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aerodynamics-expert

Expert-level aerodynamics covering subsonic and supersonic flow, lift and drag, airfoil theory, boundary layers, compressible flow, and CFD methods.

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luokai0/ai-agent-skills-by-luo-kai

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Aerodynamics Expert

Before Starting

  1. Subsonic, transonic, or supersonic regime?
  2. Internal or external flow?
  3. Analysis or design focus?

Core Expertise Areas

Airfoil Theory

Lift: generated by pressure difference between upper and lower surfaces. Camber: curvature of mean line, increases lift at zero angle of attack. Thickness: affects drag and maximum lift, NACA 4-digit series defines profile. Angle of attack: increasing AoA increases lift until stall. Stall: boundary layer separates from suction surface, lift drops suddenly.

Thin Airfoil Theory

Lift coefficient: CL = 2 pi times alpha for thin symmetric airfoil. Moment coefficient: CM about quarter chord is zero for symmetric airfoils. Aerodynamic center: point where moment coefficient is independent of AoA. Camber effect: adds lift at zero AoA proportional to maximum camber.

Drag

Pressure drag: form drag from pressure distribution, reduced by streamlining. Skin friction drag: viscous shear stress on surface, dominant for streamlined bodies. Induced drag: due to finite wing span, CDi = CL squared over pi AR e. Wave drag: energy lost to shock waves in transonic and supersonic flow. Drag polar: CD vs CL squared, slope is 1 over pi AR e.

Compressible Flow

Mach number: M = V over a, ratio of flow speed to speed of sound. Critical Mach: freestream Mach where local sonic flow first appears. Prandtl-Glauert: compressibility correction for subsonic flow, 1 over sqrt 1 minus M squared. Shock waves: normal and oblique, pressure rises discontinuously. Expansion fans: isentropic acceleration around convex corners.

Best Practices

  • Verify Reynolds number and Mach number before selecting analysis method
  • Use panel methods for subsonic, Euler for transonic, full NS for separated flow
  • Validate CFD results against wind tunnel data for critical designs
  • Check for flow separation before assuming attached flow methods are valid

Common Pitfalls

PitfallFix
Applying thin airfoil theory at high AoAValid only for small angles, below stall
Ignoring compressibility near Mach 0.3Apply Prandtl-Glauert correction above M=0.3
2D analysis for finite wingApply finite wing correction for induced drag
Inviscid analysis near separationUse viscous solver for high AoA or bluff bodies

Related Skills

  • flight-mechanics-expert
  • propulsion-expert
  • fluid-mechanics-expert

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