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|File - Download RASAero II 188.8.131.52|
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RASAero II 184.108.40.206
RASAero II is a combined aerodynamic analysis and flight simulation software package for model rockets and high power rockets, amateur rockets, and sounding rockets. RASAero II can also be used for predicting aerodynamic coefficients for use in other flight simulation programs for orbital rockets.
The RASAero II aerodynamic prediction methods are the most accurate available for model, high power, and amateur rockets, and are of equivalent accuracy to professional engineering method aerodynamic analysis codes used for missiles, sounding rockets, and space launch vehicles.
In testing in comparison with high power rocket barometric altimeter data, optical tracking data, accelerometer-based flight data, and GPS flight data, the average RASAero II altitude prediction error was 3.38%, with 78.8% of the RASAero II flight simulation altitude predictions within +/- 10% of the flight data, and 42.4% of the altitude predictions within +/- 5% of the flight data.
The RASAero II aerodynamic predictions include drag coefficient at zero degrees angle of attack, drag coefficient with a non-zero angle of attack, and lift coefficient and normal force coefficient with angle of attack; for both power-on (thrust phase) and power-off (coast phase). Center of pressure is predicted both as a function of Mach number and as a function of angle of attack. Aerodynamic coefficients are predicted for the subsonic, transonic, supersonic, and hypersonic flight regimes, from Mach 0.01 to Mach 25.
The RASAero II aerodynamic prediction methods and the RASAero II software have been calibrated against NACA and NASA wind tunnel model data, free-flight model data and sounding rocket data, missile aerodynamic data, and professional engineering method missile aerodynamic analysis programs, against which in comparison tests RASAero II has demonstrated equivalent numerical accuracy.
RASAero II release history:
Version 220.127.116.11 – Release Date August 5, 2016
Changed the recommended stability margin for subsonic Mach numbers to a stability margin of 1.0 calibers, kept the recommended stability margin for transonic and supersonic Mach numbers at 2.0 calibers, for the marginal stability warning message.
Added extension to power-on base drag model for very large nozzle exit diameters at supersonic and hypersonic Mach numbers, with the nozzle exit area filling a large portion of the rocket base area, for more accurate power-on drag coefficient (CD) predictions for first and second stages of satellite launch vehicles.
Added stability margin (calibers) to the Flight Simulation plots.
Added additional outputs to the Flight Simulation Excel (.CSV) output file.
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|2,831||6,674||Charles E. Rogers and David Cooper <img src="http://www.oldergeeks.com/downloads/gallery/thumbs/RASAeroII1_th.png"border="0">||Apr 09, 2017 - 21:28||18.104.22.168||1.72MB||ZIP||, out of 14 Votes.|
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