Experimental Laminar, Transitional, and Turbulent Boundary-layer Profiles on a Wedge at Local Mach Number 6.5 and Comparisons with Theory 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 Experimental Laminar, Transitional, and Turbulent Boundary-layer Profiles on a Wedge at Local Mach Number 6.5 and Comparisons with Theory PDF full book. Access full book title Experimental Laminar, Transitional, and Turbulent Boundary-layer Profiles on a Wedge at Local Mach Number 6.5 and Comparisons with Theory by Michael C. Fischer. Download full books in PDF and EPUB format.
Author: Michael C. Fischer
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 66
Get Book
Book Description
Wind tunnel investigation of laminar, transitional, and turbulent boundary layer profiles on wedge at hypersonic speed to confirm theoretical analysis.
Author: Michael C. Fischer
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 66
Get Book
Book Description
Wind tunnel investigation of laminar, transitional, and turbulent boundary layer profiles on wedge at hypersonic speed to confirm theoretical analysis.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 814
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 332
Get Book
Book Description
Author: S. J. Shamroth
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 76
Get Book
Book Description
An investigation was carried out to assess the accuracy of a transitional boundary layer theory in the low hypersonic Mach number regime. The theory is based upon the simultaneous numerical solution of the boundary layer partial differential equations for the mean motion and an integral form of the turbulence kinetic energy equation which controls the magnitude and development of the Reynolds stress. Comparisions with experimental data show the theory is capable of accurately predicting heat transfer and velocity profiles through the transitional regime and correctly predicts the effects of Mach number and wall cooling on transition Reynolds number. The procedure shows promise of predicting the initiation of transition for given free stream disturbance levels. The effects on transition predictions of the pressure dilitation term and of direct absorption of acoustic energy by the boundary layer were evaluated.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 814
Get Book
Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1408
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 282
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 626
Get Book
Book Description
Author: Robert L. Trimpi
Publisher:
ISBN:
Category : Attenuation (Physics)
Languages : en
Pages : 682
Get Book
Book Description
The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds nuniber of 2.5 million.
