NASA RAVEN-SWFT eVTOL Aerodynamic Analysis

eVTOL aerodynamic analysis

This page presents the results of a Stallion 3D CFD aerodynamics analysis of the NASA RAVEN-SWFT eVTOL in early transition. These preliminary results capture a forward speed of 7 m/s with rotor forces matching 1,000 lbs. Aerospace engineers use Stallion 3D to compute lift, drag, moments and stability derivatives for flight dynamics plant models (FDM) and predict aerodynamic performance.

RAVEN Transition Strategy ➡️ Stallion 3D Info. ➡️ Any questions 🧐

Key words: Aircraft Aerodynamics, NASA RAVEN-SWFT, eVTOL, CFD analysis

Results Summary

This is a Stallion 3D near-hover simulation of the NASA RAVEN SWFT, a 1,000 lb eVTOL concept, at 7 m/s forward speed. The model includes six lifting rotors with pressure plotted on the aircraft surfaces and actuator disks. The pressure scale shown is approximately 100,950 to 101,450 Pa.

Aerodynamic Metric Metric Value Imperial Value
Lift (FZ) -86.31 N -19.40 lbs
Total Drag (FX) 62.30 N 14.01 lbs
  • Pressure Drag 57.65 N 12.96 lbs
  • Friction Drag 4.65 N 1.04 lbs
Side Force (FY) -3.08 N -0.693 lbs
Pitching Moment 175.38 N-m —
Rolling Moment -1.23 N-m —
Yawing Moment -9.74 N-m —

Ideal Rotor Power Breakdown

The ideal power required across the six actuator disks is distributed as follows, totaling 47,169.70 W:

This is a simple near-hover CFD check, but it shows the type of integrated aircraft, rotor, pressure, force, moment, and power information that can be reviewed directly inside Stallion 3D.

Aerodynamics Analysis Method

The complete workflow scales seamlessly from geometry to final aerodynamic verification inside Stallion 3D:

  1. Seamless STL Import: Read the NASA RAVEN-SWFT STL geometry created by OpenVSP directly into Stallion 3D, inspect the wireframe, and confirm the correct dimensional units.
  2. Actuator Disk Configuration: Position each of the six lifting rotors using the precise STL coordinates of the rotor hubs, then define the respective diameters and thrust constraints.
  3. Automated Grid Generation: Set up the CFD grid. Start with an initial lower resolution for an instant baseline validation check to ensure boundary settings are exact without wasting engineering hours.
  4. Navier-Stokes Solver: Automatically generate the mesh and execute the flow solver to resolve full surface pressures, force components, and moments. Run higher resolutions as needed to establish mesh independence.
Learn more ➡️ Any questions 🧐