![]() ![]() Solves the isentropic flow equations for the flow through a rocket nozzle, a converging-ĭiverging turbine nozzle or a converging turbine nozzle. You can also save your current design to a "Save" file.Īt your next session you can read the "Save" file information back into the You can save your nozzle design and performance The chief advantage of this program is that it can readĪnd write files on your computer. There is an even more powerful version of MOC Nozzle which is available for You can design 2D or axisymmetric ideal nozzles,Įxternal cowl nozzles or plug nozzles, or analyze simple cone or wedge nozzles. InĪny of the modes, you can change design variables including theĭesign Mach number, throat area, plenum total pressure and temperature,Įxternal Mach number, and altitude. Program works in three modes: analysis and design, design with plume into a static flow,Īnd design with plume into a supersonic external flow. Is a simulator that performs a Method of Characteristics analysis of The chief advantage of this program is that it can It runs stand alone and you must have Java installed on your computer to This program is a Java application, not an applet. There is an even more powerful version of the Multiple Shock Wave Simulator which is available for This program also solves the single wedge problem generating an oblique or normal The simulator computes theĪngle, flow turning, and the downstream Mach number.Ī graphic shows the multiple shock intersections and reflections. Shocks or a detached normal shock is generated. Wedges may be located in series or opposite each other.ĭepending on the combination, attached oblique Mach number, wedge angles, and the spacing between the wedges. Solves the flow equations for supersonic flow past multiple wedges. Solves the flow equations for supersonic flow past a cone, as described by the Taylor-Maccoll method. Static and total pressure ratio, the temperature and density ratio, the shockĪngle and the downstream Mach number. Shock or a detached normal shock is generated. Depending on the combination, an attached oblique Solves the flow equations for supersonic flow past a 2D wedge, as described in NACA Report 1135. Specifying any one variable determines the value of all the other variables. To static pressure ratio, critical area ratio, corrected airflow per unit area, Mach number, static to total pressure, temperature, and density ratios, dynamic Solves the isentropic flow equations for a variety of inputs. Altitudes vary from 0 to 250,000 feet and Mach number varies from 0 to 25.Ĭalculations are in English or Metric units. ![]() The standard day atmosphere mathematical model to determine the speed of sound You can download a copy of each program to your computer andĪllows you to specify the altitude and speed (or Mach) of an aircraft and the program uses ![]() If you follow the instructions given below, Will take a little longer to load into your browser. ![]() The science and math behind each problem and someĪdditional instructions on the program operation. You understand the problem and contains only the applet andĪ couple of hyperlinks to additional pages which describe You to a web page which contains a simulator or calculator forĪn aerodynamics problem. The icon at the top of each section will take Here is a group of Java programs which were designed to help ![]()
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