National Advisory Committee for Aeronautics (NACA) - 5,157 Matching Results

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Wind-Tunnel Tests of a Swept-Blade Propeller and Related Straight Blades Having Thickness Ratios of 5 and 6 Percent

Description: Report discussing the aerodynamic characteristics of three sets of blades over as wide a range of operating conditions as possible. One set of blades was conventional, one had blades that embodied sweep, and one was a nonswept set with thinner blade sections. The sweptback blades were found to be generally inferior to the straight blades, but the Mach numbers tested were not high enough to include speeds that might benefit from sweepback.
Date: November 10, 1948
Creator: Gray, W. H.
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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Wind-Tunnel Tests of the 1/25-Scale Powered Model of the Martin JRM-1 Airplane. 4 - Tests with Ground Board and with Modified Wing and Hull - TED No. NACA 232, Part 4, Tests with Ground Board and with Modified Wing and Hull, TED No. NACA 232

Description: From Summary: "Wind-tunnel tests were made of a 1/25 scale model of the Martin JRM-1 airplane to determine: (1) The longitudinal stability and control characteristics of the JRM-1 model near the water and lateral and directional stability characteristics with power while moving on the surface of the water, the latter being useful for the design of tip floats; (2) The stability and stalling characteristics of the wing with a modified airfoil contour; (3) Stability characteristics of a hull of la… more
Date: September 4, 1947
Creator: Lockwood, Vernard E. & Smith, Bernard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats

Description: Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparison… more
Date: July 5, 1957
Creator: James, Harry A. & Maki, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of the static longitudinal characteristics at low speed of a swept-wing airplane with blowing flaps and leading-edge slats

Description: Report presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Flap effectiveness and stability were maintained to high angles of attack by control of leading-edge flow separation with slats. An analysis of the take-off performance, landing performance, and comparisons with flight data are provide… more
Date: July 5, 1957
Creator: James, Harry A. & Maki, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of the static longitudinal characteristics at low speed of a swept-wing airplane with slotted flaps, area-suction flaps, and wing leading-edge devices

Description: Report presenting a low-speed wind-tunnel investigation of a high-wing airplane with an aspect ratio of 6.75 and 36 degrees of sweepback on the quarter-chord line in order to determine the lift increments obtainable with area-suction flaps. Comparisons were made to the slotted flaps normally used. Results regarding the flap lift, maximum lift and stability, and boundary-layer control requirements are provided.
Date: April 30, 1957
Creator: Maki, Ralph L. & James, Harry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests to Determine Aileron Characteristics of the McDonnell XFD-1 Airplane, TED No. NACA 23102

Description: "Tests were performed on a partial span of the wing of a McDonnell XFD-1 airplane to determine a combination of sealed internal balance and spring-tab stiffness for the aileron that would give satisfactory stick-force characteristics for the airplane. Two sealed internal balances were tested in combination with spring tabs of various stiffnesses. One of the combinations was tested at several speeds to determine the variation of stick force with speed" (p. 1).
Date: September 26, 1946
Creator: Yates, Campbell C. & Schneiter, Leslie E.
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
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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 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
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Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models

Description: Report presenting data gathered on a lateral-trim change or wing dropping that involves a rapid change of lateral trim with Mach number, which has occurred on several rocket-powered models used in roll investigations at transonic speeds. The data in this report demonstrates that straight wings with airfoil sections 9 percent thick or greater are susceptible to wing dropping between Mach numbers of 0.9 and 1.0. Results for straight, sweptback, and delta wings are provided.
Date: May 26, 1950
Creator: Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow investigation of the characteristics of seven unswept, untapered airfoils of aspect ratio 8.0

Description: Report presenting testing of a series of seven 10-percent-thick unswept and untapered airfoils of aspect ratio 8.0 using the wing-flow method at a range of Mach numbers. The most significant characteristic noted was the occurrence of an unstable pitching moment variation with angle of attack for small angles of attack at Mach numbers of 0.85 to 0.90 for all airfoils with a conventional thickness distribution. Results regarding lift characteristics, moment characteristics, and drag characteristi… more
Date: June 13, 1951
Creator: Crane, Harold L. & Adams, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow measurements of longitudinal stability and control characteristics of a canard airplane configuration with a 45 degree sweptback wing and a triangular all-movable control surface

Description: Report presenting measurements of the longitudinal stability and control characteristics of a canard airplane configuration using the wing-flow method. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model with control settings between several different degrees. The experimental data are presented in summarized or abridged form and calculated trim curves are presented for various flight loading conditions.
Date: August 25, 1950
Creator: Crane, Harold L. & Adams, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces

Description: Report presenting the results of an investigation at transonic speeds by the wing-flow method of the longitudinal stability characteristics of a 42.8 degree sweptback supersonic airplane configuration. Lift, pitching-moment, and rolling-moment characteristics of the semispan model as well as stabilizer hinge moments and effective downwash at the tail were measured over a range of Mach numbers. The wing-flow data is compared to data for the same configuration from other research facilities.
Date: April 3, 1950
Creator: Crane, Harold L. & Adams, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-Flow Study of Pressure-Drag Reduction at Transonic Speed by Projecting a Jet of Air From the Nose of a Prolate Spheroid of Fineness Ratio 6

Description: Report presenting a study of the pressure-drag reduction obtained by projecting a high-energy jet of air from the nose of a prolate spheroid at transonic speeds. Results regarding the pressure distribution on the body, pressure drag, shadowgraphs, and some notes regarding the slope of the body and level of shear at the jet exit are provided.
Date: October 26, 1951
Creator: Lopatoff, Mitchell
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow tests of a triangular wing of aspect ratio two 1: effectiveness of several types of trailing-edge flaps on flat-plate models

Description: Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.
Date: November 14, 1947
Creator: Rathert, George A., Jr. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory

Description: Report presenting flight tests to determine the pressure distribution over the wing of a swept-wing jet-propelled airplane over the flight range of lift coefficients for Mach numbers up to 1.11. Results regarding the section characteristics, load distribution, and trailing-edge loads are provided.
Date: April 14, 1952
Creator: Rolls, L. Stewart & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane

Description: From Summary: "Flight measurements of the aerodynamic wing loads on the D-558-II airplane have been made in the Mach number range from 1.0 to 2.0. Nonlinear wing-panel characteristics occurred with variations in angle of attack. These nonlinear characteristics were apparent primarily at the lower supersonic speeds."
Date: March 30, 1955
Creator: Robinson, Glenn H.; Cothren, George E., Jr. & Pembo, Chris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-load measurements of the Bell X-5 research airplane at a sweep angle of 58.7 degrees

Description: Report presenting a flight investigation over a range of altitudes and lift to determine the wing loads of the Bell X-5 research airplane at a sweep angle of 58.7 degrees at subsonic and transonic Mach numbers. Testing indicated that wing loads exhibit nonlinear trends over the angle-of-attack range from zero to maximum wing lift.
Date: April 4, 1955
Creator: Banner, Richard D.; Reed, Robert D. & Marcy, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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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Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds

Description: Report presenting measurements of wing loads made on the left wing of the Bell X-1 research airplane. Data are presented within a wing-panel normal-force coefficient and Mach number range. Results regarding span load distributions, wing-panel aerodynamic characteristics, and wing-to-fuselage carry over are provided.
Date: November 4, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4

Description: Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
Date: March 14, 1951
Creator: Gillis, Clarence L. & Vitale, A. James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date: November 30, 1955
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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Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keener, Earl R. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees

Description: Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.
Date: June 7, 1949
Creator: Schneiter, Leslie E. & Hagerman, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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