Abstract
This paper presents numerical simulation of flowfields around a supersonic transport aircraft with an integrated engine nacelle. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flights, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated hi detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results were compared with wind tunnel data obtained at National Aerospace Laboratory of Japan.
Original language | English |
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DOIs | |
Publication status | Published - 2002 |
Externally published | Yes |
Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 2002 Jan 14 → 2002 Jan 17 |
Other
Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
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Country/Territory | United States |
City | Reno, NV |
Period | 02/1/14 → 02/1/17 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering