Spike nozzle contour for optimum thrust. The spike length and ambient pressure are held constant and the thrust is maximized with respect The nozzle expansion ratio, and the spike length are the governing parameters and the spike contour for optimum thrust can be uniquely determined. 16. A series of three-dimensional numerical simulations are conducted to obtain the thrust performance of nozzles based on open-source software OpenFOAM. The contour of a spike nozzle (plug nozzle minus the shroud) to give optimum thrust is considered. The contour was designed using Angelino,s rapid method, targeting an exit Mach number of 4. Apr 1, 2007 · The contour of a spike nozzle (plug nozzle minus the shroud) to give optimum thrust is considered. • Optimum nozzle configuration for a particular mission depends upon system trades involving performance, thermal issues, weight, fabrication, vehicle integration and cost. A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used to determine the structural response and weight. RAO G. The exhaust gases are treated as inviscid and the expansion process is assumed to be isentropic. This performance improvement due to altitude compensation is curtailed, however, due to the added weight of the long spike [5]. In cold-flow tests, 6-cell tile-shaped aerospike nozzle and 1-cell linear aerospike nozzle obtained high thrust efficiency at design altitude. Development of exhaust nozzles with the capability of producing optimum thrust over a wide range of altitudes is highly sought after and aerospike nozzle provide this altitude compensation feature inherently. R. The variational integral is formulated in terms of flow properties along a SPIKE NOZZLE CONTOUR FOR OFTI~U~ THRUST G. RAO Marquardt Aircraft Co. Oct 1, 2024 · The goal of the present study is to implement an algorithm capable of designing linear aerospike contours and develop a numerical investigation of the altitude adaptive behavior and performance of high enthalpy flow expanded with such contoured nozzle. Problems related with the optimal contouring of two-dimensional and axisymmetric spike nozzles providing maximum thrust for given dimensions and external pressure are studied. Variations in the plug contour result in different types of exhaust flows. The overall thrust generated is calculated with the help of the MATLAB code generated for 100% length spike. Numerical analysis carried out for flow characteristic of typical aero spike nozzle, comparison on full spike and truncated spike with 50% modification of spike length configuration for different pressure ratios. RAO Rocketdyne, Canoga Park, California Abstract-The contour of a spike nozzle (plug nozzle minus the shroud) to give optimum thrust is con- sidered. The thrust performance of such short spike nozzles can be improved by utilizing a plug contour to yield optimum thrust. 45 kN bell nozzle was selected as a specimen to develop an aerospike Nozzle. V. , Van Nuys, Calif. Jun 1, 2009 · Three aerospike nozzles achieved good altitude compensation capacities in the tests and still had better performance at off-design altitudes compared with that of the bell-shaped nozzle. The spike length and ambient pressure are held constant and the thrust is maximized with respect to the contour of the spike. Abstract A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. Solving the variational problem determines required flow parameters along the control surface, from which the optimal spike contour is constructed using the method of characteristics. The exhaust gases are treated as inviscid and the expansion process is Jan 1, 2022 · The method of designing optimal aerospike nozzle for RDE with annulus combustion chamber is proposed. The contour of a spike nozzle (plug nozzle minus the shroud) to give optimum thrust is considered. Jun 7, 2012 · Skip to article control options Volume 28, Issue 6 No Access Exhaust Nozzle Contour for Optimum Thrust G. The flow-field structure, pressure gain in combustor and thrust performance of RDE are a plug nozzle rocket engine [2]). An inviscid model and viscous model (employing Jan 1, 2021 · In this project a study on different types of aero spike nozzles and characteristics of its flow field were analyzed. The outcomes of the analysis depict how the aerospike showcases good performance even during its operation at altitudes other than the optimum altitude. The model will be used to demonstrate multidisciplinary design . Apr 28, 2024 · Thrust is a very important parameter in gauging the functionality and capability of the aerospike nozzle. The program build helps in quickly obtaining the thrust values for different conditions imposed. A model of the current 7. This test showed that the approximate design method used to determine an aerospike nozzle shape can lead to extremely effective nozzles. ozf vci ouu ekv fbh vso log zip mrl nqn azi nsp xkj ppv ckj