Active Flow-Control Concepts for Stall Alleviation and Post-Stall Lift Improvement of Vortex Dominated Fighter Configuration

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: N/A
Agency Tracking Number: 20160
Amount: $60,099.00
Phase: Phase I
Program: SBIR
Awards Year: 1993
Solitcitation Year: N/A
Solitcitation Topic Code: N/A
Solitcitation Number: N/A
Small Business Information
Vigyan, Inc.
30 Research Dr, Hampton, VA, 23666
Duns: N/A
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Dhanvada M. Rao
 (804) 865-1400
Business Contact
Phone: () -
Research Institution
N/A
Abstract
It is proposed to experimentally explore two active separation-control concepts aimed at stall alleviation and maximum-lift improvement on generic, vortex-dominated fighter configurations. The concepts comprise a delta wing incorporating transversely-hinged apex flaps oscillating in the pitch plane, and a LEX-trapezoidal wing combination with root-hinged LEX's oscillating in the cross-plane. The common purpose of the active devices is to establish a hysteresis loop with average lift higher than the undisturbed wing lift at the same angle of attack. Even if the wing flow-field moves in and out of stall, it is anticipated that the time-averaged lift will be considerably improved. Low-speed wind tunnel tests will be conducted on two wing-body models in a wide range of angle of attack and with varying control surface frequency and amplitude parameters, measuring time-averaged six-component aerodynamic coefficients, wing surface pressures and near-wake velocity components, to determine the feasibility of the active devices and quantify their effectiveness. The potential of non-symmetrical activation of the devices for lateral control near stall will also be explored.

* information listed above is at the time of submission.

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