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Wind-tunnel technique for simultaneous simulation of external flow field about nacelle inlet and exit airstreams at supersonic speeds

Description: Report presenting an investigation of several ways of simultaneously simulating the external pressure field generated by an engine exhaust jet and an air inlet. The results indicated that the pressure field in the vicinity of the exit station and external to a real exhaust jet could be adequately simulated while keeping the inlet at critical or supercritical mass flow. Results for a target probe, a perforated probe, and the pressure and airflow required in the probes are provided.
Date: January 1957
Creator: Englert, Gerald W. & Luidens, Roger W.
Partner: UNT Libraries Government Documents Department

Effects of a J34 turbojet engine on supersonic diffuser performance

Description: Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.
Date: January 4, 1956
Creator: Beheim, Milton A. & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department

Pressure recovery, drag, and subcritical stability characteristics of conical supersonic diffusers with boundary-layer removal

Description: A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Date: February 27, 1952
Creator: Obey, Leonard T; Englert, Gerald W & Nussdorfer, Theodore J , Jr
Partner: UNT Libraries Government Documents Department

Pressure recovery, drag, and subcritical stability characteristics of three conical supersonic diffusers at stream Mach numbers from 1.7 to 2.0

Description: A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J; Obery, Leonard J & Englert, Gerald W
Partner: UNT Libraries Government Documents Department

Effect of jet-nozzle-expansion ratio on drag of parabolic afterbodies

Description: The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic afterbodies was studied at free-stream Mach numbers of 2.0, 1.6, and 0.6 over a range of jet pressure ratio. The influence of the jet on boattail and base drag was very pronounced. Study of the total external afterbody drag values at supersonic speeds indicated that, over most of the high-pressure-ratio range, increasing the nozzle design expansion ratio increased the drag even though the boattail area was reduced. Increasing the pressure ratio tended to increase slightly the total-drag increment caused by angle-of-attack operation.
Date: April 19, 1954
Creator: Englert, Gerald W.; Vargo, Donald J. & Cubbison, Robert W.
Partner: UNT Libraries Government Documents Department

Matching of auxiliary inlets to secondary-air requirements of aircraft ejector exhaust nozzles

Description: Report presenting an analysis of the problems associated with matching secondary-air requirements of ejector exhaust nozzles and auxiliary inlets has been made for free-stream Mach numbers up to 2.0. The analysis indicated that inlets located in the free stream supply higher pressure recovery than ejectors generally require for optimum net internal thrust at Mach numbers above about 1.4. Net-thrust gains can be achieved by immersing the auxiliary inlet in a boundary layer where the inlet-momentum penalty is less.
Date: August 16, 1955
Creator: Hearth, Donald P.; Englert, Gerald W. & Kowalski, Kenneth L.
Partner: UNT Libraries Government Documents Department