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Inviscid analysis of two supercritical laminar-flow-control airfoils at design and off-design conditionsInviscid 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.
Document ID
19850021608
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Allison, D. O. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:84657
L-15571
NASA-TM-84657
Accession Number
85N29920
Funding Number(s)
PROJECT: RTOP 505-31-23-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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