ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Delay phenomenon of boundary layer transition according to heating flux identified from flight test
Received date: 2017-03-20
Revised date: 2017-07-18
Online published: 2017-07-18
Supported by
National Key Research and Development Program of China (2016YFA0401200);National Basic Research Program of China (2014CB744100)
This paper presents the results of an analysis of the thermocouple measurements used to infer the heating rates and dynamics of the boundary layer natural transition process during the successful first trajectory flight of China Aerodynamics Research and Development Center space vehicle model.It has been found that the approach used in the analysis of the thermocouple data for ground-based short-term experiments cannot be direct scaled to long time flight conditions.For the flight case,the variation history of temperature along the whole flying trajectory and the local 3D heat transfer between the transducer and near the vehicle structure must be considered.The heating rates on the model surface are also calculated using engineering methods,along with a discussion of the calculated flow properties that correspond to the transition events as identified in the flight data.The present analysis shows that the onset criterion number of transition from turbulent state to completely laminar flow at the place of a measurement point in the ascent stage is greater than that of the transition from the laminar flow to turbulent flow in the descent stage,meaning that there is a delay phenomenon existing in the boundary layer transition process.The results also show that the onset position of boundary layer transition in the flight condition is later than prediction by the criterion established using ground-based data,and the difference may be attributed to noise disturbances in the tunnels which caused early transition on the aft end.Comparison of calculation results and test results shows that for blunted cone shapes,when x/R>50,the flow field and heating rates become closer to the conic flow and flat plate results.The first flight data have verified that the aerothermodynamic engineering methods for hypersonic flows can be also used to predict the heating rates for the cases of Mach number below 5 with a reliable accuracy.
GUO Yijun , ZHOU Yu , XIAO Hanshan , ZHOU Shuguang , QIU Bo , ZENG Lei , LIU Xiao . Delay phenomenon of boundary layer transition according to heating flux identified from flight test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(10) : 121255 -121255 . DOI: 10.7527/S1000-6893.2017.121255
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