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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Wind-Tunnel Tests of the 1/25-Scale Powered Model of the Martin JRM-1 Airplane. IV - 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

Wind-Tunnel Tests of the 1/25-Scale Powered Model of the Martin JRM-1 Airplane. IV - 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

Date: September 4, 1947
Creator: Lockwood, Vernard E. & Smith, Bernard J.
Description: 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 larger design gross weight; The test results indicated that the elevator was powerful enough to trim the original model in a landing configuration at any lift coefficient within the specified range of centers of gravity. The ground-board tests for evaluating the aerodynamic forces and moments on an airplane in a simulated cross wind indicate a high dihedral effect in the presence of the ground board and, consequently, during low-speed taxying and take-off, large overturning moments would result which would have to be overcome by the tip floats.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of the static longitudinal characteristics at low speed of a swept-wing airplane with blowing flaps and leading-edge slats

Wind-tunnel tests of the static longitudinal characteristics at low speed of a swept-wing airplane with blowing flaps and leading-edge slats

Date: July 5, 1957
Creator: James, Harry A & Maki, Ralph L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-wing Airplane With Blowing Flaps and Leading-edge Slats

Wind-tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-wing Airplane With Blowing Flaps and Leading-edge Slats

Date: April 5, 1957
Creator: James, H. A. & Maki, R. L.
Description: Low speed aerodynamic characteristics of swept- wing aircraft with blowing flaps and leading-edge slats.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 30, 1957
Creator: Maki, Ralph L & James, Harry A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests to Determine Aileron Characteristics of the McDonnell XFD-1 Airplane, TED No. NACA 23102

Wind-Tunnel Tests to Determine Aileron Characteristics of the McDonnell XFD-1 Airplane, TED No. NACA 23102

Date: September 26, 1946
Creator: Yates, Campbell C. & Schneiter, Leslie E.
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. Estimates, based on the results of the tests, indicate that for this airplane any reduction of stick force by use of the spring tab reduces the helix angle pb/2V below the required value of 0.09. The estimates show that, of the configurations tested, the most satisfactory combination for obtaining a stick force of 30 pounds at 300 miles per hour indicated airspeed is a 0.48-chord internal balance in combination with a spring-tab stiffness of 500 pounds per inch. With this combination, a wing-tip helix angle of 0.078 is estimated. Stick-force curves for all configurations show a rapid increase in stick force above approximately 20 deg. total aileron deflection.
Contributing Partner: UNT Libraries Government Documents Department
Wing-body combinations with wings of very low aspect ratio at supersonic speeds

Wing-body combinations with wings of very low aspect ratio at supersonic speeds

Date: October 26, 1956
Creator: Jorgensen, L. H. & Katzen, E. D.
Description: Wing-body combinations with wings of very low aspect ratio at supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Wing-body combinations with wings of very low aspect ratio at supersonic speeds

Wing-body combinations with wings of very low aspect ratio at supersonic speeds

Date: October 26, 1956
Creator: Jorgenson, Leland H & Katzen, Eliott D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models

Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models

Date: May 26, 1950
Creator: Stone, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-flow investigation of the characteristics of seven unswept, untapered airfoils of aspect ratio 8.0

Wing-flow investigation of the characteristics of seven unswept, untapered airfoils of aspect ratio 8.0

Date: June 13, 1951
Creator: Crane, Harold L & Adams, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: August 25, 1950
Creator: Crane, Harold L & Adams, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department