NTRS - NASA Technical Reports Server

Back to Results
Multi-element airfoil optimization for maximum lift at high Reynolds numbersAn experimental study has been performed to assess the maximum lift capability of a supercritical multielement airfoil representative of an advanced transport aircraft wing. The airfoil model was designed with a leading-edge slat and single or two-segment trailing-edge flaps. Optimization work was performed at various slat/flap deflections as well as gap/overhang positions. Landing configurations and the attainment of maximum lift coefficients of 4.5 with single-element flaps and 5.0 with two-segment flaps was emphasized. Test results showed a relatively linear variation of the optimum gap/overhang positioning of the slat versus slat deflection, considerable differences in optimum rigging between single and double segment flaps, and large Reynolds number effects on multielement airfoil optimization.
Document ID
Document Type
Conference Paper
Valarezo, Walter O.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Dominik, Chet J.
(Douglas Aircraft Co. Long Beach, CA, United States)
Mcghee, Robert J.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Goodman, Wesley L.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Paschal, Keith B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Report/Patent Number
AIAA PAPER 91-3332
Accession Number
Distribution Limits

Available Downloads

There are no available downloads for this record.
No Preview Available