The Real Gas Effects Of Aerodynamic Heating In Hypersonic Flows

Research was made to investigate the high temperature chemical non-equilibrium effects andrarefaction effects on aerodynamic heating. Knudsen number was introduced in to classify the wholeflow area into four parts，which is called continuous flow, slip flow, transition flow and free molecularflow.For rarefied flow, including transition flow and free molecular flow, engineering method wasdrawn in to analyze the aerodynamic heating for each flow area separately. Combined with thesolution of heat transfer in material, heat-flux distribution and temperature distribution of blunt-conebody was calculated in rarefied conditions. Comparison and analysis was then made with the resultsof DSMC method.For continuous flows, inviscid outflow solution and engineering method was combined togetherto investigate the high temperature non-equilibrium effects on high speed aircraft heating. A9-speciesmodel was used as the chemical reaction model. This method not only has a greater efficiency but alsohas a good adaptability to complex aircraft models. The most important is this method can meet theengineering accuracy requirements. Heat-flux distribution and temperature was calculated, andcompared with equilibrium conditions finally.The comparison and analysis of the results show that, the calculating method for rarefied flowand the solution for high temperature non-equilibrium effects of aerodynamic heating is in highaccuracy and efficiency.