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- W264859081 abstract "Inviscid transonic flow results are provided at design and off design conditions for two supercritical laminar flow control airfoils. The newer airfoil, with its lower suction requirements for full chord laminar flow, has a higher design Mach number, steeper pressure gradients, a more positive pressure level in the forward region of the lower surface, and a recovery to a less positive pressure at the trailing edge. The two dimensional design Mach numbers for the two airfoils are 0.755 and 0.730 at a common design lift coefficient of 0.60, and their thickness to chord ratios are 0.131 and 0.135, respectively. Off design shock formation characteristics are similar for the two airfoils over a range of Mach numbers between 0.6 and 0.8 and lift coefficients from 0.4 to 0.7. The newer airfoil is similar to the one used in a large chord swept model experiment designed for the Langley 8 Foot Transonic Pressure Tunnel." @default.
- W264859081 created "2016-06-24" @default.
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- W264859081 date "1983-06-01" @default.
- W264859081 modified "2023-09-27" @default.
- W264859081 title "Inviscid analysis of two supercritical laminar-flow-control airfoils at design and off-design conditions" @default.
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