Embedded Files
Run Setup Instructions for TS Aero Recipes
Run Setup Instructions for TS Aero Recipes
VTOL
VTOL
Altitude
Altitude
- Entering a Geopotential Altitude (m) will use the Standard Temperature (K) and Pressure (Pa) at that altitude to calculate the Kinematic Viscosity (NS/m^2) and Density (kg/m^3).
- OPTIONAL: Enter Temperature Offset (K) for a non-standard day. This will adjust the Standard Temperature at the Altitude and recalculate the Kinematic Viscosity and Density.
Vehicle Settings
Vehicle Settings
- Ground Clearance is the distance between the ground and the Moment Reference Center. The ground clearance input is capped at 12 m. because ground effects would not be simulated at any larger clearance.
- Pitch and Roll inputs are relative to the ground.
- Yaw input is the yaw of the incoming freestream velocity. For positive yaw the freestream is coming from the vehicle's right side, and negative yaw is coming from the vehicle's left side.
- Forward velocity is the velocity of the incoming freestream velocity. For Hover Conditions, enter 0.01 m/s.
- Reference Moment Center is the point where the moment calculations will be based off of. This point should be the Center of Gravity of the vehicle. This does not need to be adjusted for ground clearance. For example, if your ground clearance is 4 m and your Moment Center is (0 0 0), you would still enter (0 0 0) for your Reference Moment Center.
- Reference Span Length and Reference Width will be used to calculate the Roll, Pitch, and Yaw Moments.
Airfoil
Airfoil
- Input the altitude. (The pressure, density, etc values are automatically populated to correspond to the altitude input. However, these values can be adjusted to match wind tunnel or other conditions if needed for comparison.)
- Enter Angle of Attack.
- Enter Velocity.
- Input the Reference Chord Length.
- Select the parts.
- Click Save.
It has been found that the most accurate way to run an airfoil is to use a parametric sweep. The way this works is that the first angle of attack (usually 0 degrees) is created and ran then the rest of the sweep follows from that first case. The next angle of attack is run as a continuation of the previous finished case by altering the flow direction to correspond to the new angle of attack. That case is run until it converges and then the next angle of attack uses this solution as a starting point and so on until the sweep is completed. Other than more accurate results, another benefit is this requires only one meshing of the airfoil and then subsequent runs are all ran from the original meshing. This saves computational resources and is reflected in the token cost per run.
We recommend that all airfoil cases be run using the parametric sweep set up. You will find more information on setting up a parametric sweep here.
Free Flight
Free Flight
- Input the Altitude [m]. The pressure, density, etc values are automatically populated to correspond to the altitude input.
- OPTIONAL: Input Temperature Offset [K]. This will adjust the Standard Temperature at the Altitude and recalculate the Kinematic Viscosity and Density. This adjustment is usually used to match wind tunnel or other conditions.
- Enter Angle of Attack [deg].
- Enter Yaw [deg]. Yaw input is the yaw of the incoming freestream velocity. For positive yaw the freestream is coming from the aircraft's right side, and negative yaw is coming from the aircraft's left side.
- Enter Velocity [m/s].
- Input the Reference Moment Center. The reference moment center is used for the cumulative moment forces being reported of the aircraft.
- Select the parts.
- Fill out any simulation-specific fields corresponding to the selected parts.
- Click Save.
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