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 Collection: Technical Report Archive and Image Library
Results 15391 - 15400 of 17,147
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Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Date: April 26, 1948
Creator: Braslow, A. L.; Visconti, F. & Burrows, D. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of a laminar boundary layer behind a suction point

Development of a laminar boundary layer behind a suction point

Date: March 1, 1952
Creator: Wuest, W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of drag and static longitudinal and lateral stability characteristics of a model of a 40.4 deg swept-wing airplane at Mach numbers of 1.56 and 2.06

Investigation of drag and static longitudinal and lateral stability characteristics of a model of a 40.4 deg swept-wing airplane at Mach numbers of 1.56 and 2.06

Date: January 18, 1957
Creator: Carmel, M. M. & Turner, K. L.
Description: Wind tunnel test to determine swept wing fighter aircraft drag, and logitudinal and lateral stablity at supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model

Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model

Date: July 14, 1958
Creator: Foss, W. E., Jr.; Lee, E. E., Jr. & Runckel, J. F.
Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers up to 1.9

Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers up to 1.9

Date: March 27, 1957
Creator: Petersen, R. B.
Description: Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions. The agreement between theoretical and experimental zero-lift wave-drag coefficients was generally very good, especially for a fuselage or for fuselage-wing combinations that were vertically symmetrical. For other models that had rapid changes in body shape and/or were not vertically symmetrical, the agreement of theory with experiment ranged from fair to poor, depending on the severity of the change in shape.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01

Date: May 16, 1958
Creator: Czarnecki, K. R. & Lord, D. R.
Description: Supersonic pressure distributions for tip and trailing edge controls on 60 deg delta wing.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Date: July 14, 1958
Creator: Presnell, John G., Jr.
Description: A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected. Directional stability data were obtained at M=3.51 for angles of attack of approximately 0 deg and 10 deg. These data, with summary data and typical schlieren photographs, are presented with only a brief analysis. The data indicate that the controls are effective throughout the Mach number range and lift-coefficient range (CL = -0.15 to 0.7, approximately) of the tests. There is a severe break in the pitching-moment curve at M=2.29 which might result in a pitch-up condition in flight, and also a large forward movement of the aerodynamic center with increasing Mach number that produces neutral longitudinal stability at ...
Contributing Partner: UNT Libraries Government Documents Department
A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9

A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9

Date: February 27, 1957
Creator: Mitcham, G. L.
Description: Longitudinal and lateral stability and control characteristics of swept wing fighter aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Measurement of static forces on externally carried bombs of fineness ratios 7.1 and 10.5 in the flow field of a swept-wing fighter- bomber configuration at a Mach number of 1.6

Measurement of static forces on externally carried bombs of fineness ratios 7.1 and 10.5 in the flow field of a swept-wing fighter- bomber configuration at a Mach number of 1.6

Date: January 31, 1957
Creator: Carlson, H. W. & Geier, D. J.
Description: Static force and interference drag on externally carried bomb in flow field of supersonic, swept wing fighter-bomber aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane

Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane

Date: January 24, 1958
Creator: Sellers, T. B.
Description: Horizontal tail flutter in fighter aircraft at transonic speeds.
Contributing Partner: UNT Libraries Government Documents Department