2-D Inviscid, Linearized, Thin Airfoil Theories
184.108.40.206 Incompressible Flow (Mo = 0)
Cambered Plate Geometry
Given the thin cambered plate equation
one calculates d'(x) to be
d'(x) = A 1
Fig. 15.25 Thin cambered d(x)
The Fourier coefficients A0, A1, A2,…, An for this thin cambered plate are obtained from the equation
d'[x(t)] – a = — A0 + ^ An cos nt
Changing variable from x to t in d'(x) yields
d'[x(t)] = A ^ 1 — 3(1 — cos t) + 3(1 — cos t)2^
/ 1 3 2 A
= A — 2 + 2 cos21 = — (1 + 3cos2t)
where we have made use of the identity cos21 = (1 + cos 2t )/2. Substitution in the above equation provides by simple identification all the Fourier coefficients
Ao = a — , A1 = 0, A2 = A, A3 = ••• = An = 0, n > 3
From the result for A0 one finds aadapt = A.
Sketch of the flow at the incidence of adaptation is in Fig. 15.26.
Definition of Aerodynamic Center
The aerodynamic center is the point about which the moment of the aerodynamic forces is independent of incidence.
Fig. 15.26 Thin cambered plate at incidence of adaptation and some streamlines
The aerodynamic coefficients C;(a), Cm, o(a) and Cm, a.c. are all expressed in terms of the Fourier coefficients, i. e.
Cm, a.c. = ~~r (A1 — A2) = A
Static Equilibrium About an Axis
The change of moment formula gives the aerodynamic moment coefficient at the mid-chord, x = 2
n 5 A 1 A n A
a — + 2n a — = a +
2 8 2 4 2 8
The equilibrium angle aeq is such that Cm 1 (aeq) = 0. Hence
aeq = —8