IMECH-IR  > 高温气体动力学国家重点实验室
AERODYNAMIC DRAG MEASUREMENT IN A HIGH-ENTHALPY SHOCK TUNNEL
Wang YP(汪运鹏); Jiang ZL(姜宗林); Teng HH(滕宏辉)
Source PublicationPROCEEDINGS OF THE ASME FLUIDS ENGINEERING DIVISION SUMMER MEETING, 2018, VOL 2
2018
PagesV002T14A001
Conference NameASME Fluids Engineering Division Summer Meeting (FEDSM2018)
Conference DateJUL 15-20, 2018
Conference PlaceMontreal, CANADA
AbstractShock tunnels create very high temperature and pressure in the nozzle plenum and flight velocities up to Mach 20 can be simulated for aerodynamic testing of chemically reacting flows. However, this application is limited due to milliseconds of its test duration (generally 500 mu s-20 ms). For the force test in the conventional hypersonic shock tunnel, because of the instantaneous flowfield and the short test time [1-4], the mechanical vibration of the model-balance-support (MBS) system occurs and cannot be damped during a shock tunnel run. The inertial forces lead to low frequency vibrations of the model and its motion cannot be addressed through digital filtering. This implies restriction on the model's size and mass as its natural frequencies are inversely proportional the length scale of the model. As to the MBS system, sometimes, the lowest natural frequency of 1 kHz is required for the test time of typically 5 ms in order to get better measurement results [2]. The higher the natural frequencies, the better the justification for the neglected acceleration compensation. However, that is very harsh conditions to design a high stiffness MBS structure, particularly a drag balance. Therefore, it is very hard to carried out the aerodynamic force test using traditional wind tunnel balances in the shock tunnel, though its test flow state with the high-enthalpy is closer to the real flight condition. Based on above issues, many balance researchers proposed several special balances to measure aerodynamic forces in the impulse facilities with high-enthalpy, that is, accelerometer balance [5-7], stress-wave force balance [8-10], free-flight measurement technique [11-16], and compensated balance [17]. Owing to the very short test time, however, the mature technology was undeveloped for the force measurements in the shock tunnel with short test duration. Based on the strain-gauge sensor's higher accuracy and sensitivity, Wang et al. [18, 19] designed a very high-stiffness pulse-type balance using the strain gauge sensor and successfully carried out a series of force tests in a large-scale shock tunnel, which has long test duration of more than 100 ms. In this study, a pulse-type strain-gauge balance (PSGB) was used for measuring the drag of a cone in a short-duration high enthalpy impulse facility, JF10. The test duration is approximately 3-7 ms. Force tests were conducted for a large-scale cone with a length of 375 mm in the JF 10 shock tunnel. The finite element method (FEM) was employed for the analysis of the vibrational characteristics of the MBS structure to ensure a sufficient number of cycles, particularly for the axial element structure, during 4 ms test duration (in the present flow conditions). The PSGB used in the test shows good performance, wherein the frequency of the MBS system increases because of its stiff construction. The test results were analyzed to see the effect of high temperature gas by comparing with the data obtained in nearly ten wind tunnels.
WOS IDWOS:000457516200051
Funding OrganizationNational Natural Science Foundation of China [11672357]
ISBN978-0-7918-5156-2
Indexed ByCPCI-S ; EI
Language英语
Citation statistics
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/78566
Collection高温气体动力学国家重点实验室
Affiliation1.{Wang, Yunpeng、Jiang, Zonglin} Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
2.{Wang, Yunpeng、Jiang, Zonglin} Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
3.{Teng, Honghui} Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
Recommended Citation
GB/T 7714
Wang YP,Jiang ZL,Teng HH. AERODYNAMIC DRAG MEASUREMENT IN A HIGH-ENTHALPY SHOCK TUNNEL[C],2018:V002T14A001.
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