CFD Validation for the Supersonic Transport Configuration at Low-Speed and High Alpha Flight Condition

To understand the low speed aerodynamics of the SST, CFD analysis were performed on a JAXA QSST configuration at high alpha flight conditions for which complex vortical flow dominates the overall flow field. The multi segment leading edge flaps and trailing edge flap deployed to optimal angles were installed on the main wing of the QSST. The CFD results were compared with the experimental data at three Reynolds numbers. The overall flow field by the CFD analysis relatively corresponded with the experimental results. However, details of the vortical flow were different between CFD and experimental results. Complex flow fields formed over the wing were influenced by the local vortical flow originated from the flap slits. The flow fields over the main wing depended on the Reynolds number. Furthermore, the flow at the tail plane was influenced by the flow from the main wing, and then the aerodynamics on the tail planes also strongly depended on the Reynolds number.