Computational Fluid Dynamics (CFD) is an important branch of fluid mechanics, and will continue to play great roles on the design of aerospace vehicles, exploration of new concept vehicles and new aerodynamic technology. This paper will present the progress of CFD from point of view of engineering application in recent years at CARDC, including the software integration, grid technique, speeding up of convergence, unsteady fluid computation etc., and also give some engineering application examples of CFD at CARDC. computational fluid dynamics, aircraft, unsteady flowThe development of computer plays an important role in the modern science and technology. The computer brings about computational fluid dynamics (CFD), computational structure mechanics, computational electromagnetism, etc., which produce great impact on modern aeronautics and astronautics. CFD has now been an essential tool for the aerodynamic design of aeronautic and astronautic vehicles. The Moore Law for computers will keep applicability in the next twenty or thirty years, as physical experts predicted, so in the next thirty years, the computer speed will be increased by million times of the present one [1] . The CFD therefore has a great space for development, and many problems which cannot be solved today due to the limit of the speed of computer, for example, unsteady flow over complete vehicles, large eddy simulations for engineering configurations, etc., could easily get solutions in the next twenty or thirty years. The multidisciplinary optimization (MDO) could be used for the whole design process of real flight vehicles, and people can be more confident to use CFD to explore new idea and new technology in the aerodynamic field. CFD can be used for the extensive selection of configurations with coupling associated disciplines and can make performance of the designed vehicle approach to the limit of physical laws. CFD can also be combined with the wind tunnel closely for correction of wind test data to better fit the real flight situations.As the computer goes faster and faster, and the physical models and algorithms for CFD are being improved year by year, the accuracy, and efficiency and robustness of CFD codes are be-

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Parallel test is an efficient approach for improving test efficiency in the aerospace field. To meet the challenges of implementing multiunit parallel test in practical projects, this paper presented a mixed-integer linear programming (MILP) model for solving the task scheduling problem. A novel sequence-based iterative (SBI) method is proposed to solve the model in reasonable time. The SBI method is composed of an implied sequence finding procedure (ISF) and a sequence-based iterative optimization (SBIO) procedure. The first procedure can reduce the search space by fixing free sequence variables according to the original test flowcharts, and the second procedure can solve the model iteratively in a reasonable amount of time. In addition, two indexes, namely, speed rate and average resource utilization rate, are introduced to evaluate the proposed methods comprehensively. Computational results indicate that the proposed method performs well in real-world test examples, especially for larger examples that cannot be solved by the full-space method. Furthermore, it is proved that the essence of the parallel test is trading space for time.

For increasing understanding of fundamental hypersonic phenomena, the flight test program, named MF-1, is to gather fundamental scientific and engineering data on the physics and technologies critical to future operational hypersonic flight with low-cost flight test platform, which is built on the retrofitted rockets. The MF-1 program is a hypersonic flight test program executed by China Aerodynamic Research and Development Center (CARDC). The MF-1 flight flew in December 2015. The flight focuses primarily on integration of instrumentation on the test vehicle, with application to boundary layer transition and shock interaction experiments. The MF-1 payload consists of a blunted 7°half angle cone, a cylinder and 33° flare configuration. The payload was boosted to Mach 5.32 utilizing a solid-rocket booster without control for the whole flight. The flight was fully successful, and measured transition under supersonic and hypersonic conditions. The heat flux data were given by the three-dimensional thermal identification method to discriminate transition zone. The preliminary analysis shows that the real-time flight data obtained by MF-1 are reliable and can be used to validate the transition predicting model and software. The results show that the existing model is able to predict the transition location of cone at a small angle-of-attack for supersonic or hypersonic flow. This paper describes the MF-1 mission and some general conclusions derived from the experiment.