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the angles and areas known, the geometry of the inlet has been calculated using standard trigonometric relations. 3.3.6 Nozzle A convergent β divergent nozzle lets the flow expand to ambient pressure, which for an isentropic process produces maximum thrust [11]. However, due to skin friction losses and the extra weight and length, a con - di nozzle is only a viable option if the nozzle pressure ratio is greater than about three [15] which tends to be the case for supersonic engines due to the high ram pressure ratio. The thrust loss associated with flow angularity increases sharply at great exhaust angles, therefore the angle of the divergent section should be less than 30 degrees [11]. To account for losses in the nozzle, different coefficients are used, the definitions of these may vary between different manufacturers. In this thesis the thrust coefficient, CV and the angularity coefficient πΆπ are used. CV is defined accordingly to [15]. This coefficient gives the actual thrust from the thrust that could be achieved by an ideal con β di nozzle by accounting for friction and flow non- uniformity. The value of CV has been assumed based on guidelines given in [11]. πΆπ is defined as 0, 5 Β· (1 + cos(πΌ)), where πΌ is the half angle of the divergent section [25]. The area of the nozzle inlet, throat and exit is calculated in the thermodynamic analysis. 3.3.7 Mixer The use of a mixer to combine the hot and cold stream prior to the exhaust has a few advantages compared to using two separate exhausts: a small gain in net thrust and SFC can be achieved, the optimum fan pressure ratio at a constant specific thrust is lower leading to a lower weight and cost for both the fan and the LPT, the jet noise is lower due to the velocity of the mixed stream being significantly lower than the core stream of a separate jets engine. In the decision whether to adopt a mixer these advantages need to be balanced against the disadvantages of the extra weight and cost [11]. For the thrust gain to be maximized the mixing needs to be complete (i.e. a mixer efficiency of 100%), this would require a large and heavy mixer, which in turn would require more thrust [1]. Therefore a compromise between mixer efficiency and thrust gain is necessary. Figure 7 shows the theoretical gross thrust gain by introducing a mixer assuming that: the FPR is at its optimum, the mixing efficiency is at 100% and no pressure loss is accounted for. Figure 7: Theoretical thrust gain due to mixing [11] 26PDF Image | Conceptual Design of a Supersonic Jet Engine
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