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

Solicitation Topic Code: N/A

Solicitation Number: N/A

Timeline

Solicitation Year: N/A

Award Year: 1987

Award Start Date (Proposal Award Date): N/A

Award End Date (Contract End Date): N/A

Small Business Information

Flow Research Inc

21414 68th Ave S

Kent, WA 98032

United States

DUNS: N/A

HUBZone Owned: No

Woman Owned: No

Socially and Economically Disadvantaged: No

Principal Investigator

Name: Dr Suresh Menon
Phone: (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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NUMERICAL MODELING OF NOSETIP GASJET AT HYPERSONIC SPEED