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, quick progress of data within the box of jet, rocket, nuclear, ion and electrical propulsion has led to many advances worthy to the scholar, engineer and scientist. the aim for delivering this direction is to make to be had to them those contemporary advances in concept and layout. therefore, this direction is prepared into seven components: half 1 advent; half 2 Jet Propulsion; half three Rocket Propulsion; half four Nuclear Propulsion; half five electrical and Ion Propulsion; half 6 concept on Combustion, Detonation and Fluid Injection; half 7 complicated innovations and venture purposes. it truly is written in the sort of manner that it could possibly simply be followed via different universities as a textbook for a one semester senior or graduate direction at the topic. as well as the undersigned who served because the direction 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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Rnal 2 oblique shock. Normal shock:::: 0 External 2 oblique only isentropic supersonic flow supersonic expansion flow Fig. 1-4 Ae A* 1 [ k-1 1) +--Me 2 Me Pe Pe p* Po k+l Tk~ (k ; [e; 1(lJ [ (k;') 1 r: (1-94) 1 ) (1-98) +k-1M2 -- e 2 With Po and AelAt = AeIA* known, both Pe and Me may be solved from Eqs. (1-94) and (1-98). However, Eqs. (1-94) and (1-98) have two solutions: one is the Pc and Me solution just discussed, which gives shock-free subsonic flow in the divergent section of the nozzle, and the other is the Pd andMd solution which gives a shockfree supersonic flow in the divergent section of the nozzle.

In the flow represented by curve h, the normal shock stands at the nozzle exit section and the pressure immediately behind the shock equals Ph' This value of Ph' at which normal shock attaches at the exit section, can be determined from Eqs. (1-94), (1-98), and (1-115). 1[1 MI + ¥ M12J 2A ~ 11) Use M > 1 solution here because it is in front of shock k + 1 2 . (1-94) k+1 [ 1+ G:) G:) = = (k ~ 1) ~~ J k M,2 2 k - 1 MI - - k + 1 k - I (1-98) (1-115) Here there are three unknowns, MI , Pi' Ph' in three equations; therefore, they may be solved.

And static pressure decreases continuously from p* to Pl' When P e is further reduced from Pf to P , the normal shock moves to the right as shown by curve g. In the flow represented by curve h, the normal shock stands at the nozzle exit section and the pressure immediately behind the shock equals Ph' This value of Ph' at which normal shock attaches at the exit section, can be determined from Eqs. (1-94), (1-98), and (1-115). 1[1 MI + ¥ M12J 2A ~ 11) Use M > 1 solution here because it is in front of shock k + 1 2 .

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