MAE 150B - 04C - Incompressible Flow over Airfoils

MAE 150B - 04C - Incompressible Flow over Airfoils - MAE...

Info iconThis preview shows pages 1–9. Sign up to view the full content.

View Full Document Right Arrow Icon
    MAE 150B - Chap 4 part C Incompressible Flow Over Airfoils
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
    Example 4.5  (pp. 334)  : NACA23012 The camber line defined as z/c = f(x/c) (a). Calculte the AOA at zero lift (b). Lift coef. At α =4 o Moment coef. About c/4 The location of center of pressure For a cambered airfoil, one of the most important parameter defining the shape is ____? It can be obtained easily from the given expression dx dz
Background image of page 2
    Example 4.5  (pp. 334)  : NACA23012 (a) the zero-lift AOA can be obtained from As the integration is w.r.t. d θ , we need to transform x=(c/2)(1-cos θ ) Sub dz/dx into above equation and carry out the integration We may need to use Math. Handbook to carry out the integration ( 29 ) 61 . 4 ( 1 cos 1 0 0 0 0 θ π α d dx dz L - - = =
Background image of page 3

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
    Example 4.5  (pp. 334)  : NACA23012 After zero-lift AOA is known, Eq. (4.60) can be used for the lift coef. Of any other α And the result is 2 π ( α - α L=0 ) = 2 π (0.0698- 0.0191) = 0.559 ( 29 ) 60 . 4 ( 2 0 = - = L l c α π
Background image of page 4
    Example 4.5  (pp. 334)  : NACA23012 (c) The quarter chord moment coeff. Is obtained from (4.64) We can get A1 and A2 from (4.51) A1 and A2 are n=1,2 respectively (what are they?) After some messy but straightforward operations, A1 and A2 are readily available ( 29 ) 64 . 4 ( 4 1 2 4 / , A A c c m - = π ) 51 . 4 ( cos 2 0 0 0 θ d n dx dz A n =
Background image of page 5

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
    Example 4.5  (pp. 334)  : NACA23012 Similarly, the center of pressure can be obtained by plugging A1 and A2 ( 29 ) 66 . 4 ( 1 4 2 1 - + = A A c c x l cp π
Background image of page 6
    Example 4.5: NACA23012 comparison with experimental data calculated measured α L=0 -1.09 -1.1 α (4 o ) 0.559 0.55 C m,c/4 -0.0127 -0.01
Background image of page 7

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
    Aerodynamic Center Additional consideration (4.9) Most conventional airfoils, the aerodynamic center is
Background image of page 8
Image of page 9
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 10/09/2009 for the course MAE 150B taught by Professor D during the Spring '09 term at UCLA.

Page1 / 32

MAE 150B - 04C - Incompressible Flow over Airfoils - MAE...

This preview shows document pages 1 - 9. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online