Evaluation of wave drag reduction by flow control

H. Ogawa; H. Babinsky

doi:10.2514/6.2005-1415

Evaluation of wave drag reduction by flow control

H. Ogawa, H. Babinsky

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

4 Citations (Scopus)

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
Title of host publication	43rd AIAA Aerospace Sciences Meeting and Exhibit
Pages	5519-5528
Number of pages	10
DOIs	https://doi.org/10.2514/6.2005-1415
Publication status	Published - 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/Territory	United States
City	Reno, NV
Period	1/10/05 → 1/13/05

All Science Journal Classification (ASJC) codes

Engineering(all)

Access to Document

10.2514/6.2005-1415

Cite this

@inproceedings{1d347a7cf0bb49899de5ba9755de26ca,

title = "Evaluation of wave drag reduction by flow control",

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.",

author = "H. Ogawa and H. Babinsky",

note = "Funding Information: The present research has been accomplished with the financial support of the Nakajima Foundation.; 43rd AIAA Aerospace Sciences Meeting and Exhibit ; Conference date: 10-01-2005 Through 13-01-2005",

year = "2005",

doi = "10.2514/6.2005-1415",

language = "English",

pages = "5519--5528",

booktitle = "43rd AIAA Aerospace Sciences Meeting and Exhibit",

}

TY - GEN

T1 - Evaluation of wave drag reduction by flow control

AU - Ogawa, H.

AU - Babinsky, H.

N1 - Funding Information: The present research has been accomplished with the financial support of the Nakajima Foundation.

PY - 2005

Y1 - 2005

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.

UR - http://www.scopus.com/inward/record.url?scp=30744466435&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=30744466435&partnerID=8YFLogxK

U2 - 10.2514/6.2005-1415

DO - 10.2514/6.2005-1415

M3 - Conference contribution

AN - SCOPUS:30744466435

SP - 5519

EP - 5528

BT - 43rd AIAA Aerospace Sciences Meeting and Exhibit

T2 - 43rd AIAA Aerospace Sciences Meeting and Exhibit

Y2 - 10 January 2005 through 13 January 2005

ER -

Evaluation of wave drag reduction by flow control

Abstract

Other

All Science Journal Classification (ASJC) codes

Access to Document

Other files and links

Fingerprint

Cite this