Turbulent Boundary Layer Characteristics of Pointed Bodies of Revolution at Supersonic Speeds PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Turbulent Boundary Layer Characteristics of Pointed Bodies of Revolution at Supersonic Speeds PDF full book. Access full book title Turbulent Boundary Layer Characteristics of Pointed Bodies of Revolution at Supersonic Speeds by Jerry M. Allen. Download full books in PDF and EPUB format.
Author: Jerry M. Allen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
Get Book Here
Book Description
Author: Jerry M. Allen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
Get Book Here
Book Description
Author: Jerry M. Allen
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 114
Get Book Here
Book Description
Author: William A. Cassels
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
Get Book Here
Book Description
Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author: Charlie M. Jackson
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 74
Get Book Here
Book Description
Author: Robert L. McCoy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 82
Get Book Here
Book Description
A simplified flow field solution has been programmed in an attempt to improve the accuracy of estimates of the static aerodynamic characteristics of ordnance projectiles. It provides estimates of drag, normal force, static moment, and roll damping moment for pointed bodies of revolution at supersonic speed. The program combines the Van Dyke hybrid theory for potential flow, the Van Driest compressible turbulent boundary layer theory, and the Chapman-Sternberg model for supersonic base pressure. Good agreement is demonstrated between the theoretical and experimental data.
Author: William A. Cassels
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 478
Get Book Here
Book Description
Author: William R. Wimbrow
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Get Book Here
Book Description
Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.
Author: D. K. Patel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
Get Book Here
Book Description
Author: Charlie M. Jackson
Publisher:
ISBN:
Category :
Languages : en
Pages : 65
Get Book Here
Book Description
