Analysis of viscous transonic flow over airfoil sectionsA full Navier-Stokes solver has been used to model transonic flow over three airfoil sections. The method uses a two-dimensional, implicit, conservative finite difference scheme for solving the compressible Navier-Stokes equations. Results are presented as prescribed for the Viscous Transonic Airfoil Workshop to be held at the AIAA 25th Aerospace Sciences Meeting. The NACA 0012, RAE 2822 and Jones airfoils have been investigated for both attached and separated transonic flows. Predictions for pressure distributions, loads, skin friction coefficients, boundary layer displacement thickness and velocity profiles are included and compared with experimental data when possible. Overall, the results are in good agreement with experimental data.
Document ID
19870047449
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huff, Dennis L. (NASA Lewis Research Center Cleveland, OH, United States)
Wu, Jiunn-Chi (NASA Lewis Research Center Cleveland, OH, United States)
Sankar, L. N. (Georgia Institute of Technology Atlanta, United States)