Incompressible Aerodynamics: Vortex Panel Project

Pulsed Plasma Thruster Stand

Summary

In the Vortex Panel Mini-Project, aerodynamic characteristics of four airfoils (NACA 0010, NACA 1410, NACA 2410, and NACA 6409) were analyzed using MATLAB and XFOIL software, generating graphs for lift, drag, moment coefficients, and pressure distribution at different angles of attack.

1. Vortex Panel Mini Report: Here

Main Points:

  • Gathered aerodynamic data for four airfoils: NACA 0010, NACA 1410, NACA 2410, and NACA 6409.
  • Reynolds number (Re) set to 3000000 and Mach number (Ma) to 0.1 as instructed.
  • Generated eight graphs depicting lift coefficient, drag coefficient, moment coefficient, and pressure coefficient for each airfoil at angles of attack α = 0, 5, 10 degrees.
  • NACA 0010: Symmetric airfoil with lower camber, showing good lift and low drag, suitable for high-speed designs.
  • NACA 1410: Symmetric airfoil with larger lift coefficient but slightly higher drag, reaches stall at a lower angle of attack compared to NACA 0010.
  • NACA 2410: Lower camber and thin body, reducing drag force and allowing higher speed.
  • NACA 6409: Thick and cambered, generates more lift but also more drag than NACA 0010.
  • Compared pressure distribution along airfoils using Cp vs x/c plots, observing differences in pressure buildup and gradients.