An Experimental Investigation of Recovery Factors and Heat-transfer Coefficients for Supersonic Air Flow Over Flat Plates
Author: Robert Howard Shoulberg
Publisher:
Published: 1953
Total Pages: 276
ISBN-13:
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Experimental Investigation of Recovery Factors for Air Flowing Over a Flat Plate at Supersonic Velocities
Author: Miguel A. Rivas
Publisher:
Published: 1952
Total Pages: 70
ISBN-13:
DOWNLOAD EBOOKExperimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds
Author: William R. Wimbrow
Publisher:
Published: 1949
Total Pages: 26
ISBN-13:
DOWNLOAD EBOOKLocal 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.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Published: 1956
Total Pages: 1120
ISBN-13:
DOWNLOAD EBOOKWADC Technical Report
Author: United States. Wright Air Development Division
Publisher:
Published: 1954
Total Pages: 844
ISBN-13:
DOWNLOAD EBOOKIndex of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Published: 1959
Total Pages: 388
ISBN-13:
DOWNLOAD EBOOKSubject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)
Publisher:
Published: 1960
Total Pages: 894
ISBN-13:
DOWNLOAD EBOOKExperimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-angle Settings
Author: John E. Baker
Publisher:
Published: 1949
Total Pages: 686
ISBN-13:
DOWNLOAD EBOOKThe highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment and the flutter speed increased considerably in this region with decreasing pressure. Over the rest of the pitch range, the flutter speeds were much lower and varied little with pressure.
