Abstract:

ESDU 72027 takes charts from ESDU 71019 for the prediction of the Mach number at which shock-wave drag first appears on families of aerofoils having a particular form of upper-surface pressure distribution at that drag rise condition and adapts them to three-dimensional flow. The adaptation applies to the mid-semi-span portion of a wing (away from the root, tip and any crank effects) of swept and tapered planforms having upper-surface pressure distributions in the streamwise direction equivalent to those of ESDU 71019. The adaptation uses simple sweep laws and equivalent sweep angle.