Aero-optic effect is investigated in supersonic/hypersonic flow. Flat plate, ramp and cave model in supersonic/hypersonic flow condition are studied with large eddy simulation (LES). Turbulent density pulse is predicted to verify coefficient of density pulse model-mixing length (ML) model. It indicates that LES method simulates turbulent density pulse well in flat plate boundary layer flow, oblique shock wave/boundary layer interaction and strong separation flow. Density pulse data obtained by LES is used to verify ML coefficient and set a quantitative result. The modified ML was used to predict aero-optical effect on missile successfully.

Heat transfer distribution is analyzed on a rough wall in high speed turbulent compressible flow via computational fluid dynamics(CFD) method and analytical correlations, focusing on heat transfer with different roughness number and roughness element shape. It shows that, in all cases, heat flux augmentation predicted with CFD increases with reduction of roughness element density and levels off after roughness shape density is small, which differs with data of three analytical correlations. Predicted heat fluxes are same if same roughness element density and equivalent height are imposed on analytical correlations distinguishing from tendency of CFD results, which changes with roughness element shapes.

A three-dimensional computational fluid dynamics algorithm is developed to study chemical nonequilibrium flowfield in a standard model, ELECTRE, for which flight data exits. A finite rate chemistry model based on Dunn and Kang's model is implemented. An extensive investigation on catalysis modeling relevance simulations with non-catalytic wall conditions as well as with full catalytic boundary conditions is made. The method developed is used to compute detailed flow features of hypersonic flow around forebody of a sphere-cone vehicle under different attack angles and altitudes. It is shown that reacting gas numerical results are consistent with flight data. It shows that real gas effects are prominent in thin shock wave layers closing to the wall surface. It makes outstanding distance of shock wave short. Heat flux under full catalytic wall boundary condition is higher than that under non-catalytic condition. The greater the attack angle,the more obvious this variance and the less electron number density on the wall. The higher the flight altitude,the lower dissociation of oxygen and nitrogen,and the lower heat flux on stagnation point.

In hypersonic/supersonic flow conditions, numerical simulations, experience relations and experiment analysis are made to study thermal-environment distribution characteristic around local-parts imposed by protuberance interacting body. Comparing flow characteristic structures in different shape, height, breadth ere, we found that interaction-zone size induced by high protuberance depend sensitively on effective breadth and short protuberance interaction-zone size depend on protuberance height. On the other hand, interaction-zone size is imposed by shade of lead edge, whether laminar or turbulence. Square-lead-surface and arc lead surface separation length ratio is 1.414. Sweepback affects separation length. A correlative line is built for size of separation imposed by sweepback.