Pressure measurements for mach five flows over winged re-entry configurations with aerodynamic controls.

"February 1964."Includes bibliograpical references (page 5).Air Force Contract No.Mode of access: Internet

Pressure measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

"January 1964."Includes bibliographical references (page 5).Air Force Contract No.Mode of access: Internet

Pressure and heat transfer measurements for Mach 8 flows over a blunt pryamidal configuration with aerodynamic controls.

Includes bibliograpical references (pages 7-8 ).Air Force Contract No.Mode of access: Internet

Final test report : X-29A Vortex Flow Control (VFC) flight test results /

"Final Report for 09/27/90 - 09/27/93.""November 1993."Includes bibliographical references (page 114).Research supported by the United States Air Force Flight Dynamics Directorate, and performed in part by Grumman Aircraft System, Bethpage, New York, under Contract No.Mode of access: Internet

Pressure measurements for mach five flows over winged re-entry configurations with aerodynamic controls.

Includes bibliograpical references (page 4).Air Force Contract No.Mode of access: Internet

Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock.

"May 1962."Includes bibliographical references (pages 174-177).Flight Control Laboratory Contract No.Mode of access: Internet

Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock. Part 2. Experimental pressure measurements at Mach 5 and 8 /

This report presents the results of an experimental hypersonic research program specifically designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. An analysis of the data is presented by comparison with the thin-shock-layer theory and the improved shock-expansion theory developed in the analytical program as well as with some of the simplified methods in current favor such as Newtonian, tangent-wedge, equivalent-cone, and shock-expansion methods. It is shown that in appropriate applications the thin-shock-layer theory is superior to any of these simplified methods. However, test conditions did not duplicate those necessary for complete evaluation of the improved shock-expansion theory. In certain instances the influence of viscous phenomena on the results is discussed, especially with regrad to the distinct wing-body combinations. A modified technique for taking vapor screen photographs developed in the course of these tests was found to be particularly helpful in this connection. The pressure tests on the sharp leading-edge wings, bodies, and wing-body combinations wer conducted at M~5 and 8 in tunnels A and B of the Von Karman Facility of the Arnold Engineering Development Center. The range of test variables were: angles of attack, -10 degress to 20 degrees; angles of yaw, -15 degrees to 15 degrees; Reynolds numbers, 0.83 to 6.0 x 10(superscript 6)/ft."Research supported by the United States Air Force, Air Force Systems Command, and performed by Grumman Aircraft Engineering Corporation.""May 1962."Includes bibliographical references (page 31).This report presents the results of an experimental hypersonic research program specifically designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. An analysis of the data is presented by comparison with the thin-shock-layer theory and the improved shock-expansion theory developed in the analytical program as well as with some of the simplified methods in current favor such as Newtonian, tangent-wedge, equivalent-cone, and shock-expansion methods. It is shown that in appropriate applications the thin-shock-layer theory is superior to any of these simplified methods. However, test conditions did not duplicate those necessary for complete evaluation of the improved shock-expansion theory. In certain instances the influence of viscous phenomena on the results is discussed, especially with regrad to the distinct wing-body combinations. A modified technique for taking vapor screen photographs developed in the course of these tests was found to be particularly helpful in this connection. The pressure tests on the sharp leading-edge wings, bodies, and wing-body combinations wer conducted at M~5 and 8 in tunnels A and B of the Von Karman Facility of the Arnold Engineering Development Center. The range of test variables were: angles of attack, -10 degress to 20 degrees; angles of yaw, -15 degrees to 15 degrees; Reynolds numbers, 0.83 to 6.0 x 10(superscript 6)/ft.Flight Control Laboratory Contract No.Mode of access: Internet