NUMERICAL MODELING OF NOSETIP GASJET AT HYPERSONIC SPEED

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: N/A
Agency Tracking Number: 3915
Amount: $197,000.00
Phase: Phase II
Program: SBIR
Awards Year: 1987
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Flow Research Co
21414 68th Ave S, Kent, WA, 98032
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Dr Suresh Menon
 (206) 872-8500
Business Contact
Phone: () -
Research Institution
N/A
Abstract
THE JET INJECTION AT THE TIP OF AN AXISYMMETRIC NOSE CONE IN HYPERSONIC FLOW WILL BE STUDIED BY AN EFFICIENT AND ACCURATE NUMERICAL SCHEME. THE PROPOSED RESEARCH WILL INVESTIGATE AND DEVELOP THE NUMERICAL SCHEME FOR THE FULL NAVIER-STOKES EQUATION USING A TOTAL VARIATION DIMINISHING (TVD) TYPE OF ADAPTIVE DISSIPATION TO RESOLVE THE STRONG SHOCK ACCURATELY WITHOUT GENERATING SPURIOUS OSCILLATIONS. THE NOSE JET INJECTION BOUNDARY CONDITIONS WILL BE STUDIED IN DETAIL AND WILL BE FORMULATED IN TERMS OF PHYSICAL CONTROLLABLE PARAMETERS. TEST CASES AT VARIOUS MACH NUMBERS IN THE HYPERSONIC REGIME WILL BE COMPUTED TO EVALUATE THE ADAPTIVE DISSIPATION NUMERICAL SCHEME AND THE NOSE JET INJECTION CONDITIONS. THE EFFECT OF JET INJECTION ON THE HEAT TRANSFER RATE TO THE SURFACE WILL ALSO BE DETERMINED.

* information listed above is at the time of submission.

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