Document Type

Article

Publication Date

1-26-2026

Abstract

This paper covers an aerodynamic analysis of the Boeing Bell V-22 Osprey proprotor blade by utilizing thin-airfoil theory (TAT) and lifting-line theory (LLT). The primary focus is how the coefficient of lift and induced drag respond to changes in the angle of attack of the proprotor blades. The proprotor blade is modeled as a finite wing based on the NACA 63-212 airfoil. The wing has a geometric twist of -35 degrees from root to tip. The theories used to evaluate the blade design are limited by the assumption of incompressible, inviscid flow. The results of the analysis indicate that lift coefficients are maximized at high collective blade pitch of approximately 50 degrees to overcome the geometric twist necessary to evenly distribute lift over the span. Additionally, rotating the nacelle drastically reduces the coefficient of thrust from 0.09 to 0.02 as the fixed wings of the aircraft take over lift generation and the proprotor blades produce propulsion in airplane mode.

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