Application of a semi-empirical method to model subsonic vortex lift over sharp leading-edge delta wings
| dc.contributor.author | Huynh, Daniel | |
| dc.contributor.author | Di Pasquale, Davide | |
| dc.contributor.author | Prince, Simon A. | |
| dc.contributor.author | Ahuja, Vivek | |
| dc.date.accessioned | 2023-01-31T14:45:49Z | |
| dc.date.available | 2023-01-31T14:45:49Z | |
| dc.date.issued | 2023-01-19 | |
| dc.description.abstract | A semi-empirical method is applied as a complement to the FlightStream solver, to more accurately model subsonic vortex lift over a sharp leading-edge delta wing. The method, based on the prediction of flow patterns and the application of the Polhamus method, is particularly well-adapted to a preliminary aerodynamic design phase. Within a few minutes, it can accurately predict the aerodynamic forces generated by the flow over a delta wing, which are strongly affected by the presence of a leading-edge vortex. This study presents a detailed analysis where computed results are compared against experimental data. Those were obtained from a test case of a 65° subsonic delta wing experiment (case 1), along with a sensitivity analysis against sweep angle and aspect ratio where multiple subsonic delta wings were tested (case 2). A good agreement is observed between computed data and experimental results, within pre-stall, before the vortex bursts. Analysed results demonstrate the validity of the method, for multiple wing configurations associated with different flow conditions. | en_UK |
| dc.identifier.citation | Huynh D, Di Pasquale D, Prince SA, Ahuja V. (2023) Application of a semi-empirical method to model subsonic vortex lift over sharp leading-edge delta wings. In: AIAA SciTech Forum 2023, 23-27 January 2023, National Harbor, Maryland, USA | en_UK |
| dc.identifier.uri | https://doi.org/10.2514/6.2023-2457 | |
| dc.identifier.uri | https://dspace.lib.cranfield.ac.uk/handle/1826/19067 | |
| dc.language.iso | en | en_UK |
| dc.publisher | AIAA | en_UK |
| dc.rights | Attribution-NonCommercial 4.0 International | * |
| dc.rights.uri | http://creativecommons.org/licenses/by-nc/4.0/ | * |
| dc.title | Application of a semi-empirical method to model subsonic vortex lift over sharp leading-edge delta wings | en_UK |
| dc.type | Article | en_UK |