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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15231 - 15240 of 18,582
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Dynamic Lateral Behavior of High-performance Aircraft

Dynamic Lateral Behavior of High-performance Aircraft

Date: August 6, 1958
Creator: Moul, M. T. & Paulson, J. W.
Description: Dynamic lateral stability and control of high performance hypersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Date: August 6, 1958
Creator: Obery, L. J. & Stitt, L. E.
Description: Internal compression inlet with throat bleed-off at hypersonic flow.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an All-Internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0

Performance of an All-Internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0

Date: August 6, 1958
Creator: Stitt, Leonard E. & Obery, Leonard J.
Description: An all-internal conical compression inlet with annular bleed at the throat was investigated at Mach 5.0 and zero angle of attack. The minimum contraction ratio of the supersonic diffuser, coincident with a mass-flow ratio of 1.0, was determined to be 0.084 as compared with the isentropic contraction ratio of 0.04 at Mach 5.0. The over-all inlet performance was very sensitive to the amount of annular bleed at the throat because of the extensive boundary layer. For example, the critical recovery varied from 41 percent with 6-percent bleed to 59 percent with 25-percent bleed. Decreasing the spacing between the supersonic and subsonic diffusers increased the critical mass-flow ratio but reduced the range of subcritical mass-flow regulation. A constant-area section was required ahead of the subsonic diffuser in order to obtain reasonable performance. An inlet-engine net-thrust analysis indicated that the optimum performance occurred with from 20- to 25-percent bleed, depending on how the bypassed air was handled.
Contributing Partner: UNT Libraries Government Documents Department
A study of the combustion rates of hydrocarbon fuels with red fuming nitric acid in a small rocket engine

A study of the combustion rates of hydrocarbon fuels with red fuming nitric acid in a small rocket engine

Date: August 6, 1958
Creator: Baker, Louis, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the low-speed stability and performance characteristics of a jet-powered low-aspect-ratio vertical-take-off-and-landing configuration with engines buried in tiltable wings

Wind-tunnel investigation of the low-speed stability and performance characteristics of a jet-powered low-aspect-ratio vertical-take-off-and-landing configuration with engines buried in tiltable wings

Date: August 6, 1958
Creator: Scallion, William I & Cone, Clarence D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Date: August 11, 1958
Creator: Stoney, W. E., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Date: August 11, 1958
Creator: Stoney, William E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight, analog-simulator, and analytical studies of an automatically controlled interceptor which uses a bank-angle-error computer for lateral commands

Flight, analog-simulator, and analytical studies of an automatically controlled interceptor which uses a bank-angle-error computer for lateral commands

Date: August 11, 1958
Creator: Brissenden, R. F. & Cheatham, D. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Stability of ballistic reentry bodies

Stability of ballistic reentry bodies

Date: August 11, 1958
Creator: Bird, J. D. & Reese, D. E., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

Date: August 11, 1958
Creator: Sammonds, Robert I & Reynolds, Robert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department