You are here

Advanced Aerodynamic Analysis For Propulsion Airframe Integration

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX15CL92P
Agency Tracking Number: 155224
Amount: $123,473.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A1.05
Solicitation Number: N/A
Solicitation Year: 2015
Award Year: 2015
Award Start Date (Proposal Award Date): 2015-06-17
Award End Date (Contract End Date): 2015-12-17
Small Business Information
1919 North Ashe Court
Auburn, AL 36830-2691
United States
DUNS: 078301615
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 John Burkhalter
 Principal Investigator
 (334) 444-8523
Business Contact
 Roy Hartfield
Title: Business Official
Phone: (334) 444-8523
Research Institution

Research in Flight is proposing to develop a fundamentally new, lower order, high fidelity solution approach for the aerodynamic analysis required for engine integration studies. This new approach is based on a new tool known as Flightstream. Flightstream is a surface vorticity based solver which uses an unstructured surface geometry, and a correlation for skin friction which is based on the surface vorticity. For lift and induced drag calculations, Fligthstream makes use of the Kutta Joukowski Theorem. The Kutta Joukowski Theorem has proven to be a remarkably accurate method for calculating loads for essentially all lifting configurations in which the flow is attached to the surface. Research in Flight has demonstrated many compelling capabilities of Flightstream to accurately predict the aerodynamic loads on a range of geometries including high lift configurations. This fundamentally new approach to aircraft outer mold line evaluation offers the speed and fidelity required for even optimization based design. The speed of Flightstream is comparable to traditional panel approaches yet the fidelity in calculating loads has been shown to be comparable to high fidelity CFD solutions. To further compliment the utility of FLightstream as a compelling design tool, Flightstream has been configured to operate seamlessly with NASA's Vehicle Sketch Pad (VSP) software. The primary function of the proposed activity will be to develop an automated approach to engine integration by coupling the compelling capabilities of Flightstream with optimization tools, rudimentary engine performance tools, and automated grid generation using VSP. The goals for the optimization will be related to aerodynamic performance and will include lift to drag and moment calculations in consultation with the technical point of contact at NASA. A report on the progress during Phase I will outline the process and will include preliminary results.

* Information listed above is at the time of submission. *

US Flag An Official Website of the United States Government