Pressure distribution around an airfoil

Theoretical calculations for NACA 23012

Thin Airfoil Theory

Introduction

An airfoil is defined by first drawing a “mean” camber line. The straight line that joins the leading and trailing ends of the mean camber line is called the chord line. The length of the chord line is called chord, and given the symbol ‘c’.To the mean camber line, a thickness distribution is added in a direction normal to the camber line to produce the final airfoil shape. Equal amounts of thickness are added above the camber line, and below the camber line.

                                                                                (a)

                                                                                (b)

The solid blue line represents thin airfoil theory for Cp vs x/c, a) The solid red line is at AOA = 5 deg, b) The solid red line is at AOA = 10 deg.


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