2,952 research outputs found
The flow past a straight and a swept-wing-body combination and their equivalent bodies of revolution at Mach numbers near 1.0
Get PDFTests utilizing the Schlieren method of flow photography have been conducted to provide a comparison of the complete flow fields past a straight and a swept-wing-body combination and the flow fields past their equivalent bodies of revolution at Mach numbers around 1.0. The results indicated that the shock growth and positions on the wing-body combinations were closely reproduced in the flow past the equivalent body
A Variable-frequency Light Synchronized with a High-speed Motion-picture Camera to Provide Very Short Exposure Times
Get PDFThe development and performance of two small tunnels capable of intermittent operation at Mach numbers between 0.4 and 4.0
Get PDFSome Observations on Maximum Pressure Rise Across Shocks Without Boundary-layer Separation on Airfoils at Transonic Speeds
Get PDFCompilation of Information on the Transonic Attachment of Flows at the Leading Edges of Airfoils
Get PDFSchlieren photographs have been compiled of the two-dimensional flow at transonic speeds past 37 airfoils. These airfoils have variously shaped profiles, and some are related in thickness and camber. The data for these airfoils were analyzed to provide basic information on the flow changes involved and to determine factors affecting transonic-flow attachment, which is a transition from separated to unseparated flow at the leading edges of two-dimensional airfoils at fixed angles as the subsonic Mach number is increased
Two-dimensional Transonic Investigation of Flows and Forces on a 9-percent-thick Airfoil with 30-percent-chord Flap
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