Automatic Transition Prediction in Hybrid Flow Solver, Part 2: Practical Application

Abstract

This article is the second of two companion papers which document the concept and the application of a coupled
\ncomputational fluid dynamics system which was designed to incorporate the prediction of laminar�turbulent
\ntransition into a hybrid Reynolds-averaged Navier�Stokes solver. Whereas the first part deals with the description of
\nthe transition prediction methodology and the sensitivities of the coupled system, the second part documents its
\npractical application. The complete coupled system consists of the Reynolds-averaged Navier�Stokes code, a laminar
\nboundary-layer code, and a fully automated local, linear stability code. The system predicts and applies transition
\nlocations due to Tollmien�Schlichting and crossflow instabilities using the eN method based on the two-N-factor
\napproach. The coupled system was designed to be applied to three-dimensional aircraft configurations which are of
\nindustrial relevance. The application of the coupled system to a wing�body configuration with a three-element wing
\nconsisting of slat, main wing, and flap is described and documented in this paper. The prediction of the laminar�
\nturbulent transition lines was done in a fully automatic manner. It is shown that complex aircraft configurations can
\nbe handled without a priori knowledge of the transition characteristics of the specific flow problem.