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.