NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA
An axisymmetric implicit unsteady Euler equation solver has been applied to the transonic flow past sphere-ogive-cylinder bodies. This paper documents this method and shows results that were obtained for the full range of transonic Mach numbers, 0.7 or M at infinity or 1.2. The present numerical results are compared to the experiments of Hsieh for M at infinity 0.7, 0.95, 1.0, 1.05, 1.1 flow over hemisphere cylinders. A rather extensive parametric study of sphere-ogive-cylinders was performed over the transonic Mach number range. Nose pressure drag values were calculated and are presented for varying nose radii, 0. to 1.0, varying nose length, 1.0 to 10.0 and varying Mach numbers, 0.7 to 1.2, where all geometric quantities are normalized with respect to the maximum body radius. These results have been included in the NSWC Missile Aerodynamic Computer program to improve transonic nose drag estimates.