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An investigation of jet effects on adjacent surfaces

Description: From Summary: "The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit."
Date: June 28, 1955
Creator: Bressette, Walter E. & Faget, Maxime A.
Partner: UNT Libraries Government Documents Department

Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration

Description: Report presenting an investigation of a free-flight model of a delta-wing configuration with four engines mounted two to a nacelle below the wing with rocket turbojet simulators operating at a range of Mach numbers. Results regarding wing pressure coefficients, fuselage pressure coefficient, airplane aerodynamic characteristics, and airplane trim are provided.
Date: August 16, 1957
Creator: Judd, Joseph H. & Falanga, Ralph A.
Partner: UNT Libraries Government Documents Department

Investigation of jet effects on a flat surface downstream of the exit of a simulated turbojet nacelle at a free-stream Mach number of 1.39

Description: Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.
Date: April 2, 1956
Creator: Bressette, Walter E. & Leiss, Abraham
Partner: UNT Libraries Government Documents Department

Free-flight transonic model investigation of jet effects on a fighter-type configuration employing a tail boom and three horizontal-tail positions

Description: Report presenting the results of a limited research program initiated to study the effects of a hot propulsive jet on the longitudinal stability characteristics of a fighter-type airplane configuration. The data was obtained from a rocket-boosted free-flight model investigation over a range of Mach numbers using four models that differed only in the position and size of the horizontal tail. Results regarding the time histories, trim, normal force, pitching moment, aerodynamic-center location, dynamic stability, trim drag, and pressure data are provided.
Date: February 20, 1958
Creator: Jackson, Bruce G.
Partner: UNT Libraries Government Documents Department

Free-flight investigation at transonic speeds of drag coefficients of a boattail body of revolution with a simulated turbojet exhaust issuing at the base from conical short-length ejectors

Description: Report presenting tests of four 7.5 degree boattail bodies of revolution with secondary air scoops in free flight to find the change in drag coefficient when a simulated turbojet exhaust issued from conical short-length ejectors. Results indicated that the jet-on total drag coefficients were lower throughout the test Mach number range than corresponding jet-off values of the forebody drag coefficient. Results regarding drag and ejector-shroud characteristics are provided.
Date: December 13, 1956
Creator: Falanga, Ralph A. & Leiss, Abraham
Partner: UNT Libraries Government Documents Department