Heating Estimated on Hypersonic Blunt Cones

Hypersonic flight is one of the most important transportations in the future and it refers to the flight with speeds higher than Mach5 through the atmosphere below around 90 km. However, when the speed of the flight reaches Mach number 5, the aerodynamic frication can make a mass of heat on the hypersonic flight, and that heat is even big enough to melt steel. Therefore the testing and simulation for the properties of microstructure is necessary to be done for designing hypersonic flight. The main purpose for this thesis is to estimate the heating on a hypersonic blunt cones and do the calculation for the heating on blunt cones and the answer will be compared to the experimental data. Based on many countries’ research on hypersonic area, a lot of methods for calculating the heating on the hypersonic flight were exist. Hence, this thesis starts from determining the method and equations that can be used for the further calculations. It includes equations for calculating the heat flux for different parts (stagnation point, sphere body, cylinder body and so on) on the hypersonic flight, the equations for calculating the properties across a normal shock and the equations for the pressure distribution on the hypersonic flight surface. Then, based on all the equations summarized in the first step, one computer program was made and it can be used for estimating the heating on the blunt cones. After putting the input data into the computer program, the values for different factors can be found. Then based on the computer program’s result, few graphs was made and NASA’s experimental data was used to test the accuracy for the computer program. In conclusion, this thesis summaries a reliable, simple method of estimating the aerodynamic heat for the hypersonic flight and the computer program that III developed in this thesis could be applied for designing or testing hypersonic flight