NONINTRUSIVE METHOD FOR DETERMINING PLASMA PROFILES IN HYPERSONIC BOUNDARY LAYERS

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$49,833.00
Award Year:
1990
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
12181
Agency Tracking Number:
12181
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
2421 Glyndon Ave, Venice, CA, 90291
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
William P Peschel
(213) 306-2287
Business Contact:
() -
Research Institute:
n/a
Abstract
COMPRISES IN WIND TUNNEL OPERATIONAL PARAMETERS, RELATIVE TO ACTUAL ATMOSPHERIC FLIGHT, AND INADEQUACINES IN NUMERICAL SIMULATIONS INDICATE THE REQUIREMENT FOR A NONINTRUSIVE DIAGNOSTIC TECHNIQUE WHICH CAN ENABLE PROFILES OF KEY PLASMA BOUNDARY LAYER PARAMETERS (E.E., ELECTRON DENSITY AND ELECTRON COLLISION FREQUENCY) TO BE DIRECTLY MEASURED IN REAL FLIGHT OR WIND TUNNEL ENVIRONMENT. WE PROPOSE AN INNOVATIVE APPROACH WHEREBY THE REQUIRED NONINTRUSIVE DIAGNOSITC TECHNIQUE RESULTS FROM THE ELECTROMAGNETIC PROBING OF HYPERSONIC BOUNDARY LAYERS, AND THE PLASMA SPATIAL PROFILES ARE ANALYTICALLY AND COMPUTATIONALLY RECONSTRUCTED FROM IMPEDANCE MEASUREMENTS. IN PHASE I, WE WILL DEMONSTRATE THE CONCEPT FEASIBILITYTHROUGH THE COMBINATION OF ANALYSIS, NUMERICAL COMPUTATIONS, AND EXPERIMENTS. PHASE II WILL INCLUDE EXPERIMENTAL DEMONSTRATION TESTS AND THE OPTIMIZATION OF COMPUTATIONAL ALGORITHMS FOR THE QUANTITATIVE DETERMINATION OF PLASMA SPATIAL PROFILES. THE PROPOSED TECHNIQUE COULD SIGNIFICANTLY ENHANCE THE BENCHMARK OF REAL GAS COMPUTATIONAL FLUID DYNAMIC (CFD) SIMULATION CODES, AND IT COULD ENABLE ON-LINE EVALUATIONS OF CRITICAL PLASMA PROPERTIES DURING WIND TUNNEL SIMULATED AND ACTUAL ATMOSPHERIC HYPERSONIC FLIGHT.

* information listed above is at the time of submission.

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