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Subsonic Finite Wing Theory - ZACM3031
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Faculty: UNSW@ADFA (Australian Defence Force Academy)
 
 
School:  UC Aerospace, Civ and Mech Eng
 
 
Course Outline: UNSW@ADFA Student Gateway
 
 
Campus: University College Campus
 
 
Career: Undergraduate
 
 
Units of Credit: 3
 
 
EFTSL: 0.06250 (more info)
 
 
Indicative Contact Hours per Week: 3
 
 
Enrolment Requirements:
 
 
Prerequisite: ZACM2032
 
 
Fee Band: 2 (more info)
 
 
Further Information: See Class Timetable
 
 

Description

The finite span of a real aircraft wing creates three dimensional flow effects, such as downwash, which reduce the wing's total lift and increase its drag from that expected from direct application of airfoil (infinite span wing) behaviour. Prandtl's classic and general lifting line theories are presented to obtain lift and drag estimates for finite wings in incompressible flow. This theory is extended to panel methods applicable to straight and swept finite wings and to blade element theory applicable to propellers.

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