Experimental Investigation Of The Effect Of Boundary Layer Transition On The Average Heat Transfer To A Yawed Cylinder In Supersonic Flow
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Proceedings of the NASA-University Conference on the Science and Technology of Space Exploration
| Author | : |
| Publisher | : |
| Total Pages | : 544 |
| Release | : 1962 |
| Genre | : Outer space |
| ISBN | : |
A Chinese boy's greatest wish is to be an artist but he is too poor to buy a good brush until a wizard appears and gives him one with magic powers.
An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow
| Author | : Mitchel H. Bertram |
| Publisher | : |
| Total Pages | : 134 |
| Release | : 1963 |
| Genre | : Airplanes |
| ISBN | : |
Proceedings of the NASA-University Conference on the Science and Technology of Space Exploration, Chicago, Illinois, November 1-3, 1962
| Author | : United States. National Aeronautics and Space Administration |
| Publisher | : |
| Total Pages | : 992 |
| Release | : 1962 |
| Genre | : Outer space |
| ISBN | : |
Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds
| Author | : Gary T. Chapman |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1961 |
| Genre | : Fluid mechanics |
| ISBN | : |
NASA Technical Report
| Author | : United States. National Aeronautics and Space Administration |
| Publisher | : |
| Total Pages | : 930 |
| Release | : 1963 |
| Genre | : Aerodynamics |
| ISBN | : |
An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow
| Author | : Robert W. Higgins |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1951 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.
