Flow Prediction for Propfan Engine Installation Effects on Transport Aircraft at Transonic SpeedsAn Euler-based method for aerodynamic analysis of turboprop transport aircraft at transonic speeds has been developed. In this method, inviscid Euler equations are solved over surface-fitted grids constructed about aircraft configurations. Propeller effects are simulated by specifying sources of momentum and energy on an actuator disc located in place of the propeller. A stripwise boundary layer procedure is included to account for the viscous effects. A preliminary version of an approach to embed the exhaust plume within the global Euler solution has also been developed for more accurate treatment of the exhaust flow. The resulting system of programs is capable of handling wing-body-nacelle-propeller configurations. The propeller disks may be tractors or pushers and may represent single or counterrotation propellers. Results from analyses of three test cases of interest (a wing alone, a wing-body-nacelle model, and a wing-nacelle-endplate model) are presented. A user's manual for executing the system of computer programs with formats of various input files, sample job decks, and sample input files is provided in appendices. |
Common terms and phrases
aerodynamic analysis angle approach ATTACH body Boeing Commercial Airplane boundary condition boundary layer calculated cells CHARGE chord CHRGNO Column common boundary computational domain configuration containing convergence coordinate COPY counter CYBER DAYFILE defined described desired developed direction disk distribution downstream effects equations Euler Equations EXECUTE exhaust flow exhaust plume extract field Figure flowfield flux fuselage geometry given global grid cells grid embedding Header card includes input file interest intersection JCS="USER leading edge LOAD located lower mesh method MFLINK momentum nacelle nonzero normal NOTE origin OUTPUT Parameter PASSWOR performed physical plane present PROCESSING propeller Propfan PURGE Recommended value Reference region represents SAMANT section curve shown simulated solution solved spanwise ST=MZZ step SUMMARY surface grid swirl TONOS Transonic typical upper USERNOC variables vectorization volume grid wing surface Wing-Nacelle