Aerospace Toolbox 2.5

Calculating Best Glide Quantities  

This demonstration shows how to use Aerospace Toolbox to calculate values of velocity and glide angle that minimize drag and maximize lift-drag ratio.

Comparing Zonal Harmonic Gravity Model to Other Gravity Models    

Displaying Flight Trajectory Data  

This demo shows how you can use Aerospace Toolbox to visualize your flight data in FlightGear flight simulator for quickly reconstructing behavioral anomalies in your flight test results.

Estimating G Forces for Flight Data  

This demonstration shows how you can use Aerospace Toolbox to load flight data and calculate G forces during the flight.

Importing from USAF Digital DATCOM Files  

This demonstration shows how Aerospace Toolbox enables import of Digital DATCOM files into MATLAB.

Overlaying Simulated and Actual Flight Data  

This demo illustrates how you can use Aerospace Toolbox to visualize simulated versus actual flight trajectories and manipulate body properties.

Visualize Aircraft Takeoff via Simulink 3D Animation™  

This demo shows how to visualize aircraft take-off and to add a chase helicopter to the virtual scene using the interface to Simulink 3D Animation™ provided by the Aerospace Toolbox.

Calculating Compressor Power Required in a Supersonic Wind Tunnel  

This demo illustrates how to calculate the required compressor power in a supersonic wind tunnel, which allows the system to operate.

Analyzing Flow with Friction Through an Insulated Constant Area Duct  

This demo illustrates steady, viscous flow through an insulated, constant-area duct also called Fanno line flow.

Determining Heat Transfer and Mass Flow Rate in a Ramjet Combustion Chamber  

This demo illustrates how to use the Aerospace Toolbox functions to determine heat transfer and mass flow rate in a ramjet combustion chamber.

Solving for the Exit Flow of a Supersonic Nozzle  

This demo illustrates how to use the method of characteristics and Prandtl-Meyer flow theory to solve a problem in supersonic flow involving expansions. We solve for the flow field downstream of the exit of a supersonic nozzle.