126.96.36.199 Incompressible Flow (M0 = 0)
In 2-D, the following aerodynamic coefficients C/, Cm, o, and Cd are defined as
Fig. 15.13 Forces locations at take-off
L’ _ M _ D
2 pU2c m’° 2 pU2c2’ d 2 pU2c
The expressions for Cl(a), Cm, o (a) and Cd for a symmetric profile are
See the sketch of the flat plate at incidence and of the force due to pressure integration and the suction force on Fig. 15.14.
The suction force coefficient can be obtained since the resulting drag coefficient must be zero. Hence
Cs — F’j ^—pU2c^ — Ci sin a = Ci a — 2na2
The thickness distribution contributes to recuperating the suction force by allowing the boundary layer to remain attached at the rounded leading edge, thanks to the elimination of the singularity at the sharp trailing edge of the plate.
Center of Pressure
Definition: the center of pressure is the point about which the moment of the aerodynamic forces is zero.
As seen in class, the center of pressure for a symmetric profile is at the quarter – chord. This is easily shown by using the transfer of moment formula
xcp Cm, o 1
~ = cT = 4
For a symmetric profile, Cm, ac = 0, since the center of pressure coincides with the aerodynamic center (the formula for the value of Cm, ac is the same as that for
Computing Cm, o(a) from the Cm, ac, the change of moment formula gives
188.8.131.52 Supersonic Flow (Mo > 1, в = ^— 1)
A thin double wedge airfoil equips the fins of a missile cruising at Mach number M0 > 1 in a uniform atmosphere. The chord of the airfoil is c. The profile camber and thickness are:
d (x) = 0
20x, 0 < x < c/2
2в(е – x), c/2 < x < c
with z±(x) = d(x) ± e(x)/2.
C + and C – are the same at a = 0. One finds
C+ = C – = в в, 0 < x < c/2 C+ = C- = – вв, c/2 < x < c
See Fig. 15.15.
The lift coefficient Ct (a) for all thin airfoils in supersonic flow is only a function of incidence
Ct (a) = a
Fig. 15.15 Pressure coefficients at a — 0
The drag (wave drag) at zero incidence, (Cd)a=0, is
4 2 4 2
Cd (a) = в2 + a2
The zero incidence moment coefficient (Cm, o) 0 = 0 since it only depends on
Thus, the values of the coefficient Cm, o for the general case a = 0 is
The inverse of the finess, 1/f — Cd/Ci is
1/f = + a
and the value of a that maximizes f satisfies
The solution is a = в (a =—в for negative lift). See Fig. 15.16 for remarkable waves (shocks, expansions).