FINITE DIFFERENCE FLOW CALCULATIONS FOR HELICOPTER ROTOR/FUSELAGE CONFIGURATIONS

Award Information
Agency:
Department of Defense
Branch
Army
Amount:
$58,750.00
Award Year:
1987
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
6636
Agency Tracking Number:
6636
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
9208 Ridge Blvd, Brooklyn, NY, 11209
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
JOHN STEINHOFF
(615) 455-1678
Business Contact:
() -
Research Institute:
n/a
Abstract
THE DEVELOPMENT OF A COMPUTER CODE TO SOLVE FOR THE FLOW OVER A HELICOPTER ROTOR/FUSELAGE CONFIGURATION IS PROPOSED. A MODULAR APPROACH IS TO BE USED WHERE TWO EXISTING FINITE DIFFERENCE CODES, ONE FOR THE ROTOR, THE OTHER FOR THE FUSELAGE ARE MATED. THE INDIVIDUAL MODULES HAVE BEEN PREVIOUSLY DEVELOPED BY THE INVESTIGATORS. THE ROTOR MODULE INVOLVES A BLADE-FIXED COORDINATE SYSTEM. IT HAS BEEN SUCCESSFULLY VALIDATED BY COMPARISON WITH EXPERIMENT FOR TWO ND FOUR BLADE ROTORS AND SUBSONIC AND TRANSONIC CASES. THE FUSELAGE MODULE, INCLUDING A GRID GENERATION CODE, HAS BEEN USED TO SOLVE FOR THE FLOW OVER COMPLEX AIRCRAFT CONFIGURATIONS. THE MATING PROCEDURE INVOLVES A UNIQUE "SLIDING INTERFACE" THAT ALLOWS THE GRID USED IN EACH MODULE TO SLIDE PAST THE OTHER GRID ALONG A COMMON INTERFACE AS THE ROTOR ROTATES WITH RESPECT TO THE FUSELAGE, AND YET ENABLES FLOW VARIABLES TO BE TRANSFERRED ACROSS THE INTERFACE WITHOUT REQUIRING INTERPOLATION. THE MODULAR APPROACHED PROPOSED WILL ALLOW THE EXISTING CODES PREVIOUSLY DEVELOPED TO BE USED WITH STRAIGHTFORWARD MODIFICATIONS, WITH REQUIRING THE DEVELOPMENT WORK TO BE REPEATED. A SUCCESSFUL FINITE DIFFERENCE CODE FOR THE ROTOR/FUSELAGE PROBLEM WILL BE SUPERIOR COMPARED TO INTEGRAL METHODS WITH RESPECT TO THE TREATMENT OF COMPESSIBILITY, ACCURACY, AND, IN THE FUTURE, THE INCLUSION OF TURBULENT TRANSPORT TERMS.

* information listed above is at the time of submission.

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