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Novel Fluidic Flow Control of Scramjet Isolators

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-22-C-0665
Agency Tracking Number: N211-081-1506
Amount: $999,847.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: N211-081
Solicitation Number: 21.1
Solicitation Year: 2021
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-09-28
Award End Date (Contract End Date): 2024-03-29
Small Business Information
61 Keyland Ct.
Bohemia, NY 11716-2654
United States
DUNS: 078466424
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Robert Bakos
 (631) 793-8439
Business Contact
 Robert Bakos
Phone: (631) 793-8439
Research Institution

As hypersonic propulsion technology moves from the laboratory to flight demonstrators and on to operational systems, improved overall engine performance and operability become more critical. Numerous factors challenge engine designers, however, the inlet/isolator compression system that couples to the hypersonic ramjet/scramjet combustor is one of the most vexing. Packaging, acceleration, range, maneuverability, survivability, are all first order design drivers. These flow down to requirements for the inlet/isolator to achieve high engine back pressure, deliver minimum flow distortion at the engine aerodynamic inlet plane, and avoid unstart over an accelerating and maneuvering flight profile. To achieve these objectives, Innoveering has identified a fluidic system for inlet/isolator integration that can deliver the needed improvements. The proposed Phase II activity will further mature this concept using combined CFD and optimization and prepare for experimental assessment, optimization, and verification.

* Information listed above is at the time of submission. *

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