TY - GEN
T1 - A Near-field CFD Method for Wave Drag Decomposition
AU - Hart, Pierce L.
AU - Vogel, Anja
AU - Bradley, Freya
AU - Schmitz, Sven
N1 - Publisher Copyright:
© 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2025
Y1 - 2025
N2 - Partial-Pressure Fields have shown the capabilities to decompose drag into relevant sources. In transonic flow, they may be used in combination with classical far-field integrals to derive wave drag. The original method presented (Hart, P. L., and Schmitz, S., “Drag Decomposition using Partial-Pressure Fields: ONERA M6 Wing,” AIAA Journal, Vol. 60, No. 5, 2022 pp. 2941–2951) is reliant on both an accurate near-field and far-field grids, making it less advantageous than classical far-field wave drag integrals. In the present work, a new method was developed to predict wave drag solely using a near-field analysis. The method utilizes both partial-pressure fields and lifting-line theory. The theory behind this method is demonstrated, and applied to a total of four cases on the ONERA M6 wing, including three transonic cases, one of which is a special zero lift case, and a subsonic compressible case. A comparison of resulting wave drag results is conducted between the new method, classical far-field decompositions, and the original hybrid partial-pressure field method.
AB - Partial-Pressure Fields have shown the capabilities to decompose drag into relevant sources. In transonic flow, they may be used in combination with classical far-field integrals to derive wave drag. The original method presented (Hart, P. L., and Schmitz, S., “Drag Decomposition using Partial-Pressure Fields: ONERA M6 Wing,” AIAA Journal, Vol. 60, No. 5, 2022 pp. 2941–2951) is reliant on both an accurate near-field and far-field grids, making it less advantageous than classical far-field wave drag integrals. In the present work, a new method was developed to predict wave drag solely using a near-field analysis. The method utilizes both partial-pressure fields and lifting-line theory. The theory behind this method is demonstrated, and applied to a total of four cases on the ONERA M6 wing, including three transonic cases, one of which is a special zero lift case, and a subsonic compressible case. A comparison of resulting wave drag results is conducted between the new method, classical far-field decompositions, and the original hybrid partial-pressure field method.
UR - https://www.scopus.com/pages/publications/105018039145
UR - https://www.scopus.com/inward/citedby.url?scp=105018039145&partnerID=8YFLogxK
U2 - 10.2514/6.2025-3430
DO - 10.2514/6.2025-3430
M3 - Conference contribution
AN - SCOPUS:105018039145
SN - 9781624107382
T3 - AIAA Aviation Forum and ASCEND, 2025
BT - AIAA AVIATION FORUM AND ASCEND, 2025
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION FORUM AND ASCEND, 2025
Y2 - 21 July 2025 through 25 July 2025
ER -