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- W2341561254 abstract "Aerodynamic heating on the fin leading edges of a sounding rocket flying at hypersonic speed is evaluated. The fluid flow properties are obtained in an approximate fashion, whereas the convective heat flux is calculated from classical relationships provided in the literature to this type of problem. Since an ablative type of material is applied externally to the fins, a transient one-dimensional coupled conductive-change phase material problem results. The finite volume method is then used to solve the resulting equations and temperature distributions at the fin are obtained. For one of the simulations, it was possible to compare against experimental measurements, taken during the flight of VSB-30 sounding rocket. Considering the approximations used in the development of this work, as well as the uncertainties involved on the flight measurements, there was a fair agreement between the estimated values and the ones measured." @default.
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- W2341561254 date "2005-01-01" @default.
- W2341561254 modified "2023-09-27" @default.
- W2341561254 title "AERODYNAMIC HEATING ON VSB-30 SOUNDING ROCKET" @default.
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