NASA NTRS · 19780010056
Two-dimensional transonic testing with splitter plates
Abstract
The use of splitter plates for two dimensional transonic testing in wind tunnels was investigated on a 12% biconvex airfoil section over the Mach number range 0.6 to 1.0. Measured pressure distributions were compared to transonic theory and to other experiments, including an investigation in the same facility without splitter plates. The results of the experiment show the best agreement with theory over the entire transonic Mach number range.
Keep this discovery
Explore connections, maps & timelines
Davis, S., Satyanarayana, B.. 1978-02-01. Two-dimensional transonic testing with splitter plates. https://ntrs.nasa.gov/citations/19780010056
Cite the original work for its findings. Save a collection to share your selection of sources.