Aerodynamic prediction of sounding rocket using semi-empirical method

MS. Le Vu Dan Thanh; Dr. Nguyen Anh Tuan; MS. Nguyen Van Thang
Military Technical Academy

Drag coefficient with variation of Mach number: a) before stage separation; b) after stage separation

The prediction of the aerodynamic coefficients of flying vehicles such as sounding rockets plays an important role in their design and development procedures, espescially in early stages. In practice, the aerodynamic coefficients can be estimated using experimental measurements, numerical simulations, or semi-empirical engineering tools. In the present paper, a semi-empirical method was used for the aerodynamic estimation of a sounding rocket with the supersonic flight conditions up to 3.5 Mach. The lift, drag and pitching moment coefficients, as well as the position of pressure center for several rocket configurations are presented.

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