Author: Lelan Ray Jamison
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 156
Book Description
Experimental Measurements of the Drag on Spheres in a Low Density, Low Supersonic Flow
Author: Lelan Ray Jamison
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 156
Book Description
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 156
Book Description
Sphere Drag in a Low Density Supersonic Flow
Author: Jerome Aroesty
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 318
Book Description
Sphere drag coefficients were measured in the Berkeley Low Density Wind Tunnel at Mach equals 2, 4, and 6, and free stream Reynolds numbers between 10 and 10,000 for both insulated and cold wall conditions. The measurements indicate that sphere drag in this regime is strongly dependent on the Reynolds number behind a normal shock wave, and only weakly dependent on Mach number. In addition, it was found that a decrease in wall temperature/stagnation temperature (T sub w/T sub o) from 1 to 0.26 was accompanied by a 5 - 10% decrease in the drag coefficient. A precision microbalance was used to obtain data for insulated spheres, and a moving model technique was used to obtain data for small spheres falling freely through a wind tunnel jet. These latter tests were performed using both cold and insulated models. The results on insulated spheres at M equal 2 and 4 were in good agreement with the measurements of other investigators. The results of the cold wall tests indicate that for Mach numbers greater than 5 in air, sphere drag coefficients are a function only of T sub w/T sub o and the post normal shock Reynolds number. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 318
Book Description
Sphere drag coefficients were measured in the Berkeley Low Density Wind Tunnel at Mach equals 2, 4, and 6, and free stream Reynolds numbers between 10 and 10,000 for both insulated and cold wall conditions. The measurements indicate that sphere drag in this regime is strongly dependent on the Reynolds number behind a normal shock wave, and only weakly dependent on Mach number. In addition, it was found that a decrease in wall temperature/stagnation temperature (T sub w/T sub o) from 1 to 0.26 was accompanied by a 5 - 10% decrease in the drag coefficient. A precision microbalance was used to obtain data for insulated spheres, and a moving model technique was used to obtain data for small spheres falling freely through a wind tunnel jet. These latter tests were performed using both cold and insulated models. The results on insulated spheres at M equal 2 and 4 were in good agreement with the measurements of other investigators. The results of the cold wall tests indicate that for Mach numbers greater than 5 in air, sphere drag coefficients are a function only of T sub w/T sub o and the post normal shock Reynolds number. (Author).
Low-Density Supersonic Sphere Drag with Variable Wall Temperature
Author: D. L. Whitfield
Publisher:
ISBN:
Category :
Languages : en
Pages : 47
Book Description
Force measurements were made to investigate the effect of wall temperature on sphere drag in low-density supersonic flow. Drag data were obtained by fixing flow conditions and changing only the sphere wall temperature. A means of correlating drag data in transition flow is suggested, and its validity is assessed by applying the correlation parameter to this and several other sets of experimental data. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 47
Book Description
Force measurements were made to investigate the effect of wall temperature on sphere drag in low-density supersonic flow. Drag data were obtained by fixing flow conditions and changing only the sphere wall temperature. A means of correlating drag data in transition flow is suggested, and its validity is assessed by applying the correlation parameter to this and several other sets of experimental data. (Author).
Some Sphere Drag Measurements in Low Density Shock Tunnel Flows
Author: R. E. Geiger
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 0
Book Description
The free flight technique was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indcates that : a) The free flight technique is useful for shock tunnel measurements of aerodynamic forces in non-continuum flows. b) There is little to choose from between Kn[subscript infinity], Re[subscript infinity], Re2 as a correlating variable for experimental sphere drag coefficients. (c) The parameter C [subscript D] - C [subscript Di] over C [subscript Dfm] - C [subscriptDi] yields a useful correlatin of sphere drag over a wide range of Mach numbers, Reynolds number and wall temperatures.
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 0
Book Description
The free flight technique was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indcates that : a) The free flight technique is useful for shock tunnel measurements of aerodynamic forces in non-continuum flows. b) There is little to choose from between Kn[subscript infinity], Re[subscript infinity], Re2 as a correlating variable for experimental sphere drag coefficients. (c) The parameter C [subscript D] - C [subscript Di] over C [subscript Dfm] - C [subscriptDi] yields a useful correlatin of sphere drag over a wide range of Mach numbers, Reynolds number and wall temperatures.
Measurement of Drag Forces in Low Density Flows
Author: J. J. Smolderen
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 30
Book Description
A new technique to accurately measure low level forces and its application to the determination of drag coefficients in rarefied hypersonic flow are described. Preliminary results are presented for cylinders and spheres at M = 8 in the transitional and near-free-molecule flow regimes. (Author).
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 30
Book Description
A new technique to accurately measure low level forces and its application to the determination of drag coefficients in rarefied hypersonic flow are described. Preliminary results are presented for cylinders and spheres at M = 8 in the transitional and near-free-molecule flow regimes. (Author).
Upper Atmosphere Density Obtained from Falling Sphere Drag Measurements
Author: G. A. Faucher
Publisher:
ISBN:
Category : Atmosphere, Upper
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Atmosphere, Upper
Languages : en
Pages : 44
Book Description
Some Sphere Drag Measurements in Low Density Shock Tunnel Flows
Author: R. E. Geiger
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 14
Book Description
The free flight technique was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indcates that : a) The free flight technique is useful for shock tunnel measurements of aerodynamic forces in non-continuum flows. b) There is little to choose from between Kn[subscript infinity], Re[subscript infinity], Re2 as a correlating variable for experimental sphere drag coefficients. (c) The parameter C [subscript D] - C [subscript Di] over C [subscript Dfm] - C [subscriptDi] yields a useful correlatin of sphere drag over a wide range of Mach numbers, Reynolds number and wall temperatures.
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 14
Book Description
The free flight technique was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indcates that : a) The free flight technique is useful for shock tunnel measurements of aerodynamic forces in non-continuum flows. b) There is little to choose from between Kn[subscript infinity], Re[subscript infinity], Re2 as a correlating variable for experimental sphere drag coefficients. (c) The parameter C [subscript D] - C [subscript Di] over C [subscript Dfm] - C [subscriptDi] yields a useful correlatin of sphere drag over a wide range of Mach numbers, Reynolds number and wall temperatures.
Experimental Determination of the Effect of Horizontal-tail Size, Tail Length, and Vertical Location on Low-speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45 ̊sweptback Wing and Tail Surfaces
Author: Arthur Earl Bryson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 340
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 340
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Proceedings of the International Symposium on Two-Phase Systems
Author: G. Hetsroni
Publisher: Elsevier
ISBN: 1483160505
Category : Science
Languages : en
Pages : 779
Book Description
Proceedings of the International Symposium on Two-Phase Systems
Publisher: Elsevier
ISBN: 1483160505
Category : Science
Languages : en
Pages : 779
Book Description
Proceedings of the International Symposium on Two-Phase Systems