In order to perform magenetohydrodynamic (MHD) technical experiments, the experimental system needs to meet the following two conditions: one is supersonic or hypersonic flow; the other is that the flow must be conductivity. In this paper, basic composition, design methods, and debugging situation of a supersonic MHD technical experimental system based on shock tunnel are introduced. Mach number Ma=2 supersonic nozzle and testing section are designed; helium is used to drive argon gas, equilibrium contact surface operating mode is used for getting high temperature gas, and the conductive gas is obtained by adding ionization seed K2CO3 powder to the driven section. The following results are obtained: the effective testing time is about 9 ms by adjusting the length of driver section and driven section; the temperature in the 5th zone reaches over 3 500 K; due to short-time running, cooling problem of the nozzle and working section can be ignored; the conductivity of Ma=2 supersonic flow is 40 S/m, the magnetic interaction parameter Q is 0.174 under the conditions of p1=3 kPa, L=0.2 m and B=2.0 T realized by electromagnet, while Q is 0.164 when p1=1 kPa, L=1 m and B=0.5 T using permanent magnet. This experimental system could be used to perform preliminary experimental researches such as MHD flow control, MHD power generation and MHD acceleration.
LI Yiwen, LI Yinghong, ZHANG Bailing, JIN Di, CHEN Feng, ZHU Tao
. Supersonic Magnetohydrodynamic Technical Experimental System Based on Shock Tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(6)
: 1015
-1024
.
DOI: CNKI:11-1929/V.20110427.1600.002
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