Fiscal Year:
1987
Title:
FINITE DIFFERENCE FLOW CALCULATIONS FOR HELICOPTER ROTOR/FUSELAGE CONFIGURATIONS
Agency / Branch:
DOD / ARMY
Contract:
N/A
Award Amount:
$58,750.00
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.
Principal Investigator:
John steinhoff
6154551678
Business Contact:
Small Business Information at Submission:
Vra Inc
9208 Ridge Blvd Brooklyn, NY 11209
EIN/Tax ID:
DUNS:
N/A
Number of Employees:
Woman-Owned:
No
Minority-Owned:
No
HUBZone-Owned:
No