Three-dimensional compressible boundary layer calculations to fourth order accuracy on wings and fuselagesLaminar flow control and drag reduction research requires accurate boundary layer solutions as input to the three-dimensional stability analysis procedures currently under development. In support of these major programs, a fourth-order accurate finite difference scheme for solving the three-dimensional, compressible boundary layer equations has been developed and is presented in this paper. The method employs a two-point scheme in the wall normal direction and second order zigzag scheme in the cross flow direction. Accurate procedures to interface with the inviscid results are also presented. The results of applying the procedure to laminar flow on wings and fuselages are presented.
Document ID
19890037744
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Iyer, Venkit (NASA Langley Research Center Hampton, VA, United States)
Harris, Julius E. (NASA Langley Research Center Hampton, VA, United States)