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This document discusses lift estimation for the conceptual design phase of an aircraft. It calculates the coefficient of lift (CL) at different flight phases. Specifically, it calculates: 1. The required maximum CL (CLmax) needed based on constraints. 2. The available CLmax from the selected airfoil, including calculating the Ostwald efficiency factor. 3. The difference between the required and available CLmax, which indicates that slotted flaps should be added to the wing design to increase the lift b

Author

Avinash Singh

Language

EN