Moment Coefficient

Because the maximum camber ratio of a thin airfoil is small by definition, the moment expression for a cambered airfoil can be represented adequately by the expression derived for a symmetrical airfoil (i. e., flat plate). Then, referring to Fig. 5.21 and the development for a symmetrical airfoil:

c c

MLle = – J(PL – PU)(x)dx = – J(pVji)(x)dx.

0 0

Moment Coefficient Подпись: Jy (Ф)[1 - cos Ф]^ІП ф)dф. 0

Applying the transformation from linear to angular measure and writing this equation in coefficient form results in:

Moment Coefficient Moment Coefficient Подпись: (5.31)

Substituting for у (ф) = у (0) from Eq. 5.21 and integrating using basic trigonometric identities and integral tables results in:

The moment coefficient for a cambered airfoil is seen as depending on only three Fourier-series coefficients and as a function of the angle of attack and camber.

Leave a reply

You may use these HTML tags and attributes: <a href="" title=""> <abbr title=""> <acronym title=""> <b> <blockquote cite=""> <cite> <code> <del datetime=""> <em> <i> <q cite=""> <s> <strike> <strong>