Aerodynamic engineering prediction methods for winged reentry vehicles

Focused on the calculation inaccuracy of existing engineering prediction methods for winged reentry vehicles, a modified component partition strategy and pressure method selection rationale were developed. Through comparison of the experimental data and the engineering prediction on longitude aerodynamic characteristics of space shuttle orbiter and a X-34 like vehicle, it is shown that the prediction method can meet the accuracy requirements at Mach 3.0 or higher. The maximum relatively error is less than 10% for lift coefficients and drag coefficients. Compared with the existing methods, the proposed strategy and rationale improves the prediction accuracy in pitching moment coefficient, with the same accuracy in lift and drag characteristics. Besides, the predictive pressure distribution is in agreement with the numerical results.