Interactive Airfoil Design

This page lets you analyze and design airfoils. You can enter the coordinates of an airfoil section in the textarea that appears when the "Data" button is highlighted. By clicking "Plot" the computed pressure distribution is shown. The transition location parameters let you force transition to turbulent flow at the indicated chordwise position on the upper or lower surface. Setting xt/c = 1.0 corresponds to free transition while setting it to a small value such as 0.05 forces mostly turbulent flow.

Hints: Change angle of attack by either entering a value and clicking "Update" or by clicking on the angle of attack displayed on the plot. Holding down shift while clicking on the plot reduces alpha. You may also change scale by clicking on the Cp axis labels. Also note that you may modify the airfoil shape by clicking on the upper or lower surface to add thickness near the point where you have clicked. Hold down the shift key while clicking to remove thickness. The boundary layer computations indicate transition to turbulent flow (T), laminar separation (LS), or turbulent separation (TS). If you change parameters, click "Update" to enter these values. The parameters associated with bump width and height control the extent and magnitude of airfoil changes.