National Advisory Committee for Aeronautics (NACA) - 867 Matching Results

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Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds

Description: Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.
Date: January 10, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the damping in roll of the Bell X-1E research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.
Date: April 26, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the damping in roll of the Douglas D-558-II research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Douglas D-558-II research airplane and its components have been obtained at five different Mach numbers. Large effects of Reynolds number, boundary layer, and wing-incidence angle on the damping in roll were obtained.
Date: September 7, 1956
Creator: McDearmon, Russell W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds

Description: From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."
Date: September 26, 1956
Creator: Hammond, Alexander D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bump method

Description: Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.
Date: June 1956
Creator: Emerson, Horace F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Effect of Nose Ring Spoilers on a Low-Speed Slowly Spinning Fin-Stabilized Rocket

Description: Memorandum presenting an investigation made in the stability tunnel with a model of a low-speed slowly spinning fin-stabilized rocket to determine the effectiveness of a nose ring spoiler in reducing the unstable Magnus moments on a sting-mounted completely spinning model and, if possible, to find the effect of a nonspinning center section, used in a previous investigation, on the unstable Magnus moment.
Date: July 20, 1956
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Interference Effects during Separation of a 1/40-Scale Model Convair B-58 Airplane and Store at Mach Numbers of 1.41, 1.61, and 2.01

Description: "An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a 1/40-sca!e pod-separation model of the Convair B-58 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete return component and the complete pod with its canard controls were tested, both alone and in the presence of each other, at Mach numbers of 1.61 and 2.01. The complete pod and various combinations of its components were tested alone at Mach numbe… more
Date: December 28, 1956
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Two Vertical-Takeoff-and-Landing Jet Bomber Airplane Configurations at Mach Numbers of 1.94 and 2.40

Description: Report presenting an investigation to obtain information about the basic aerodynamic characteristics of two vertical-take-off-and-landing jet bomber airplanes, one with a high wing and one with a low wing. Results regarding pitch and sideslip are provided. The high-tail configurations were found to have higher lift-drag ratios for both high- and low-wing models.
Date: October 31, 1956
Creator: Jones, Robert A. & Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Results regarding the methods of analysis and vertical-tail contributions are provided.
Date: November 1956
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Measurements of Wing Buffeting on 1/16-Scale Model of Douglas D-558-II Research Airplane

Description: Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in mode… more
Date: September 24, 1956
Creator: Kemp, William B., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of blowing boundary-layer control with jet pressure ratios up to 9.5 on the trailing-edge flaps of a 35 degree sweptback wing airplane

Description: Report presenting a full-scale wind-tunnel investigation to determine whether the effects of blowing high-velocity air over trailing-edge flaps could be adequately correlated by jet momentum over a range of jet velocities. Good correlation of lift with jet momentum was obtained over the range of jet pressure ratios.
Date: October 26, 1956
Creator: Kelly, Mark W. & Tucker, Jeffrey H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-Body Combinations With Certain Geometric Restraints Having Low Zero-Lift Wave Drag at Low Supersonic Mach Numbers

Description: "Several variational problems involving optimum wing and body combinations having minimum wave drags for different kinds of geometrical restraints are analyzed. Particular attention is paid to the effect on the wave drag of shortening the fuselage and, for slender axially symmetric bodies, the effect of fixing the fuselage diameter at several points or even of fixing whole portions of its shape" (p. 1).
Date: February 1956
Creator: Lomax, Harvard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio have been determined for Mach numbers of 1.97 and 3.33. The angle-of-attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. The results of the investigation indicate that there are distinct aerodynamic advantages to the use of highly swept wings of very low aspect ratio.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing loads and load distributions throughout the lift range of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the left wing of the Douglas X-3 to determine the effects of angle of attack and Mach number on the wing characteristics at transonic Mach numbers. The wing had an aspect ratio of 3.09 and a modified 4.5-percent-thick hexagonal section. Data covered a range of lift values and Mach numbers.
Date: November 9, 1956
Creator: Keener, Earl R. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

Description: An extensive program was undertaken to investigate the effect of several geometric variables on the performance of two-dimensional inlets. This investigation included inlets having single-wedge, double-wedge, and isentropic compression ramps with various side-plate configurations and subsonic diffusers. The tests were conducted over a range of Reynolds number based on inlet height from 0.50 to 2.67(sup x)10(sup 6). Generally, the performance levels of the two-dimensional inlets were somewhat be… more
Date: February 29, 1956
Creator: Woollett, Richard R. & Connors, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10

Description: Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.
Date: July 26, 1956
Creator: Stoney, William E., Jr. & Royall, John F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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