In this paper, a study on designing a thick supercritical airfoil by utilizing Takanashi's inverse design method is discussed. One of the problems to design a thick supercritical airfoil by Takanashi's method is that an oscillation of the geometry may occur during the iteration process. To reduce the oscillation, an airfoil parameterization method is utilized as the smoothing procedure. A guideline to determine the target pressure distribution to realize the thick airfoil is also discussed.
|Number of pages||6|
|Journal||Transactions of the Japan Society for Aeronautical and Space Sciences|
|Publication status||Published - 2000 Aug|
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science