Affiliation:
1. Council of Scientific and Industrial Research (CSIR), National Aerospace Laboratories, Experimental Aerodynamics Division (EAD), Bangalore 560 017, India
Abstract
An experimental investigation is conducted to improve the control effectiveness of an array of vane-type vortex generators (VG) implemented 6 [Formula: see text] upstream of an incident shock-induced separation generated using a 14-deg wedge in a Mach 2.05 flow. Initially, the effect of an array of rectangular vanes (RRV) is studied by varying the vane 1) chord to height [Formula: see text], 4.2, 2) angle [Formula: see text], 20, 18, and 16 deg, 3) height to boundary-layer thickness [Formula: see text], 0.5, 0.3, and 0.2, and 4) interdevice spacing to height [Formula: see text], 9.5, 7.5, 6.5, 5.7, 5.5, and 5.0. Similar tests were also performed for ramp vanes (RV) with [Formula: see text]. Due to inherent design differences, an RRV device generates a larger region of vortex influence relative to an RV device. Therefore, reducing [Formula: see text] significantly reduces the extent of uncontrolled separation regions between neighboring VGs that improves their separation control capability. The best performing RRV devices with vane height [Formula: see text], [Formula: see text], and [Formula: see text] show maximum reduction in separation extent of nearly 80, 74, and 70%, respectively, relative to no control. The equivalent RV devices, however, show much reduced control effectiveness. All controls exhibit a shift in the dominant separation frequency to higher values, indicating a reduction in the overall extent of separation.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)