Design Studies for Three-Dimensional Forebody of Hypersonic Vehicle Based on PNS Optimization Procedure
- Paper number
IAC-07-C4.5.02
- Author
Mr. Xu Dajun, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Prof. Guobiao Cai, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Prof. Xu Xu, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Mr. Bing Chen, Beijing University of Aeronautics and Astronautics, China
- Year
2007
- Abstract
The forebody of hypersonic vehicle provides precompressed air to the scramjet engine’s inlets, so the forebody’s geometry greatly influences the propulsion efficiency and the overall performance of a hypersonic vehicle. Propulsion system of hypersonic vehicle demands a high static pressure of the precompressed air, a large inlet air mass flow, and minimized total pressure losses at the inlet entry. Small gradients of all flow parameters and a tolerable distortion across the inlet entry are also required to realize the undisturbed operation of inlets and scramjet engines. The forebody’s shape also influences the external aerodynamic performance, include lift, drag and stability. In order to investigate effects of forebody geometries on inlet entry flow and external aerodynamic performance, a exponent function is chosen to generate a series of three-dimensional forebody’s shape, changing from spatular nose to sharp nose in a continual way. The three-dimensional flowfields around these forebody geometries are calculated by Navier-Stokes (NS) code and parabolized Navier-Stokes (PNS) code. The results of calculations comprise forebody precompression data sets for a flight Mach number at Ma6, angles of attack range between -6 deg and 10 deg, and anlges of yaw range between 0 deg and 6 deg. The results are compared by static and total pressure ratios for the captured stream tubes, inlet entry Mach numbers, inlet air mass ratios, and aerodynamic parameters of forebody. The results and comparisons show different forebody shape serious affect inlet entry condition and aerodynamics performance. Process of calculation validates that PNS code is more efficient than NS code for hypersonic flow, so PNS code can reduce the runtime of optimization design when it is applied in the design process. A PNS-based optimization procedure is constructed and used to design forebody of hypersonic vehicle. The advantage of this procedure is that it optimizes the design of forebody’s shape under a good balance and tradeoff between inlet entry condition and forebody aerodynamics performance.
- Abstract document
- Manuscript document
IAC-07-C4.5.02.pdf (🔒 authorized access only).
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