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Active Flow-Control Concepts for Stall Alleviation and Post-Stall Lift…

Award Information

Department of Defense
Air Force
Award ID:
Program Year/Program:
1993 / SBIR
Agency Tracking Number:
Solicitation Year:
Solicitation Topic Code:
Solicitation Number:
Small Business Information
Vigyan Inc
VA Hampton, VA 23666-1325
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Woman-Owned: No
Minority-Owned: Yes
HUBZone-Owned: No
Phase 1
Fiscal Year: 1993
Title: Active Flow-Control Concepts for Stall Alleviation and Post-Stall Lift Improvement of Vortex Dominated Fighter Configuration
Agency / Branch: DOD / USAF
Contract: N/A
Award Amount: $60,099.00


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.

Principal Investigator:

Dhanvada M. Rao

Business Contact:

Small Business Information at Submission:

Vigyan, Inc.
30 Research Dr Hampton, VA 23666

Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No