Fluidic Nozzle to Improve Transonic Performance of Hypersonic Vehicle

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-04-M-2422
Agency Tracking Number: F041-188-0195
Amount: $99,988.00
Phase: Phase I
Program: SBIR
Awards Year: 2004
Solicitation Year: 2004
Solicitation Topic Code: AF04-188
Solicitation Number: 2004.1
Small Business Information
SPIRITECH ADVANCED PRODUCTS, INC.
880 Jupiter Park Drive, Suite 8, Jupiter, FL, 33458
DUNS: 017391348
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Eric Gamble
 Principal Investigator
 (561) 741-3441
 egamble@spiritech.cc
Business Contact
 Rich DeFrancesco
Title: President
Phone: (561) 741-3441
Email: defran@spiritech.cc
Research Institution
N/A
Abstract
Use of fluidic injection of high-pressure air is proposed to improve a hypersonic vehicle's installed nozzle performance and eliminate undesirable pitching moments at off-design, transonic flight conditions. Hypersonic flight vehicles are typically designed with a high expansion ratio Single Expansion Ramp Nozzle (SERN) for a design point at high Mach number flight conditions. However, at low Mach number (transonic) flight, the nozzle is over-expanded, resulting in low, sub-ambient pressures acting on the expansion ramp surface. These sub-ambient pressures cause increased drag, reduced performance, and large pitching moments. The loss in net thrust-minus-drag performance may be as high as 25% throughout much of the transonic flight regime. The corresponding pitching moment is large and must be overcome by increasing the size of the vehicle's control surfaces. The proposed fluidic injection concept eliminates these problems and improves the overall vehicle performance by injecting high-pressure air into the nozzle to induce a flow separation, thereby increasing the pressure on the SERN ramp. The objective of this Phase I program is to demonstrate the feasibility of fluidic injection to improve off-design performance of hypersonic aircraft at transonic speeds, culminating in the preliminary design of an experimental rig to be used for Phase II testing.

* information listed above is at the time of submission.

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