Investigation of spike length on wave drag reduction of standard model in hypersonic flow

The Blunt body in the Hypersonic flow creates drastic aerodynamic drag and heating. One of the most effective methods of reducing aerodynamic drag and heating is using of aerodisk in the front of the nose. This study examines the aerodisk method as an Right tool in reducing the HB1 nose drag in the Hypersonic flow regime. The results are obtained from experimental test of hypersonic wind tunnel and numerical simulation in mach 6.44. In this study the effect of aerodisk length on drag reduction of standard model was evaluated. For this purpose, four aerodisks with a length to diameter ratio of 0.5, 1, 1.5 and 2 were used. Numerical and experimental results had a significant adaptation and it was observed that aerodisk have a significant effect on the nose hypersonic drag reduction and increase its length, can provide more drag reduction. According to the results, aerodisk with length to diameter ratio of 2, showed the best performance with 43% drag rduction.