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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15221 - 15230 of 17,147
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Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Date: September 10, 1958
Creator: Cocke, Bennie W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and Experimental Investigation of a Single-stage Turbine With a Rotor Entering Relative Mach Number of 2

Design and Experimental Investigation of a Single-stage Turbine With a Rotor Entering Relative Mach Number of 2

Date: September 15, 1958
Creator: Moffitt, T. P.
Description: Design of single-stage turbine for rotor entering at supersonic speed - performance characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Date: September 15, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7.
Contributing Partner: UNT Libraries Government Documents Department
The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

Date: September 15, 1958
Creator: Lopez, Armando E & Tinling, Bruce E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Date: September 15, 1958
Creator: Kelly, Mark W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Date: September 17, 1958
Creator: Gloria, H. R.; Sarabia, M. F. & Syvertson, C. A.
Description: Aerodynamic performance characteristics and static stability and control of hypersonic glider with arrow planform wings.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18

Date: September 17, 1958
Creator: Syvertson, Clarence A; Gloria, Hermilo R & Sarabia, Michael F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Date: September 17, 1958
Creator: Lazzeroni, Frank A.
Description: Wind tunnel tests of wingless low aspect ratio folding control missile configurations.
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the buffeting loads on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane

Measurements of the buffeting loads on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane

Date: September 17, 1958
Creator: Rainey, A Gerald & Igoe, William B
Description: The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizontal tail of the airplaneand of the model indicated that the model horizontal tail, which was of conventional force-test-model design, responded in an entirely different mode than did the airplane.This result implied that if quantitative extrapolation of model data to flight conditions were desired a dynamically scaled model of the rearward portion of the fuselage and empennage would be required. A study of the sources of horizontal-tail buffeting of the model indicated that the wing wake contributed a large part of the total buffeting load. At one condition it was found that removal of the wing wake would reduce the buffeting loads on the horizontal tail to about one-third of the original value.
Contributing Partner: UNT Libraries Government Documents Department
Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14

Date: September 17, 1958
Creator: Coltrane, Lucille C
Description: None
Contributing Partner: UNT Libraries Government Documents Department