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| Author | : Malcom Green |
| Publisher | : |
| Total Pages | : 78 |
| Release | : 1951 |
| Genre | : |
| ISBN | : |
| Author | : Gary L. Barr |
| Publisher | : |
| Total Pages | : 118 |
| Release | : 1972 |
| Genre | : Rockets (Aeronautics) |
| ISBN | : |
| Author | : Joseph Francis Madden (Jr.) |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1941 |
| Genre | : |
| ISBN | : |
| Author | : E. V. Laitone |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1950 |
| Genre | : Ultrasonic waves |
| ISBN | : |
| Author | : Edward Malcolm Harvey Newton |
| Publisher | : |
| Total Pages | : 100 |
| Release | : 1964 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : Robert Earl Wilson |
| Publisher | : |
| Total Pages | : 110 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
| Author | : William C. Ragsdale |
| Publisher | : |
| Total Pages | : 160 |
| Release | : 1972 |
| Genre | : Laminar boundary layer |
| ISBN | : |
Pitot pressure surveys were made of the laminar boundary layer on an ogive-cylinder model at Mach 3.02 and 4.10. Surveys were made at five stations along the model, at angles of attack of zero and four degrees, with and without spin. Tests with spin were performed at Mach 3.02. The pitot pressure data has been used to compute boundary-layer velocity profiles, and results from two data-reduction procedures are presented. Some comparisons are made with theoretical velocity profiles for the zero spin, zero angle-of-attack case. (Author).
| Author | : Frederic Alan Gruenich |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1962 |
| Genre | : Heat |
| ISBN | : |
| Author | : W. E. Moeckel |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1950 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.
| Author | : H. Ronald Miller |
| Publisher | : |
| Total Pages | : 144 |
| Release | : 1962 |
| Genre | : |
| ISBN | : |
