The efficient solution of transonic wing flow fieldsAn evaluation of the transonic-wing-analysis computer code TWING is presented. TWING utilizes a fully implicit, approximate-factorization iteration scheme to solve the full-potential equation in conservative form. A numerical elliptic-solver grid-generation scheme is used to generate the required finite-difference mesh. Several wing configurations have been analyzed, and comparisons of computed results have been made with available experimental data. Results indicate that the code is robust, accurate (when significant viscous effects are not present), and efficient. TWING generally produces solutions an order of magnitude faster than other conservative, full-potential codes using successive-line overrelaxation. The present method is applicable to a wide range of isolated wing configurations, including high-aspect-ratio transport wings and low-aspect-ratio, high-sweep, fighter configurations.
Document ID
19840027317
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Holst, T. L. (NASA Ames Research Center Moffett Field, CA, United States)
Subramanian, N. R. (NASA Ames Research Center Moffett Field, CA, United States)
Thomas, S. D. (Informatics General Corp. Palo Alto, CA, United States)