Optimization of natural laminar flow airfoils for high section lift-to-drag ratios in the lower Reynolds number rangeRelatively thin natural-laminar-flow airfoils were arranged optimally for different design lift coefficients in the wing chord Reynolds number ranges of 200,000-600,00 and 0.875 x 10 to the 6th to 2 x 10 to the 6th. The 9.5 percent thick airfoil ASM-LRN-010, the 7.9 percent thick airfoil ASM-LRN-012, the 10.4 percent thick airfoil ASM-LRN-015, and the 8.2 percent thick airfoil ASM-LRN-017 were designed for high lift-to-drag ratios using Drela's design and analysis.
Document ID
19890041057
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pfenninger, Werner (Analytical Services and Materials, Inc. Hampton, VA, United States)
Vemuru, Chandra S. (Analytical Services and Materials, Inc. Hampton, VA, United States)