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COMPUTATION OF THE TIP VORTEX FLOW FIELD FOR ADVANCED PROPELLERS

Award Information

Agency:
National Aeronautics and Space Administration
Branch:
N/A
Award ID:
1668
Program Year/Program:
1986 / SBIR
Agency Tracking Number:
1668
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
SCIENTIFIC RESEARCH ASSOC., INC.
P. O. Box 1058, 30C Hebron Avenue Glastonbury, CT 06033
View profile »
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 2
Fiscal Year: 1986
Title: COMPUTATION OF THE TIP VORTEX FLOW FIELD FOR ADVANCED PROPELLERS
Agency: NASA
Contract: N/A
Award Amount: $476,246.00
 

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.

Principal Investigator:

Ralph Levy
Investigator
0

Business Contact:

Small Business Information at Submission:

Scientific Research Associates
P.o. Box 498 Glastonbury, CT 06033

EIN/Tax ID:
DUNS: N/A
Number of Employees: N/A
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No