ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Microaerodynamic experiment and computation of near space high speed vehicles
Received date: 2022-02-24
Revised date: 2022-03-09
Accepted date: 2022-03-25
Online published: 2022-04-06
Supported by
National Natural Science Foundation of China(11902313)
Structural design and static calibration were developed for accurate measurement of micro aerodynamic wind tunnel tests in near space atmospheric environments. Then，the simple blunt cone model was used for the micro-aerodynamic force experiment verification，and the complex shape of the triangular lift body was adopted to explore the ability to measure the micro-aerodynamic force in thinner atmospheric environments. The results show that the repeatability accuracy of aerodynamic data of each balance load unit is better than 4.8% in the three times of the blunt cone shape verification test. In the exploration test，the triangular lift body adopts the lowest density state the wind tunnel can currently achieve，and the test results show that the micro-force balance performs well in the limit state. The numerical simulation results，compared with the experimental results，show that the aerodynamic forces of the blunt cone and the delta wing lift body are in good agreement with those measured by microbalance； for the simple blunt cone，the compressive resistance of the blunt surface is significantly higher than the frictional resistance under its test conditions，while the surface friction ratio of the complex delta wing body is equal to the piezoresistive，with much thinner test conditions.
Key words： near space; wind tunnel test; microbalance; aerodynamic force; high speed vehicles
Junhong LI , Xuhong JIN , Chunfeng LIU , Wenbo MIAO , Xiaoli CHENG . Microaerodynamic experiment and computation of near space high speed vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(6) : 127072 -127072 . DOI: 10.7527/S1000-6893.2022.27072
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