NASA 1996 SBIR Phase I


PROPOSAL NUMBER : 96-1 01.05-0818

PROJECT TITLE : A Novel Computational Tool for Hypersonic Transition Prediction

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Laminar to turbulent transition phenomenon in hypersonic flows remains poorly understood although it has a profound impact on the thermal protection system weight, vehicle drag and air-breathing engine performance. Transition location uncertainty forces designers to be conservative by adding weight and reducing thrust. Accurate prediction techniques are in dyer need. Here, we propose to develop a transition prediction tool based on an innovative Navier-Stokes solver. The resulting code is computationally efficient and can be used to study the receptivity and disturbance growth without the restriction of slowly varying mean flows. The low streamwise resolution requirement in the proposed approach is made possible by a transformation which not only improves the accuracy but also helps in imposition of the outflow boundary conditions. The proposed tool can be used for studying various instability problems of relevance in supersonic and hypersonic flows such as blunt body flow and flow past a corner. This project will result in a reliable tool for prediction of transition for hypersonic vehicles.
POTENTIAL COMMERCIAL APPLICATIONS
Transition location affects thermal protection system weight, vehicle drag and air-breathing engine performance. The proposed project will be a major step towards developing reliable techniques for hypersonic transition prediction. Therefore, the code will be of interest to aerospace companies. Since NASA is also involved in designing hypersonic vehicles, the developed code will also be of interest to NASA.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
Dr. Mujeeb R. Malik
High Technology Corporation
28 Research Drive
Hampton, VA 23666
NAME AND ADDRESS OF OFFEROR
High Technology Corporation
28 Research Drive
Hampton, VA 23666