A review of numerical and experimental study of rocket aerodynamic coefficients in ultrasonic conditions

There are various methods for calculating the aerodynamic coefficients of a rocket that are used at different stages of design. Today, three methods are used to do this: experimental, engineering and numerical. Experimental methods have required precise measuring instruments and massive installations. The basis of engineering methods is aerodynamic linear relations. The most important software in this field is the M.D engineering code, which is widely used in the design of missiles and rockets. However, this software can cause errors in some cases, such as high angle of attack. In recent decades, with the development of computers, the use of numerical methods to simulate fluid flow has become more important. In this research, the aerodynamic coefficients of a missile are calculated numerically and compared with the experimental method and the M.D. engineering code with attack angles from ۰ to ۲۰. The Navier-Stokes equations of the next stable receptor density were used to simulate. For numerical solution, the finite volume and density-based solver method with the correct formula and first-order accuracy were used. The turbulence model K-ε-RNG was used to match the experimental and numerical results.

Keywords:

Missle , Numerical analysis , aspect ratio , wind tunnel , M.D code