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Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Description: From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."
Date: August 6, 1957
Creator: Strass, H. Kurt & Stephens, Emily W.
Partner: UNT Libraries Government Documents Department

Application of a windshield-display system to the low-altitude bombing problem

Description: From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."
Date: January 4, 1957
Creator: Barnett, Robert M.; Kaufman, William M. & Fulcher, Elmer C.
Partner: UNT Libraries Government Documents Department

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection

Description: From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."
Date: June 15, 1948
Creator: Dietz, Robert O., Jr.; Wishnek, George & Kuenzig, John K.
Partner: UNT Libraries Government Documents Department

Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Description: From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."
Date: February 10, 1947
Creator: Krebs, Richard P & Palasics, John
Partner: UNT Libraries Government Documents Department