Results are presented from two-dimensional and three dimensional wind tunnel tests of the NACA 23024· airfoil. Variables include Reynolds numbers ranging from To , the addition of one to three layers of boundary layer trip strips, and the differences between the 2D and reflection plane testing techniques. Angles of attack ranged from -10° to +500 degrees. In order to demonstrate the repeatability of the experimental apparatus, results from similar tests on several dates are compared. In addition, the 3-dimensional data (aspect ratio of 13.33) are used as input to an algorithm providing corrections to approximate 2-dimensional conditions, and these results are compared to the actual 2D data. The corrections include post-stall effects as well as the familiar Prandtl downwash adjustment. Within the range of Reynolds numbers tested, decreased maximum lift coefficients are associated with increased Reynolds numbers, while the addition of trip strips was seen to cause a relatively drastic decrement in and a max sharpening of the stall break. The 3O-to-2D correction algorithm was seen to give a close approximation to 2D data for drag at high angles of attack and for lift at low angles of attack; the correction was less successful at and in the near post-stall regime, where the behavior Max of thick 230-series airfoils is known to be erratic.