Axisymmetric Flows and Slender Body Theories
Axisymmetric flows are needed to analyze flow over bodies of revolution. Extensions to bodies of revolution with fins (missiles) or slender wings (low aspect ratio) are also possible, using perturbations of axisymmetric flows. In this chapter, it is natural to use cylindrical coordinates. After the derivation of the governing equations at different Mach number regimes (subsonic, supersonic, transonic), lift and drag are calculated for standard shapes (Fig. 7.1).
7.1 Governing Equations in Cylindrical Coordinates
Assuming steady, inviscid, adiabatic, irrotational and isentropic flow with uniform upstream conditions, the governing equations, in vector notation, are
V.(pV) = 0, VxV = to = 0 (7.1)
In cylindrical coordinates, Fig. 7.2, the conservation of mass is
(p Ux) + (prur) + (pue) = 0 (7.2)
dx r dr r 89
where (ux, ur, u9 ) are the velocity components in x, r and 9directions, respectively. The vorticity components are
1 d 1 d
Mx = (rue) – (ur) (7.3)
r dr r d9
1 d d
Mr = (ux) – (u9) (7.4)
r d9 dx
© Springer Science+Business Media Dordrecht 2015
J. J. Chattot and M. M. Hafez, Theoretical and Applied Aerodynamics,
DOI 10.1007/9789401798259_7
Notice that Vм = 0, since м = Vx V. The condition is a consequence of the vector identity: the divergence of a curl vanishes.
The density can be calculated from Bernoulli’s law, assuming isentropic conditions
(7.6)
Fig. 7.2 Slender body of revolution and coordinate system
and
Y p V2
+ = H0 = const. (7.7)
Y – 1 P 2
In the latter equation of isoenergetic flow, the potential energy is assumed constant (and does not appear in the total energy).
From the above two equations, one obtains
For the irrotational flow, the velocity can be described by the gradient of a potential function
V = VФ
The potential equation in cylindrical coordinates is given by
The tangency boundary condition on a solid surface is VФ. п = 0, where n is the unit vector normal to the surface. Together with the far field condition, Ф ^ 0, as x2 + r2 ^ to, the formulation is complete.
For a body of revolution at zero angle of attack, there is no dependency on в, and the governing equation reduces to
or
гдФ _ дФ dR _ 1 дФ dS дг дx dx 2п дx dx
where S(x) = п R2(x), is the crosssectional area of the body. The pressure coefficient is
and
respectively. Also, the pressure coefficient becomes
(7.21)
Note that, for body of revolution, д/дв = 0, and the last term in the above equations vanishes.
For incompressible flows (M0 = 0), the fundamental solution of the Laplace equation is
1 1
4n Vx2 + r2
For subsonic flows (M0 < 1), using the PrandtlGlauert transformation, the fundamental solution becomes
For a source distribution q(x) per unit length along the xaxis, the perturbation potential at a point (x, r) reads
The strength of the sources is determined through imposing the boundary condition
where S(x) = n R2(x) represents the cross section of the body of revolution. Notice from mass balance, one obtains (see Fig. 7.3)
q(x)Ax = 2nRAR U = UAS (7.26)
hence
Also, integrating the tangency condition in the proximity of the xaxis (small r)
дф U, U ,
r = S'(x), ^ ф ~ S(x) ln r + g(x) (7.29)
д r 2n 2n
Oswatitsch and Keune [2] provided an approximation of the singular integral leading to
Note that the term g(x) depends in general on M0. For a body with a pointed nose and ending at a point or as a cylinder (S'(l) = 0)
U. (в U fx,, U fl,,
g(x) ~ 2ПS'(x) ln 2 – __ s"(§) ln(x §)d§ + — S (§) ln(§ – x)d§
0 x (7.31)
For supersonic flow (M0 > 1), the fundamental solution is different. The solution for a supersonic source is
The potential is a real number only within the Mach cone, Fig. 7.4. A source distribution will give the solution
where the integral is evaluated only for values of § < x – вr, Fig. 7.5.
Von Karman and Moore [3] analyzed this singular integral. Their results are given by






















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