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This document discusses the optimization of wing loading for an airplane based on range considerations. It provides an example calculation to determine the optimum wing loading of 4539 N/m^2 for a 60-seat turboprop airplane given a range of 1740 km. Allowing a 5% increase in fuel consumption yields a permissible range of wing loadings between 3116-6604 N/m^2. A table is presented comparing the optimum wing loadings based on take-off, landing, and range criteria, and a final wing loading of 3740 N/m^2 is sel

Author

zackufairu

Language

EN