In this paper, the inverse shape design is introduced using the permeable wall boundary condition.
Inverse shape design defines the blade shape for the prescribed Mach numbers or pressure distribution
on its surface. It calculates the normal mass flux from the difference between the calculated and
prescribed pressure at the surface. A new geometry can be achieved after applying the quasi
one-dimensional continuity equation from the leading edge to the trailing edge. For validation of this
method, two test cases are studied. The first test case of inverse shape design illustrates the cosine
bump with a strong shock. After seven geometry modifications, the shock-free bump geometry can be
obtained. The second example concerns the redesign of a subsonic airfoil. The pressure distribution of
NACA0012 airfoil is imposed on the initial airfoil and the close geometry to NACA0012 can be
obtained. This proposed inverse design method has proven to be an efficient and robust tool in
turbomachinery design fields.