Altitude-adapted nozzles are designed to facilitate flow adaptation during rocket ascent in the atmosphere, without requiring mechanical activation. As a consequence, the performance of the nozzle is significantly improved. The aim of this study is to develop a new profile of axisymmetric supersonic nozzles adapted at altitude (Dual Bell Nozzle with Central Body), which is characterized by an E-D nozzle as a basic profile. The performances obtained for this nozzle (E-D Nozzle) are then compared to those of a Plug nozzle. The E-D nozzle shows significant performance advantages over the Plug nozzle, including a 13.02% increase in thrust, knowing that the length of the E-D nozzle is half that of the Plug nozzle under the same design conditions. Finally, viscous calculations using the k-ω SST turbulence model were conducted to compare the performance of the dual bell nozzle with central body (DBNCB) and the E-D nozzle with the same cross-sectional ratio, and to assess the impact of nozzle pressure ratio (NPR) variations on the operation mode of the DBNCB. The results obtained show that the DBNCB offers the best performance in most phases of flight.
The popular problem for space propulsion researchers is fuel consumption, which is associated with the weight of the vehicle, and from there, any weight gain leads to fuel gain. We studied the weight reduction of the supersonic nozzle of a space vehicle without any significant effect on the thrust. We first created the contour of the plug nozzle using the method of characteristics, According to the analysis of the pressure profile on the wall of the Plug nozzle we notice that the pressure first decreases very quickly in the initial expansion area, at the level of the col, and continuously decreases in the divergent part before it stabilizes at the tip of the nozzle, approaching the atmospheric pressure value at the outlet of the nozzle. So the last part of the divergent is substantially constant. Therefore, if truncated in this part, this does not lead to a significant decrease in the maximum thrust. In this study, we truncated an ideal supersonic plug nozzle into four different points and we have four Plug nozzles of different lengths and maximum thrust as well. We then choose the Plug nozzle which has an optimized thrust/weight ratio. Finally, we have a Plug nozzle with significant weight gain and a slight maximum thrust loss compared to the ideal plug nozzle.
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