The present paper shows integral boundary-layer solutions and finite-volume Reynolds-Averaged Navier Stokes (RANS) Computational Fluid Dynamics (CFD) results for flow around a NACA 8H12 airfoil profile. The objective of the present paper is to verify and compare a CFD tool with traditional integral code results and experimental data in two subsonic Reynolds numbers: . and . , where open literature experimental data exist for NACA 8H12 airfoil. An incompressible boundary-layer code coupled with external potential flow solution can be adequate for subsonic Reynolds ranges with ideal airfoils but has limitations for applications in compressible-flow regime, notably out of the correlation corrections range, in presence of massive separation at high angles of attack, particularly when one is trying to solve actual airfoil shapes. A numerical code that solves integral equations of boundary layer -with transition onset and length predictions as well as the intermittency evolution -is implemented based on literature models. Both CFD and integral code results are compared with experimental data for pressure, drag, lift and moment coefficients. The results show that laminar-turbulent transition consideration is very important to represent actual airfoil aerodynamics performance.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.