A Preliminary Design Tool for Shrouded-Fans

Award Information
Agency:
Department of Defense
Branch
Army
Amount:
$119,018.00
Award Year:
2002
Program:
SBIR
Phase:
Phase I
Contract:
DAAH10-02-C-0040
Award Id:
58009
Agency Tracking Number:
A012-0478
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Sukra Helitek, Inc. (Currently Sukra Helitek Inc.)
3146, Greenwood road, Ames, IA, 50014
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
877929125
Principal Investigator:
Saeid Niazi
Aeronautical Engineer
(515) 292-8918
niazi@sukrahelitek.com
Business Contact:
R Nappinnai
President
(515) 292-9646
nappi@sukra-helitek.com
Research Institution:
n/a
Abstract
"Shrouded-fans are an integral part of the U.S. Army's transportation systems. TheRAH-66's fan-tail, Sikorsky's Cypher and Micro-Craft's UAV are testimonials to theirincreasing importance. Shrouded-fans are efficient, but aerodynamically very complex,particularly in non-axial flight conditions such as conversion modes. The viscouscharacteristics of the flow through the shrouded-fan play an imortant role in thethree dimensional moments and forces generated in non-axial flight conditons.This proposal offers to develop an efficient, robust and fast preliminary designtool capable of analyzing the performance and flowfield of shrouded-fans in axialand non-axial flight conditions.The principle parts of the tool are:1. A viscous solver for shroud conforming grids2. An efficient rotor model3. An integral body conforming grid generatorIn Phase I, viscous flow through a shrouded-fan in non-axial flight conditions,but with fixed shroud orientation, will be computed as proof-of-concept of anefficient design tool. In Phase II, continuous rotation of the shroud about itsown axis, such as in conversion modes from hover to forward flight, will beundertaken. The software developed under this initiative will find wide usage in the DODrotorcraft organizations, rotorcraft industry and NASA. This proposal offers acomputational tool that will lay the foundations for true transient wakecalculation of a shrouded-fan in axial and non-axial flight conditions.S

* information listed above is at the time of submission.

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