Abstract
The flow about a wing-body-sting configuration with a 65-deg sharp-edged cropped delta wing and an under-wing body is simulated by solving the Euler equations. Results are presented for the configuration at a Mach number of 0.85 and at incidences ranging from 10 to 20 deg. For this transonic free-stream Mach number a strong leading-edge vortex as well as shocks develop in the flow field above the wing. For the wing-body-sting configuration the numerical solution is investigated in detail and computational results are compared with experimental data. The investigation includes the analysis of the complex flow pattern in the near wake. The influence of the under-wing body on the flow field about the wing is assessed by comparing the solution for the complete configuration with the solution obtained for the wing alone on a grid similar to that for the wing-body-sting configuration.
| Original language | English |
|---|---|
| Title of host publication | 9th Applied Aerodynamics Conference 1991 |
| Subtitle of host publication | 23 September 1991 - 25 September 1991, Baltimore, MD, U.S.A. |
| Place of Publication | Reston, VA |
| Publisher | Aerospace Research Central |
| DOIs | |
| Publication status | Published - 1991 |
| Externally published | Yes |
| Event | 9th Applied Aerodynamics Conference, 1991 - Baltimore, United States Duration: 23 Sept 1991 → 25 Sept 1991 Conference number: 9 |
Publication series
| Name | AIAA Meeting Paper |
|---|---|
| Publisher | Aerospace Research Central |
| Number | 91-3310 |
| ISSN (Print) | 0146-3705 |
Conference
| Conference | 9th Applied Aerodynamics Conference, 1991 |
|---|---|
| Country/Territory | United States |
| City | Baltimore |
| Period | 23/09/91 → 25/09/91 |