TY - JOUR
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 - 2006/1
Y1 - 2006/1
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 in the absence of control, 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 in the absence of control, 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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U2 - 10.1016/j.ast.2005.08.001
DO - 10.1016/j.ast.2005.08.001
M3 - Article
AN - SCOPUS:31044452879
SN - 1270-9638
VL - 10
SP - 1
EP - 8
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
IS - 1
ER -