CFD Analysis Results on NEXST-1 Shinkyu Jeong and Takashi Misaka Institute of Fluid Science, Tohoku University, Sendai, Miyagi, 980-8577, JAPAN ABSTRACT In this study, flow computations were performed on the NEXST-1 (National EXperiment Supersonic Transport) with unstructured mesh solver. Two different meshes and two different turbulence models were used. The computational results were compared with NEXST-1’s flight data. As a whole, the computational result showed a good agreement with flight data, except the pressure distribution on the lower surface in _sweep cases. Introduction Japan Aerospace eXploration Agency (JAXA, formerly National Aerospace Laboratory, NAL) started a scaled supersonic experimental aircraft program, called NEXST (National Experimental Supersonic Transport) [1] in 1996 in order to establish advanced design technology, especially based on CFD, for a next generational supersonic civil transport. To prove the developed design technologies, the program included two types of experimental aircraft: un-manned non-powered (NEXST-1) and un-manned jet-powered (NEXST-2). On 10 October 2005 at the Woomera test range, JAXA performed the NEXST-1 flight test successfully. In this study, CFD analysis was conducted on the NEXST-1 to compare the CFD result with the flight test data. The result showed that the result of CFD corresponds to the flight test data except the pressure distribution on lower surface in _sweep cases. Flow Solver In this study, TAS (Tohoku University Aerodynamic Simulation) Codes [2] developed by Nakahashi was used for mesh generation and flow calculation. This code is based on an unstructured mesh system and consists of TAS_MESH and TAS_FLOW. TAS_MESH is a mesh generator with graphical user interface (GUI) tools [3-6]. It generates triangular surface mesh with the advancing front method [3, 4] and tetrahedral volume mesh with Delaunay tetrahedral method [5]. It also generates hybrid volume mesh composed of tetrahedrons, prisms, and pyramids for viscous flows with high Reynolds number [6]. In TAS_FLOW, Navier-Stokes equations are solved on the unstructured mesh by using a cell-vertex finite volume method. HLLEW (Harten-Lax-van Leer-Einfeldt-Wada) method [7] is used for the numerical flux calculations. Second-order spatial accuracy is realized by a linear reconstruction of the primitive variables. This document is provided by JAXA.