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This problem will be treated in detail in Part II. In this chapter the answer to the question will be limited to two aspects: o from the point of view investigated by E. G. S. Roslyakov in their work: "Main Prtnciples of Choosing a Jet Engine Nozzle". Both works were recently published and are of great importance. In two new papers NASA scientists emphasize the need for design criteria, design procedures, and design philosophy (COOPER &SCHEER 1988 and DAVIS &DIXON 1988). 42). A first instructive example has been offered by the study on air-augmented rockets based on a small N2 H4 /N 2 04 motor.

S) in Appendix 1 and causes -ERROR 1-. 2 this relationship is shown graphically. 4. 12) - is the cause for the previously mentioned 'pressure drop' in ~ , as opposed to PF. 2). With J-2 type engines having relatively low a-values, one has to deal with pressure drops in the combustion chamber nearly 20% lower than the feed pressure PF - a result that usually is not taken into consideration. One should note that the gas velocities in f and ~ practically coincide in a combustion chamber with a uniform section.

AT =m/(fATPE) I fct. of a,1t =I = via = me = aATPCv e = mC . = mC = sF sF ("ERROR 2") sF ("ERROR 3") ~V2 h « CONSTRAINTS Mach number M mass flow rate MF m « . ," ambient press. pU thrust S Table 4 z z given definition Relationships for calculating the properties of state - considering the set of constraints; (Eq. = equation, fct. = function). 3 Sequence of States * 'Flame' and 'Fluid' States In state £ the system is established for the following process by pressure PF and temperature TF . 15 Since the value vF is completely unimportant for the energy conversion of interest in here, vF can simply be given the value zero in calculating TF.

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