Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading

John R. Erwin, Melvyn Savage, James C. Emery
naca-tn-3817
Nov 1956


Comparative tests of blade sections having an isolated airfoil lift coefficient of 1.2 were made for two other blade sections with mean lines having different loading distributions at an inlet angle of 45 degrees with a solidity of 1.5 and at an inlet angle of 60 degrees with a solidity of 1.0.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1956/naca-tn-3817.pdf