Abstract
The flow in a low-powered arc gas heater combined with a supersonic nozzle of throat diameter less than 1 mm is quite complicated and difficult to describe in quantitative detail. Experiments on arc-heated supersonic jet thrusters of monatomic gases argon and helium have been carried out and their performance measured. The flow characteristics are analyzed with the help of numerical simulation. Results show that the viscous effect is the most important factor causing the large difference between ideal and real performance. A large outer section of the exit flow is slow-moving. This is especially pronounced in helium, where 70 % of the exit area of the nozzle might be in subsonic flow. Friction forces can be much larger than the net thrust, reaching several times higher in helium, resulting in very low efficiencies. Other factors causing the differences between ideal and real flow include: complex flow in the throat region, electric arc extending to the nozzle expansion section, heat transfer to the inlet gas and from the hot plasma, and environmental pressure in the vacuum chamber. It is recognized that the ordinary concepts of supersonic nozzle flow must be greatly modified when dealing with such complicated situations. The general concepts presented in this paper could be helpful in guiding the design and operation of this equipment.
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Abbreviations
- \(A^{*}\) :
-
Throat area, \(\hbox {m}^{2}\)
- C :
-
Nozzle flow coefficient
- \(c_\mathrm{p}\) :
-
Specific heat, \(\hbox {J}/(\hbox {kg}~\hbox {K})\)
- F :
-
Thrust, N
- \(F_{0}\) :
-
Cold thrust, N
- \(h_{0}\) :
-
Total enthalpy, J/kg
- I :
-
Arc current, A
- \(I_\mathrm{sp}\) :
-
Specific impulse, m/s (or s)
- \(\dot{m}\) :
-
Mass flow rate, kg/s
- Ma :
-
Mach number
- \(p_{0}\) :
-
Inlet pressure, Pa
- \(p_\mathrm{vc}\) :
-
Vacuum chamber pressure, Pa
- r :
-
Radial distance from axis, m
- R :
-
Gas constant, \(\hbox {J}/(\hbox {kg}~\hbox {K})\)
- Re :
-
Reynolds number
- \(T_{0}\) :
-
Total temperature, K
- u :
-
Axial velocity, m/s
- U :
-
Arc voltage, V
- z :
-
Axial distance from the inlet plane, m
- \(V_\mathrm{e}\) :
-
Exhaust velocity, m/s
- \(W_\mathrm{sp}\) :
-
Specific power, J/kg
- \(\gamma \) :
-
Specific heat ratio
- \(\eta _\mathrm{Isp}\) :
-
Specific impulse efficiency
- \(\eta _\mathrm{T}\) :
-
Thrust efficiency
- \(\rho \) :
-
Mass density, \(\hbox {kg/m}^{3}\)
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Acknowledgments
This work was supported by the National Natural Science Foundation of China (Grants 50836007, 11475239, 10921062, and 11275021).
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Wu, CK., Pan, WX., Meng, X. et al. Mechanisms for non-ideal flow in low-power arc-heated supersonic nozzles. Acta Mech. Sin. 31, 500–511 (2015). https://doi.org/10.1007/s10409-015-0430-9
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DOI: https://doi.org/10.1007/s10409-015-0430-9