The Reduction of Flight Test Climb Data to Standard Air Conditions

General equations for the reduction of flight test climb data to standard air conditions are given, indicating how the airplane and engine characteristics affect the necessary rate of climb corrections. Charts are given to provide an aid in the reduction of climb data of airplanes having modern engine installations. The method of climb reduction presented is then expressed in terms of the climb altitude, which has had wide use in the past. The author feels that this correlation shows the limitation of each method, and when one or the other is best suited. The equivalent climb altitude constant K is shown to depend mainly upon Oswald's airplane parameter A which enables K to be readily selected for most any type of airplane. While K = = 0 . 3 7 for modern bimotor airplanes in two engine climb, it may increase to K = 0.50 for the same airplane in single engine flight.