Abstract
An analytical expression is proposed to estimate the wave drag of an aerofoil equipped with shock control. The analysis extends the conventional approach for a single normal shock wave, based on the knowledge that all types of successful shock control on transonic aerofoils cause bifurcated λ-shock structures. The influence of surface curvature on the λ-shock structure has been taken into account. The extended method has been found to produce fairly good agreement with the results obtained by CFD methods while requiring negligible computational effort. This new formulation is expected to be beneficial in the industrial design process of transonic aerofoils and wings where a large number of computational simulations have to be performed.
| Original language | English |
|---|---|
| Pages | 5519-5528 |
| Number of pages | 10 |
| Publication status | Published - Dec 1 2005 |
| Externally published | Yes |
| Event | 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 10 2005 → Jan 13 2005 |
Other
| Other | 43rd AIAA Aerospace Sciences Meeting and Exhibit |
|---|---|
| Country | United States |
| City | Reno, NV |
| Period | 1/10/05 → 1/13/05 |
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All Science Journal Classification (ASJC) codes
- Engineering(all)
Cite this
Evaluation of wave drag reduction by flow control. / Ogawa, H.; Babinsky, H.
2005. 5519-5528 Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.Research output: Contribution to conference › Paper
}
TY - CONF
T1 - Evaluation of wave drag reduction by flow control
AU - Ogawa, H.
AU - Babinsky, H.
PY - 2005/12/1
Y1 - 2005/12/1
N2 - An analytical expression is proposed to estimate the wave drag of an aerofoil equipped with shock control. The analysis extends the conventional approach for a single normal shock wave, based on the knowledge that all types of successful shock control on transonic aerofoils cause bifurcated λ-shock structures. The influence of surface curvature on the λ-shock structure has been taken into account. The extended method has been found to produce fairly good agreement with the results obtained by CFD methods while requiring negligible computational effort. This new formulation is expected to be beneficial in the industrial design process of transonic aerofoils and wings where a large number of computational simulations have to be performed.
AB - An analytical expression is proposed to estimate the wave drag of an aerofoil equipped with shock control. The analysis extends the conventional approach for a single normal shock wave, based on the knowledge that all types of successful shock control on transonic aerofoils cause bifurcated λ-shock structures. The influence of surface curvature on the λ-shock structure has been taken into account. The extended method has been found to produce fairly good agreement with the results obtained by CFD methods while requiring negligible computational effort. This new formulation is expected to be beneficial in the industrial design process of transonic aerofoils and wings where a large number of computational simulations have to be performed.
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UR - http://www.scopus.com/inward/citedby.url?scp=30744466435&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:30744466435
SP - 5519
EP - 5528
ER -