A method is developed which accurately predicts for blunt-based bodies of revolution the normal force coefficient and the pitching moment coefficient for angles of attack far beyond the range of potential theory. It is based on the principle of superposition of the results of potential theory and the viscous force on a cylindrical body due to the transverse component of flow. In contrast to previously used methods, the viscous cross force is assumed not to be in a steady state, but in a transient development along the body. The method is compared with experimental data for both subsonic and supersonic flows and with both laminar and turbulent axial boundary layers. The method is also useful for extrapolation of small-yaw data to large yaws and to different Reynolds numbers. The results presented have been applied only in the range M = 0 to M = 2.87 and for a limited range of Reynolds numbers.

A method initially proposed by Bryson is extended to include asymmetric shedding. This method employs the impulsive flow analogy, and models each wake vortex using a single-point vortex. Free parameters inherent in the problem formulation are determined empirically. Normal force, pitching moment and yawing force coefficients are predicted for slender bodies with a nose fineness ratio greater than four and at a Mach number less than 0.9. (Modified author abstract).

Linear regression techniques are used to establish a quantitative description of side forces on bodies at high incidence. A data base is assembled concerning the key side force characteristics of maximum observed side force, angle of occurrence, and minimum angle of attack at which a side force is observed. This information is examined to determine the important trends and a predictive model for side force based on the crossflow analogy is developed to suggest other important variables. A linear regression model for these quantities is developed to include only those variables which are statistically significant. Results indicate that peak side force coefficients are a function of Mach number and only weakly of Reynolds number. Nose fineness is the critical model dimension which suggests that peak side force is a product of the nose flow field. The angle at which peak side forces occur is found to be dependent on model length and Mach number, while the onset angle of attack is a function of model length only.