COMPUTATION OF THE TIP VORTEX FLOW FIELD FOR ADVANCED PROPELLERS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$476,246.00
Award Year:
1986
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
1668
Agency Tracking Number:
1668
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
P.o. Box 498, Glastonbury, CT, 06033
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Ralph Levy
Investigator
() -
Business Contact:
() -
Research Institute:
n/a
Abstract
THE BLADE TIP VORTEX FLOW FIELD HAS A SIGNIFICANT IMPACT ON THE AERODYNAMIC PERFORMANCE AND ACOUSTIC CHARACTERISTICS OF AIRCRAFT PROPELLERS. THIS PROJECT INVOLVES COMPUTATION OF TIP VORTEX GENERATION PROCESS FOR ADVANCED PROPELLERS USING A FORWARD MACHING PROCEDURE. THE PROCEDURE WOULD BE USED TO COMPUTE COMPRESSIBLE HIGH SUBSONIC, HIGH REYNOLDS NUMBER TURBULENT FLOW FIELD ENCOUNTERED IN ADVANCED PROPELLERS. FOR THIS PURPOSE, AN EXISTING COMPUTER CODE WILL BE EXTENDED TO COMPUTE THE TIP VORTEX GENERATION PROCESS FOR COMPRESSIBLE HIGH SUBSONIC TURBULENT FLOWS. A COMPUTATION WILL BE CARRIED OUT TO DEMONSTRATE THE FEASIBILITY OF COMPUTING THE TIP VORTEX FLOW FIELD FOR ADVANCED PROPELLERS. A SUBSEQUENT PHASE II EFFORT WILL EXTEND THE METHOD TO ACTUAL PROPELLER GEOMETRIES. THE PREDICTIVE PROCEDURE WOULD BE ASSESSED AGAINST AVAILABLE DATA. APPLICATION OF THIS VISCOUS, THREE-DIMENSIONAL PROCEDURE WOULD PRESENT A NEW AND PROMISING APPROACH TO THE PROBLEM OF ADVANCED PROPELLER DESIGN FLOW FIELDS.

* information listed above is at the time of submission.

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