Flow Control for Vehicle Populsion/Weapons Integration

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$0.00
Award Year:
2001
Program:
SBIR
Phase:
Phase I
Contract:
F33615-01-C-3118
Award Id:
55326
Agency Tracking Number:
001VA-1824
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
174 North Main Street, P.O. Box 1150, Dublin, PA, 18917
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator:
NeerajSinha
Vice President & Technica
(215) 249-9780
sinha@craft-tech.com
Business Contact:
NeerajSinha
Vice President & Technica
(215) 249-9780
sinha@craft-tech.com
Research Institute:
n/a
Abstract
An internal aircraft weapons bay, when exposed to freestream flow, experiences an intense aeroacoustic environment and varied suppression concepts have been tested for attenuating flow-induced oscillations. Recent tests with open-loop, high-frequencyexcitation have shown great promise in providing broadband attenuation and elimination of tones. High frequency actuation apparently alters the dynamics of the turbulent energy cascade and accelerates the transfer of energy from low frequency, large scaleeddies to high frequency, small-scale eddies, where it finally gets dissipated as heat. The proposed program is focused on using a Hartmann-Sprenger resonance tube as a high frequency actuator for cavity acoustic attenuation. Large Eddy Simulation (LES)will be complemented by Phase-averaged Schlieren and by Particle Image Velocimetry (PIV) measurements in miniature and sub-scale cavities. These diagnostics will provide insight into turbulence-acoustic interactions. Testing at varied scales will providevalidation of scaling laws for high frequency actuation physics. CFD simulations will provide guidance for the design of the high frequency actuator. These investigations will provide the foundation for designing a prototype High Frequency AcousticSuppression (HFAS) system for eventual flight-testing on a RAAF F-111. The HFAS prototype will be based on a modification of the full-scale Active Separation Control (ASC) flight demonstration model.

* information listed above is at the time of submission.

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