flow properties (X,Y, Mn etc) at each characteristic mesh point to a data file. Aerospike Rocket Motor Design Example AeroCFD.2 Analysis by John Cipolla Annular aerospike designed to produce 225,000 pounds of thrust. Input data for the results in Figure-10 based on data from Figure-9 using AeroSpike version. Added the ability to include base thrust for truncated aerospike nozzles. CF verses Pressure Ratio (Pc/Pa) - Semi-Log plot, Maximum PR 1000. Anderson note about MLN analysis accuracy: The Minimum Length Nozzle (MLN) analysis illustrated in Figure-2 uses exact input data from Modern Compressible Flow With Historical Perspective. Design Mach number (Mdesign The Mach number at the exit of the nozzle where the flow is uniform. Note: Some jurisdictions have established legal requirements for password length as part of establishing security regulations. Define the angle the sonic section of the thruster makes with the axis of the aerospike nozzle. Output all flow variables to the printer or text file for use with spreadsheet applications. Where, X truncation refers to an aerospike nozzle where (100-X) of the expansion ramp has been removed leaving a blunt base region.
Server type or Group Policy Object (GPO). Save the nozzle description file from a previous session. Thruster pressure ratio (Pc/Pei Ratio of chamber pressure to thruster exit pressure. However, the user can over-ride significant influence college essay any input value by inserting new data directly into each data entry box on the Aerospike Nozzle Design screen. The ratio of specific heats, gas constant (Rgas chamber pressure (Pc and pressure ratio (PR) are required for the Aerospike Nozzle analysis. The nozzle contour is drawn by starting at the throat corner where the maximum expansion angle of the wall, q w_max is equal to one-half the Prandtl-Meyer function, n( Mn) / 2, at the design exit Mach number. For comparison purposes all results are referenced to the curved sonic line analysis for 2-D and 3-D axisymmetric nozzles. Time between X-33 flights was planned to normally be seven days, but the program hoped to demonstrate a two-day turnaround between flights during the flight-test phase of the program. Read the nozzle description file from a previous session. In the Aerospike Nozzle Data section added a display of Distance from throat (origin) to end of thruster. However, the user can over-ride the inserted ratio of specific heats by simply inserting his own ratio of specific heats in the data entry box. Aerospike Nozzle - Secondary Input Data Entry Area for Annular/Linear nozzle and thruster angle inputs.
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