Thin-Airfoil Lift Curve

Visualize finite-wing lift curve, induced drag, and L/D from angle of attack, aspect ratio, and Oswald efficiency.

visual calculatorAerodynamics & External Flow

Read the flow shape before trusting the number.

This page turns a CFD setup into regime, scale, and dominant-effect cues. Adjust the calculator below and compare the moving graphic with the computed result.

input scale

model

check

thin airfoillift curveinduced dragvisualization

formula

KaTeX rendered

\begin{aligned}\text{C\_L \~{}= a alpha}\\[0.35em]\text{a = 2 pi / (1 + 2/(AR e))}\\[0.35em]\text{C\_Di = C\_L\^{}2/(pi AR e)}\end{aligned}

ASCII source

C_L ~= a alpha, a = 2 pi / (1 + 2/(AR e)), C_Di = C_L^2/(pi AR e)

alpha (deg)aspect ratioOswald eC_D0stall angle (deg)

dCL/dalpha per deg

0.0847

C_L

0.4237

C_Di

0.0084

C_D

0.0334

L/D

12.684

Use this as a first-pass inviscid lift and induced-drag check. It is not a stall-resolved airfoil polar.

thin airfoil lift curve induced drag visualization