TY - GEN
T1 - Exploration of a Low-Speed, Flapped, Slotted, Natural-Laminar-Flow Airfoil
AU - Maughmer, Mark D.
AU - Metkowski, Leonard P.
AU - Axten, Christopher J.
AU - Somers, Dan M.
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - A 12.91-percent-thick, flapped, slotted, natural-laminar-flow (SNLF) airfoil, the S702, intended for a low-speed, fixed-wing aircraft has been designed, analyzed theoretically, and verified experimentally in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The two primary objectives of high maximum lift, insensitive to roughness, and low profile drag have been achieved. The use of a simple flap for manipulation of the low-drag region and control purposes was also explored and found to provide the desired characteristics. The airfoil exhibits a sharp stall that is less abrupt than the stalls of earlier SNLF airfoils, which meets the design objective. The constraint on the pitching moment has been satisfied. Comparisons of the theoretical and experimental results show reasonably good agreement overall, given the complexity of the configuration.
AB - A 12.91-percent-thick, flapped, slotted, natural-laminar-flow (SNLF) airfoil, the S702, intended for a low-speed, fixed-wing aircraft has been designed, analyzed theoretically, and verified experimentally in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The two primary objectives of high maximum lift, insensitive to roughness, and low profile drag have been achieved. The use of a simple flap for manipulation of the low-drag region and control purposes was also explored and found to provide the desired characteristics. The airfoil exhibits a sharp stall that is less abrupt than the stalls of earlier SNLF airfoils, which meets the design objective. The constraint on the pitching moment has been satisfied. Comparisons of the theoretical and experimental results show reasonably good agreement overall, given the complexity of the configuration.
UR - https://www.scopus.com/pages/publications/85192176253
UR - https://www.scopus.com/pages/publications/85192176253#tab=citedBy
U2 - 10.2514/6.2023-4313
DO - 10.2514/6.2023-4313
M3 - Conference contribution
AN - SCOPUS:85192176253
SN - 9781624107047
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
Y2 - 12 June 2023 through 16 June 2023
ER -