: April 1, 1945
Creator: Addie, A N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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