[bdb5e] *Full@ !Download^ Surface-Pressure and Flow-Visualization Data at Mach Number of 1.60 for Three 65 Deg Delta Wings Varying in Leading-Edge Radius and Camber - National Aeronautics and Space Administration *e.P.u.b% Online

[bdb5e] *F.u.l.l.% *D.o.w.n.l.o.a.d% Surface-Pressure and Flow-Visualization Data at Mach Number of 1.60 for Three 65 Deg Delta Wings Varying in Leading-Edge Radius and Camber - National Aeronautics and Space Administration %ePub*

An experimental investigation of the effect of leading-edge radius, camber, Reynolds number, and boundary-layer state on the incipient separation of a delta wing at supersonic speeds was conducted at the Langley Unitary Plan Wind Tunnel at Mach number of 1.60 over a free-stream Reynolds number range of 1 x 106 to 5 x 106 ft-1. The three delta wing models examined had a 65

Title : Surface-Pressure and Flow-Visualization Data at Mach Number of 1.60 for Three 65 Deg Delta Wings Varying in Leading-Edge Radius and Camber
Author : National Aeronautics and Space Administration
Language : en
Rating :
4.90 out of 5 stars
Type : PDF, ePub, Kindle
Uploaded : Apr 15, 2021
Book code : bdb5e

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