This study aims to develop a computational fluid dynamics (CFD) analysis model to be used in the nose optimization at hypersonic speeds and to validate the model. While creating the analysis model, standard hyperballistic-1 (HB-1) geometry, whose tests were made in the wind tunnel, was used. Base equation used in the study is compressible real gas Navier-Stokes equations. Generated structured grids were analyzed in METACOMP CFD++. During the model validation, aerodynamic coefficients obtained from the CFD analysis were compared with the wind tunnel test results for HB-1. Comparing CFD results and wind tunnel data for axial force coefficient indicated that CFD analysis estimates this coefficient 5% lesser. Examining normal force coefficient and pitching moment coefficient showed that the results obtained from CFD analysis had a similar trend to the wind tunnel results.
Development of Viscous CFD Analysis Model Including Real Gas Effects for Nose Optimization at Hypersonic Speeds
Sustainable aviat.
International Symposium on Electric Aircraft and Autonomous Systems ; 2022 ; Maribor, Slovenia July 19, 2022 - July 21, 2022
2023-08-24
10 pages
Article/Chapter (Book)
Electronic Resource
English
Laminar turbulent transition at hypersonic speeds: the effects of nose blunting
British Library Online Contents | 1995
|Laminar turbulent transition at hypersonic speeds: the effects of nose blunting
British Library Conference Proceedings | 1995
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