SBIR/STTR Research Award
COMPUTATION OF THE TIP VORTEX FLOW FIELD FOR ADVANCED PROPELLERS
Award amount
$476,246Program and phase
SBIR · Phase IIAward year
1986Award details
- Awarding agency
- National Aeronautics and Space Administration
- Branch
- Not reported
- Recipient company
- SCIENTIFIC RESEARCH ASSOC., INC.
- Proposal award date
- Not reported
- Contract end date
- Not reported
- UEI
- Not reported
- Solicitation number
- Not reported
- Topic code
- Not reported
Research 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.
Technology keywords
Not reported