Fast prediction method for multi-batch aerodynamic data of hypersonic vehicle

Abstract

The invention discloses a quick prediction method of the multi-batch aerodynamic data of a hypersonic flight vehicle. A complex multiregion grid is subjected to sectional calculation, two files, which are independently a flow field information storage file and a cache file, are distributed to each grid block, flow field information in the sectional calculation is stored in the cache file, and meanwhile, an aerodynamic force integral file is created. If the sectional calculation is successful, the cache file information is transferred to the flow field information storage file to which each block belongs, the current-section aerodynamic force data is written into the aerodynamic force integral file, the flow field information of the last section of the current section is stored in a sectional information transfer file so as to bring convenience for a next section to read to start calculation; and if the sectional calculation fails, the cache file information is abandoned, a calculation parameter is regulated, the flow field information of the last section of a previous section is read, and the calculation of the current section is restarted. When a tail configuration is changed, a sectional line can be arranged on a configuration change position, a calculation result before the sectional line can be reused, recalculation is not required, and the calculation after the sectional line can regulate a grid at will according to the configuration change.

Description

technical field [0001] The invention relates to a fast prediction method for multiple batches of aerodynamic data of a hypersonic aircraft. Background technique [0002] The PNS or Euler equation space propulsion program can be used to efficiently and quickly obtain the aerodynamic performance of a supersonic vehicle, and is an ideal rapid evaluation tool in the early stage of vehicle design. When evaluating the aerodynamic performance of an aircraft, it is often necessary to obtain a large amount of aerodynamic data with different rudder deflection, or to keep the shape of the front body unchanged and only change the aerodynamic layout of the tail. If the flow field data of the precursor can be reused and only the flow field of the changed part of the tail shape can be calculated, the efficiency of multi-batch aerodynamic prediction will be greatly improved. The PNS space propulsion method can theoretically meet the above requirements, but it is poorly adaptable to complex...

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Problems solved by technology

The PNS space propulsion method can theoretically meet the above requirements, but it is poorly adaptable to complex multi-block grids. figure 1 The multi-block grid calculation shown cannot be conveniently calculated figure 2 grid shown

The spatial propulsion method can only obtain one layer of flow data in one calculation step, but cannot obtain the flow field information of the entire grid. The main problem brought about by this is that if the calculation collapses when calculating a certain layer of data, even if the upstream of the collapsed layer If the data is valid, the calculation must be restarted from the head of the aircraft, which increases the amount of calculation for no reason

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