Program to obtain data on thick airfoils to be used for pressure-jet rotor system; hovering performance of rotor for tip Mach number from 0.27 to 0.76 and corresponding blade tip Reynolds number range; performance characteristics of thick airfoils may be seriously limited by stall starting at trailing edges of airfoils; hovering performance of rotor with vortex generator compared with smooth-blade rotor.
High-tip-speed static-thrust tests of rotor having NACA 63215 A018 airfoil sections with and without vortex generators installed
NASA -- Tech Note
1960
21 pages
Report
English
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High speed subsonic characteristics of 16 NACA 6-series airfoil sections
Engineering Index Backfile | 1952
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