Comparison of two-dimensional and three-dimensional droplet trajectory calculations in the vicinity of finite wingsComputational predictions of ice accretion on flying aircraft most commonly rely on modeling in 2D. These 2D methods treat an aircraft geometry either as wing-like with infinite span, or as an axisymmetric body. Recently, fully 3D methods have been introduced that model an aircraft's true 3D shape. Because 3D methods are more computationally expensive than 2D methods, 2D methods continue to be widely used. However, a 3D method allows investigation of whether it is valid to continue applying 2D methods to a finite wing. The extent of disagreement between LEWICE, a 2D method, and LEWICE3D, a 3D method, in calculating local collection efficiencies at the leading edge of finite wings is investigated.
Document ID
19920045591
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mohler, Stanley R., Jr. (NASA Lewis Research Center Cleveland; Sverdrup Technology, Inc., Brook Park, OH, United States)
Bidwell, Colin S. (NASA Lewis Research Center Cleveland, OH, United States)