A Comparison of Experimental and Theoretical Results for the Compressible Turbulent-boundary-layer Skin Friction with Zero Pressure Gradient
Title | A Comparison of Experimental and Theoretical Results for the Compressible Turbulent-boundary-layer Skin Friction with Zero Pressure Gradient PDF eBook |
Author | John B. Peterson |
Publisher | |
Pages | 60 |
Release | 1963 |
Genre | Skin friction (Aerodynamics) |
ISBN |
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NASA Technical Note
Title | NASA Technical Note PDF eBook |
Author | |
Publisher | |
Pages | 434 |
Release | 1974 |
Genre | |
ISBN |
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NASA Technical Paper
Title | NASA Technical Paper PDF eBook |
Author | United States. National Aeronautics and Space Administration |
Publisher | |
Pages | 814 |
Release | 1978 |
Genre | Aeronautics |
ISBN |
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Development of a Low-aspect Ratio Fin for Flight Research Experiments
Title | Development of a Low-aspect Ratio Fin for Flight Research Experiments PDF eBook |
Author | David M. Richwine |
Publisher | |
Pages | 20 |
Release | 1994 |
Genre | Flow visualization |
ISBN |
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Heat-transfer Measurements at Mach 8 on a Flat Plate with Deflected Trailing-edge Flap with Effects of Transition Included
Title | Heat-transfer Measurements at Mach 8 on a Flat Plate with Deflected Trailing-edge Flap with Effects of Transition Included PDF eBook |
Author | Charles Borden Johnson |
Publisher | |
Pages | 60 |
Release | 1970 |
Genre | Heat |
ISBN |
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NASA Technical Paper
Title | NASA Technical Paper PDF eBook |
Author | |
Publisher | |
Pages | 56 |
Release | 1980 |
Genre | Science |
ISBN |
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The Characteristics of a Laminar Boundary Layer on a Spinning Tangent Ogive Cylinder at Angle of Attack
Title | The Characteristics of a Laminar Boundary Layer on a Spinning Tangent Ogive Cylinder at Angle of Attack PDF eBook |
Author | H. R. Vaughn |
Publisher | |
Pages | 56 |
Release | 1972 |
Genre | Angle of attack (Aerodynamics) |
ISBN |
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Streamwise velocity profiles of a laminar boundary layer were determined from pitot pressure measurements made in a supersonic wind tunnel on a spinning tangent ogive cylinder at zero and four degrees angle of attack. A transformation was found which transforms the velocity profiles to be in agreement with the incompressible Blasius profile.