Experimental Investigation of a Mach 3.5 Waverider Designed Using Computational Fluid Dynamics

Abstract

A computational-fluid-dynamics-based waverider design approach is discussed, which can allow arbitrary generating flowfields (for which no analytical solution exists) to be used in waverider design. To validate this design technique, a waverider with a lift-to-drag ratio of 2.62 was designed and optimized using a Mach 3.5 conical flowfield for a series of wind-tunnel experiments. A payload volume constraint was implemented such that an aerodynamically optimized design could be generated that met wind-tunnel installation and model manufacturability requirements. A variety of experiments at both on- and off-design conditions were performed using a blowdown supersonic wind tunnel. Measurements were obtained using a sting balance, pressure-sensitive paint (with an a priori temperature compensation approach), and schlieren and oil-flow visualization. For comparison with the experimental results, computational-fluid-dynamics simulations of the configuration were also performed; the design and aerodynamic coefficients were predicted by the computational fluid dynamics and design code to within 11% of the sting-balance measurements. Additionally, the schlieren and oil-flow visualization results showed the attached shock-wave characteristics and reproduction of the conical generating flowfield by the waverider at on-design conditions. Experiments at Mach 3 and 4 conditions indicated a change in of less than 3% for the waverider tested, and the design also demonstrated a positive for the full angle of attack range tested (from to 8 deg).