Simulations of the NASA Langley 14- by 22-Foot Subsonic Tunnel for the Juncture Flow Experiment

Lee, Henry ; Pulliam, Thomas H ; Rumsey, Christopher L ; Carlson, Jan-Renee

关键词: COMPUTERIZED SIMULATION;    APPLICATIONS PROGRAMS (COMPUTERS);    COMPUTATIONAL FLUID DYNAMICS;    SUBSONIC WIND TUNNELS;    BODY-WING CONFIGURATIONS;    TRAILING EDGES;    SEPARATED FLOW;    VISCOUS FLOW;    WALL FLOW;    TURBULENT FLOW;    CORNER FLOW;    WIND TUNNEL TESTS;    NASA PROGRAMS;   

RP-ID  :  STO-MP-AVT-284-02,ARC-E-DAA-TN52010

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来源: NASA Technical Reports Server

【 摘 要 】

NASA’s Transformational Tools and Technologies Program’s Juncture Flow experiment aims to provide data to improve Computational Fluid Dynamics (CFD) modeling in the juncture flow region. The experiment is planned to provide validation-quality data for CFD that focuses on the separation bubble near the wing-body juncture trailing edge region. Because wind tunnel tests associated with the Juncture Flow project have been designed for the purpose of CFD validation, considerable effort is going into modeling and simulating the wind tunnel. This is not only important because wind tunnel wall effects can play a role in integrated testing uncertainties, but also because the better the boundary conditions are known, the better CFD can accurately represent the experiment. This paper builds on the recent CFD efforts to model the NASA Langley 14- by 22-Foot Subsonic Tunnel. Current best practices in simulating wind tunnels are evaluated. The features of each method, as well as some of their pros and cons, are highlighted. Boundary conditions and modeling techniques currently used by CFD for empty-tunnel simulations are also described. Preliminary CFD studies associated with modeling the Juncture Flow model are summarized, with the intention to determine sensitivities of the flow near the wing-body juncture region of the model to a variety of modeling decisions.