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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15231 - 15240 of 17,147
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A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

Date: September 20, 1958
Creator: Heinle, D. R. & Turner, H. L.
Description: Effects of manual attack-display noise filtering on pilot tracking performance.
Contributing Partner: UNT Libraries Government Documents Department
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external- compression inlet

Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external- compression inlet

Date: September 23, 1958
Creator: Cubbison, R. N. & Samanich, N. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external-compression inlet

Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external-compression inlet

Date: September 23, 1958
Creator: Cubbison, R W & Samanich, N E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Date: September 23, 1958
Creator: Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Date: September 23, 1958
Creator: Nettle, J. Cary
Description: A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0

Date: September 23, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Date: September 26, 1958
Creator: Mugler, John P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89

Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89

Date: September 26, 1958
Creator: Bond, Aleck C.; Lee, Dorothy B. & Rumsey, Charles B.
Description: Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices

Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices

Date: September 26, 1958
Creator: Aoyagi, Kiyoshi & Hickey, David H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Date: September 26, 1958
Creator: Lampkin, Bedford A & Tunnell, Phillips J
Description: None
Contributing Partner: UNT Libraries Government Documents Department