Predictions of Aerodynamic Heating on Tactical Missile Domes
NAVAL SURFACE WEAPONS CENTER WHITE OAK LAB SILVER SPRING MD
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The laminar heating on the hemisphere-cylinder configuration has been calculated using various predictive techniques in the Mach number range of one to five. The accuracy of these approximate results is assessed using the Cebeci-Smith finite difference code as a standard. A new procedure is suggested which is based on the consistent use of the Kays semi-empirical formulas, and it appears to offer very accurate predictions of aerodynamic heating on the configuration under study. A similar comparison on the turbulent heating predictions is also briefly discussed. In the transition region, a new approach of aerodynamic heating calculation based on the so-called spot theory is introduced, and some results are presented and discussed. Transient heat conduction inside the missile structure is studied using a new integral technique.
- Guided Missiles
- Fluid Mechanics