Author: Harold R. Mead
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock. Part III, Experimental measurements of forces at Mach 8 and pressures at Mach 21
Author: Harold R. Mead
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock
Author: Harold R. Mead
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 80
Book Description
This report presents the results of tests which are part of an experimental hypersonic research program designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. The data obtained include six-component force data at Mach 8 for seven configurations which were previously pressure tested at Mach 5 and 8 under the original program. The force tests were run in tunnel B of the Von Karman Facility of the Arnold Engineering Development Center. The ranges of test variables were: angle of attack, -10 degrees to 20 degrees; angle of yaw, -3 degrees to 15 degrees; Reynolds number per foot, 0.8 and 2.0 x 10(superscript 6). Data were also obtained at a nominal Mach number of 21 for three pressure instrumented configurations tested earilier at Mach 5 and 8 under the original program. The tests were run in tunnel HS-2 of the Von Karman Facility. Pitch data were measured over the angle of attack range -5 degrees to 20 degrees at a Reynolds number per foot of approximately 4X10(superscript 6). Some of the measured pressures are compared with thin-shock-layer thoery, Newtonian pressure formula, equivalent-cone and tangent-wedge approximations with the thin-shock-layer theory being generally superior in appropriate applications.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 80
Book Description
This report presents the results of tests which are part of an experimental hypersonic research program designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. The data obtained include six-component force data at Mach 8 for seven configurations which were previously pressure tested at Mach 5 and 8 under the original program. The force tests were run in tunnel B of the Von Karman Facility of the Arnold Engineering Development Center. The ranges of test variables were: angle of attack, -10 degrees to 20 degrees; angle of yaw, -3 degrees to 15 degrees; Reynolds number per foot, 0.8 and 2.0 x 10(superscript 6). Data were also obtained at a nominal Mach number of 21 for three pressure instrumented configurations tested earilier at Mach 5 and 8 under the original program. The tests were run in tunnel HS-2 of the Von Karman Facility. Pitch data were measured over the angle of attack range -5 degrees to 20 degrees at a Reynolds number per foot of approximately 4X10(superscript 6). Some of the measured pressures are compared with thin-shock-layer thoery, Newtonian pressure formula, equivalent-cone and tangent-wedge approximations with the thin-shock-layer theory being generally superior in appropriate applications.
Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock
Author: Harold R. Mead
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 190
Book Description
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 M̃5 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.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 190
Book Description
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 M̃5 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.
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 410
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 410
Book Description
U.S. Government Research Reports
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 2180
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 2180
Book Description
Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock
Author: Richard A. Scheuing
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 200
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 200
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1196
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1196
Book Description
Experimental Investigation of Pressures on a Blunt Two-dimensional Profile and on Sharp and Blunt Conical Shapes of Noncircular Cross Section at Mach 5 and 8
Author: Harold R. Mead
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 130
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 130
Book Description
Theoretical Prediction of Pressures in Hypersonic Flow: Configurations with Attached Leading Edge Shock
Author: Richard A. Scheuing
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Aeronautical Report
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 472
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 472
Book Description