Jet, Rocket, Nuclear, Ion and Electric Propulsion: Theory by W. H. T. Loh (auth.), W. H. T. Loh (eds.)
By W. H. T. Loh (auth.), W. H. T. Loh (eds.)
During the decade, swift progress of information within the box of jet, rocket, nuclear, ion and electrical propulsion has led to many advances helpful to the coed, engineer and scientist. the aim for supplying this direction is to make to be had to them those contemporary advances in conception and layout. as a result, this direction is geared up into seven components: half 1 creation; half 2 Jet Propulsion; half three Rocket Propulsion; half four Nuclear Propulsion; half five electrical and Ion Propulsion; half 6 idea on Combustion, Detonation and Fluid Injection; half 7 complex recommendations and challenge functions. it truly is written in this sort of means that it may possibly simply be followed by means of different universities as a textbook for a one semester senior or graduate path at the topic. as well as the undersigned who served because the path teacher and wrote bankruptcy I, 2 and three, visitor teachers integrated: DR. G. L. DUGGER who wrote bankruptcy four "Ram-jets and Air-Aug mented Rockets," DR. GEORGE P. SUTTON who wrote bankruptcy five "Rockets and Cooling Methods," DR . . MARTIN SUMMERFIELD who wrote bankruptcy 6 "Solid Propellant Rockets," DR. HOWARD S. SEIFERT who wrote bankruptcy 7 "Hybrid Rockets," DR. CHANDLER C. Ross who wrote bankruptcy eight "Advanced Nuclear Rocket Design," MR. GEORGE H. McLAFFERTY who wrote bankruptcy nine "Gaseous Nuclear Rockets," DR. S. G. FORBES who wrote bankruptcy 10 "Electric and Ion Propul sion," DR. R. H. BODEN who wrote bankruptcy eleven "Ion Propulsion," DR.
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Additional resources for Jet, Rocket, Nuclear, Ion and Electric Propulsion: Theory and Design
Equations (1-116) and (1-117) each represent a curve in the h-s diagram (which is a function of Eqs. (1-6) and (1-52». The former is called the Rayleigh line and the latter the Fanno line. These lines intersect at two points, whose coordinates satisfy both equations and, therefore, correspond to the state of the flow on opposite sides of the shock. Figure 1-1 shows typical forms of these two curves. The Rayleigh and Fanno lines are plotted as follows. When conditions on the upstream side of the shock are given, the constants C L C2, and C3 can be computed.
Curve f indicates that the static pressure across the shock decreases and the Mach number which is supersonic at the left of the shock decreases and becomes subsonic at the right of the shock. Since after the shock Mach number is less than 1, the velocity decreases and static pressure increases in the divergent section behind the shock which is in contrast to the divergent section in front of the shock, where the Mach number increases continuously 42 Jet, Rocket, Nuclear, Ion and Electric Propulsion from unity at the throat to a supersonic Mach number MI.
1-13c), it gives poor diffusion efficiency. Figure I-lad shows the farthest upstream position (at the throat section) for which the flow is still stable. However, a slight disturbance in the flow pattern of Fig. 1-13d will move the shock out of the inlet. Such a diffuser possesses the so-called hysteresis effect. During acceleration, the shock will not be swallowed until the speed Md (Fig. 1-12) is reached. Once swallowed, the shock will not be pushed out upon deceleration until the speed Mb (Point b of Fig.