Analytical method for the ditching analysis of an airborne vehicle

NASA NTRS · Reprint (Version printed in journal) · 19900044225 · Published 1995-11-28 · Langley Research Center · 1 author

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Abstract and citation only, verbatim from NASA NTRS; full text lives there. All credit to the authors and Langley Research Center.

Abstract

A simple analytical method has been introduced for aerohydrodynamic load analysis of an airborne configuration during water ditching. The method employs an aerodynamic panel code, based on linear potential flow theory, to simulate the flow of air and water around an aircraft configuration. The free surface separating the air and water region is represented by doublet" singularities. Although all the theoretical load distributions are computed for air, provisions are made to correct the pressure coefficients obtained on the configuration-wetted surfaces to account for the water density. As an analytical tool, a vortex aerodynamic code is chosen to carry out the present investigation. After assessing· the validity of the method, an application is presented for the water ditching of the Space Shuttle configuration at a 12-deg attitude.

Author

Farhad Ghaffari ViGYAN (United States)

Keywords

Pressure coefficient
Angle of attack
Aircraft ditching
Aerodynamic properties
Flow conditions
Space shuttle
Surface modeling
Flow characteristics
Solid rocket boosters
Wind tunnels

Citation

Farhad Ghaffari (1995). Analytical method for the ditching analysis of an airborne vehicle. Langley Research Center. NASA NTRS ID 19900044225. https://ntrs.nasa.gov/citations/19900044225 ↗