TY - GEN
T1 - Drag Decomposition Using Partial-Pressure Fields – ONERA M6 Wing
AU - Hart, Pierce L.
AU - Schmitz, Sven
N1 - Funding Information:
This material covered is based upon work supported by the National Aeronautics and Space Administration (NASA) under cooperative agreement award number NNX17AJ95A. The work was performed under the University Leadership Initiative (ULI) at the Pennsylvania State University for the “Advanced Aerodynamic Design Center for Ultra-Efficient Commercial Vehicles”
Funding Information:
This material covered is based upon work supported by the National Aeronautics and Space Administration (NASA) under cooperative agreement award number NNX17AJ95A. The work was performed under the University Leadership Initiative (ULI) at the Pennsylvania State University for the ?Advanced Aerodynamic Design Center for Ultra-Efficient Commercial Vehicles?
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Drag decomposition has classically been undertaken using a farfield approach both from a wind tunnel testing and computational fluid dynamics standpoint. It has been suggested ("Drag Decomposition Using Partial-Pressure Fields in the Compressible Navier-Stokes Equa-tions", AIAA Journal, Vol.57, No.5, 2019, pp. 2030-2038) that a decomposition of static pressure into partial pressure fields can allow one to decompose a computational fluids dynamics solution in the nearfield. This paper covers the implementation process of partial pressure fields on the ONERA M6 wing at conditions relevant to commercial transport aircraft. Relations between partial pressure field decomposition, the classical farfield theory, and physical drag sources are discussed. It is demonstrated that the nearfield partial pressure field decomposition is equivalent to classical farfield analysis. In transonic flow, a new method to compute wave drag using a combination of both partial pressure fields and the farfield method is demonstrated.
AB - Drag decomposition has classically been undertaken using a farfield approach both from a wind tunnel testing and computational fluid dynamics standpoint. It has been suggested ("Drag Decomposition Using Partial-Pressure Fields in the Compressible Navier-Stokes Equa-tions", AIAA Journal, Vol.57, No.5, 2019, pp. 2030-2038) that a decomposition of static pressure into partial pressure fields can allow one to decompose a computational fluids dynamics solution in the nearfield. This paper covers the implementation process of partial pressure fields on the ONERA M6 wing at conditions relevant to commercial transport aircraft. Relations between partial pressure field decomposition, the classical farfield theory, and physical drag sources are discussed. It is demonstrated that the nearfield partial pressure field decomposition is equivalent to classical farfield analysis. In transonic flow, a new method to compute wave drag using a combination of both partial pressure fields and the farfield method is demonstrated.
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U2 - 10.2514/6.2021-2555
DO - 10.2514/6.2021-2555
M3 - Conference contribution
AN - SCOPUS:85123882663
SN - 9781624106101
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
Y2 - 2 August 2021 through 6 August 2021
ER -