Theoretical results for the initial lift‐curve slope of straight‐tapered wings, based on the linearized equations of inviscid motion, have been evaluated and are presented in the form of graphs.
Stanbrook, A. (1954), "Lift‐Curve Slope at Subsonic and Supersonic Speeds: Graphical Presentation of Theoretical Results for Straight‐Tapered Wings", Aircraft Engineering and Aerospace Technology, Vol. 26 No. 8, pp. 244-257. https://doi.org/10.1108/eb032455
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