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 L / D 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 L / D 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 L / D of less than 3% for the waverider tested, and the design also demonstrated a positive L / D for the full angle of attack range tested (from 8 to 8 deg).


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    Title :

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


    Contributors:

    Published in:

    AIAA Journal ; 53 , 6 ; 1590-1601


    Publication date :

    2015-06-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English