Accession Number : ADA073217


Title :   Predictions of Aerodynamic Heating on Tactical Missile Domes


Descriptive Note : Technical rept.


Corporate Author : NAVAL SURFACE WEAPONS CENTER WHITE OAK LAB SILVER SPRING MD


Personal Author(s) : Zien, T F ; Ragsdale, W C


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a073217.pdf


Report Date : 25 Apr 1979


Pagination or Media Count : 75


Abstract : 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.


Descriptors :   *AERODYNAMIC HEATING , *GUIDED MISSILE DOMES , HEAT TRANSFER , MATHEMATICAL MODELS , ABLATION , FINITE DIFFERENCE THEORY , BOUNDARY LAYER FLOW , PRESSURE DISTRIBUTION , APPROXIMATION(MATHEMATICS) , BOUNDARY LAYER TRANSITION , CONDUCTION(HEAT TRANSFER)


Subject Categories : Guided Missiles
      Fluid Mechanics
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE