INTERNAL FLUID MECHANICS OF LIQUID PROPELLANT ROCKET THRUST CHAMBERS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$494,238.00
Award Year:
1986
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Agency Tracking Number:
1764
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Scientific Research Associates
P.o. Box 498, Glastonbury, CT, 06033
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Howard J. Gibeling
Investigator
() -
Business Contact:
() -
Research Institution:
n/a
Abstract
THIS PROJECT ADDRESSES A COMPUTER CODE CAPABLE OF ACCURATELY SIMULATING THE INTERNAL FLUID MECHANICS OF LIQUID PROPELLANT ROCKET THRUST CHAMBERS USING A COMBINED EULERIAN-LAGRANGIAN DESCRIPTION. SUCH A CODE WILL BE EXTREMELY USEFUL IN CONDUCTING A PARAMETRIC STUDY OF THE EFFECT OF DESIGN PARAMETERS ON ENGINE PERFORMANCE AND IN STUDYING THE PERFORMANCE OF THRUST CHAMBERS WITH VARIABLE THRUST. WHILE THE LONG TERM GOAL OF THE EFFORT IS THE DEVELOPMENT OF A CODE TO SIMULATE THE MULTI-COMPONENT, MULTI-PHASE, REACTING FLOW IN REALISTIC THRUST CHAMBERS, THE OBJECTIVE OF THE PHASE I EFFORT IS TO ESTABLISH THE FEASIBILITY OF THE APPROACH BY SIMULATING THE FLOW FIELD IN A SIMPLIFIED MODEL THRUST CHAMBER INVOLVING SINGLE-COMPONENT, TWO-PHASE, NON-REACTING FLOW OF EVAPORATING "PROPELLANT". THIS OBJECTIVE WILL BE ACHIEVED BY SUITABLY MODIFYING AN EXISTING MULTIDIMENSIONAL, TIME-DEPENDENT NAVIER-STOKES CODE TO INCLUDE THE LAGRANGIAN DESCRIPTION OF THE DROPLET DYNAMICS.

* information listed above is at the time of submission.

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