UNT Libraries Government Documents Department - 5,163 Matching Results

Search Results

Some Research on the Lift and Stability of Wing-Body Combinations

Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.

Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield

Description: Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.
Date: September 29, 1958
Creator: Strass, H. K. & Goodman, V. M.

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

Description: From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."
Date: September 26, 1958
Creator: Mugler, John P , Jr

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

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.
Date: September 23, 1958
Creator: Nettle, J. Cary

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

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.
Date: September 23, 1958
Creator: Anderson, B. H. & Bowditch, D. N.