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.
|Number of pages||10|
|Publication status||Published - Dec 1 2005|
|Event||43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
Duration: Jan 10 2005 → Jan 13 2005
|Other||43rd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||1/10/05 → 1/13/05|
All Science Journal Classification (ASJC) codes