Aug 17, 2012 design of a pulsefacility nozzle using the rotational method of characteristics richard l. Since the length of nozzle with ideal design is too long to meet the trim requirements of integrated airbreathing hypersonic vehicles, it is necessary to design a truncated nozzle to provide excellent aerodynamic performance. Matrix solution cramercramer ss rule v y dv u x dy dx u a v a uv a 0 0. An interactive computer program using moc has been developed to allow.
Forget that it was designed using method of characteristics. The method allows for the nozzle boundary to be formed through a full method of characteristics solution. The shadow method was used with hsp and the matlab 2016a software mathworks co. A series solution of the nonlinear wave equation was used, only the leading terms in the series being retained in the design proper. Schematic of supersonic nozzle design above centerline by the method of characteristics. Apr, 2018 we show you how to design your own solid rocket nozzle using microsoft excel and fusion 360.
It is my guess that these software are used by big rocket companies and are not available for the general population. The code presented here was used to develop nozzle geometry for a supersonic wind tunnel, which has been fabricated, tested, and verified. Of the direct design techniques, the method of characteristics is the most frequently utilized technique for the purpose of nozzle contour design. This respository contains code to design a rocket nozzle using the method of characteristics moc. The contour formed allows for a smooth throat, shock free nozzle. Hi, as the title says, i am looking to design a gradual expansion nozzle by the method of characteristics. Applied physics laboratory rtdctps48 i laurel md 207236099 y 2d and 3d method of characteristic tools for complex nozzle development final report tharen rice june 3 0,2003 prepared under grant no. Solid fog nozzle velocity tapered columns larger solid fog, mist particles of. Os fc jt s xrs n 03 7 v, 305 washinc3t0n jtme 1918 m2 r. Design of a supersonic nozzle using method of characteristics. In this paper, a method based on the theory of characteristics is presented for two dimensional,supersonic nozzle design. Schematic of supersonic nozzle design by the method of characteristics. I found the following sketch in the andersons book where the mathematical expressions giving such a nozzle is missing.
The minimum length nozzle routine performs a minimum length nozzle mln design using the method of characteristics. An interactive method of characteristics java applet to design and analyze supersonic aircraft nozzles thomas j. Cfd simulation has been carried out for supersonic nozzle flow with exit mach number of 3 and flow characteristics studied using commercial software fluent. A nozzle design which does not directly employ the mathematical method of characteristics was evolved by friedrichs 1 o 1944. We present below the 1d model of gas flow in nozzles. It is used by academics as well as industry professionals to design rocket engine. We are making it available for beta testing among the nozzle team members. The method proposed here results in a more practical approach to obtaining an optimum nozzle shape when the nozzle is an integral part of a system to be designed. Ill discuss the materials i plan to use and my method of cooling in later posts, and in this post i will cover the basic design and geometry of the combustion chamber and nozzle. Apr 16, 2018 classification and characteristics of spray nozzle design. Due to the multidimensionality of the converging subsonic flow, the sonic line is gently curved. The solution of flow problems using the method of characteristics can be simplified by dividing the flow into regions of uniform flow with no waves, simple waves where straight waves belonging to one family of characteristics are present and complex waves where curved waves belonging to both. Rocket engine design with matlab and solidworks method.
The nozzle accelerates the combustion products to 17,000 feet per second at the nozzle exit, generating 470,000 pounds of thrust at vacuum. In the method of characteristics moc for the supersonic. Solid nozzle dust mainly dominated hollow nozzle dust barrier. As a special case, the method calculates an optimum nozzle contour for a fixed end point. Jan 16, 2009 a solve for the nozzle exit area that produces the max amount of thrust. Automated nozzle design through axissymmetric method of. The design and computational validation of a mach 3 wind. I use this software to simulate 2 dimensional planar nozzles. Design, analysis, and simulation of rocket propulsion system. This thesis presents a program that the user chooses input parameters pertinent to design a rocket nozzle and runs calculations that are then used to create a 3d model and to perform cfd analysis. The architecture of the ndarc code accommodates configuration flexibility, a hierarchy of models, and ultimately. The code presented here was used to develop nozzle geometry for a supersonic wind tunnel, which has.
A complete and robust approach to axisymmetric method of. If possible, the computer program generates a nozzle contour which produces supersonic, shockfree, uniform. An interactive method of characteristics java applet to. This algorithm uses the method of characteristics moc which is a very popular tool to design a rocket engine. As you know, the input of such method is the gamma cpcv, the desired mach number at outlet and the number of characteristic lines. How to design a gradual expansion nozzle by the method of. Benson1 nasa glenn research center, cleveland, ohio, 445 the method of characteristics moc is a classic technique for designing supersonic nozzles. This development allows the process for designing rocket nozzles to be automated, fa. Spray characteristics can also be manipulated by special fluid control method or special nozzle design, which is capable of manipulating the droplet size by controlling the secondary flow rate in the nozzle hole.
Minimum length rocket nozzle using the method of characteristics. How to design a bell nozzle from scratch closed ask question asked 2 years. The method of characteristics is a graphical solution of a flowfield, and it was first developed by ludwig prandtl and adolf busemann in 1929 4. The 2d nozzle design tool can quickly solve for an inviscid nozzle contour for various tpes of nozzles and flow inputs. Employs inviscid, 2d method of characteristics for rectangular crosssections to develop geometry for the diverging section of a supersonic nozzle. The innovation is a computer program which can be used to design twodimensional or axisymmetric nozzles having uniform or nonuniform mach number andor flow angle supersonic inflow. Full text of 2d and 3d method of characteristic tools for. Approach to axisymmetric method of characteristics for nozzle design. The second half of the project has also investigated the reliability and accuracy of the method of characteristics as a nozzle design tool. For more realistic design, beyond this simple model, a 2d or axisymmetric analysis by the method of characteristics and boundary layer effects should follow, to be completed with a full 3d nozzleflow analysis by cfd. Either the nozzle length or the nozzle area ratio may be specified. Method of characteristics design tool for nozzle contour. This is a numerical method, but the merit is that the method itself determines the grid or mesh it requires.
Design of a supersonic nozzle using method of characteristics written by md akhtar khan, sanjay kumar sardiwal, m. Design of a pulsefacility nozzle using the rotational method of characteristics richard l. The geometry is obtained by method of characteristics. A minimum length nozzle has the smallest possible throattoexit length that is still capable of maintaining uniform supersonic flow at the exit. However, after running the code, it seems that the output points and plot show the variation of area ratio aa along the nozzle length. Software for nozzle design i was wondering if there are any software available for rocket design or nozzle design.
Because the last one percent of ssme thrust at a fixed mass flow rate translates to about 5,000 pounds of shuttle payload, high priority was placed on nozzle design and performance. Moc nozzle is a simulator that performs a method of characteristics analysis of several different nozzle problems. Calculates a supersonic exhaust nozzle contour that gives maximum thrust for its length. My understanding was that the method should provide the nozzle contour, hence the code must output the coordinates of points along the nozzle contour. Rocket engine design with matlab and solidworks method of. Nozzle design optimization by methodofcharacteristics. Sai sharath published on 201030 download full article with reference data and citations. In this instructable i will introduce one method of making nozzles. Nag32460, design of exhaust nozzle for the rbcc gtx concept, with the nasa glenn research. Full text of supersonic nozzle design see other formats o vo li i co ro go 3 j national advisory committee for aeronautics technical note no. Combustion chamber and nozzle design ad astra per aspera. I was curious enough to see if this was still in use. It can then determinine the interactions between these three flow fields.
Method of characteristics supersonic nozzle design. Experimental high power rocketry is an extreme sport which offers makers a variety of opportunities to utilize their skills, obtain new skills, and explore. Supersonic nozzle design tool file exchange matlab central. The design is done using method of characteristics moc. I will be making a gui for this in the near future. Facility nozzle using the rotational method of characteristics. For now, the user can change values in the inputs section in the main file. The program can calculate the length of the conical section needed in order to achieve the desired mach number within the limits of the curvature provided.
Design of a supersonic nozzle cranfield university. Threedimensional flow breakup characteristics of a. When i tried simulating a nozzle using a chamber temperature of t3126. The jet surface oscillated, and sinuous waves were observed along the liquid jet. A generalized method for the design of optimum rocket nozzles. Nov 23, 2018 if youre a student in mechanical or aerospace engineering, this tutorial will teach you how to design a custom rocket engine nozzle in a programming language matlab and create a cad model of it. Modeling a sprinkler system or a system with nozzles there are several ways to model a sprinkler system or a system with nozzles in pipeflo professional.
We show you how to design your own solid rocket nozzle using microsoft excel and fusion 360. Ndarc software is an aircraft system analysis tool that supports both conceptual design efforts and technology impact assessments of rotorcraft that meet specified requirements. For simplicity, it is assumed that the sonic line is straight line. Threedimensional flow breakup characteristics of a circular. Modeling a spray nozzle engineered software knowledge base. It uses the classic method of characteristics moc technique to design a jet nozzle and analzye the internal flow field, the plume, and the external flow near the nozzle exit. The optimization method uses the calculus of variations for an ideal gas, constant gamma expansion. In the present study, an axisymmetric minimum length nozzle was firstly designed using method of characteristics. Full text of supersonic nozzle design internet archive. You are asking why the 1d and real flow is different. The method of characteristics is a very convenient tool to calculate isentropic portions within a supersonic flows. Also the method of characteristics is normally used only to design the diverging part of the nozzle.
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