NASA NTRS · 19750004827
Numerical solution for unsteady sonic flow over thin wings
Abstract
A numerical solution precedure of a simplified unsteady transonic equation which is fast, reasonably accurate, and takes into account many of the effects of the steady flow field is described. The numeric solution of this equation is accurate and is accomplished on an IBM 360/65 computer. Arbitrary planform shape is accommodated and variable local Mach number effects from the steady flow are easily handled.
Keep this discovery
Explore connections, maps & timelines
Kimble, K. R., Wu, J. M.. 1974-08-01. Numerical solution for unsteady sonic flow over thin wings. https://ntrs.nasa.gov/citations/19750004827
Cite the original work for its findings. Save a collection to share your selection of sources.