Investigation Of The Variation Of Maximum Lift For A Pitching Airplane Model And Comparison With Flight Results
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| Author | : Paul W. Harper |
| Publisher | : |
| Total Pages | : 704 |
| Release | : 1948 |
| Genre | : Airplanes |
| ISBN | : |
Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, the maximum lift coefficient was determined as a function of the rate of change of angle of attack over a Mach number range from approximately 0.2 to 0.6 in wind-tunnel tests of a 1/20-scale model of a conventional single-engine fighter airplane and was conpared with existing flight data of this airplane. The wind-tunnel and flight results were found to be in good agreement.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 294 |
| Release | : 1948 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 460 |
| Release | : 1950 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 616 |
| Release | : 1949 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 1180 |
| Release | : 1957 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 808 |
| Release | : 1930 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : George E. Sweet |
| Publisher | : |
| Total Pages | : 64 |
| Release | : 1964 |
| Genre | : Rotors (Helicopters) |
| ISBN | : |
| Author | : Lipman Bers |
| Publisher | : |
| Total Pages | : 700 |
| Release | : 1950 |
| Genre | : Aerofoils |
| ISBN | : |
The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determing the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerical by an iteration method. A numerical example is given.
| Author | : |
| Publisher | : |
| Total Pages | : 664 |
| Release | : 1949 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 1196 |
| Release | : 1963 |
| Genre | : Mechanics, Applied |
| ISBN | : |
