A method of calculating the aerodynamic characteristics of bodies on the basis of invariant relations of the theory of local interaction

Antonets, A. V.; Dubinskii, A. V.

doi:10.1016/0021-8928(83)90150-8

Cited by 2 publications

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“…The idea of replacing a vehicle with a complicated original shape by one or more equivalent bodies (expansion in the chosen basis) is widely used in aerodynamics for developing approximate computational methods (see, for example, [1][2][3][4][5][6][7][8][9]). In particular, the application of the local force interaction principle has made it possible to derive such effective calculation methods as the rules of local sharp and blunt cones [2,3], the plane cross-section law (piston analogy) [2], the invariant relation method [7], and others.…”

Section: Methods Of Equivalent Bodies For Calculating Unsteady Aerodynmentioning

confidence: 99%

“…In particular, the application of the local force interaction principle has made it possible to derive such effective calculation methods as the rules of local sharp and blunt cones [2,3], the plane cross-section law (piston analogy) [2], the invariant relation method [7], and others. The most general formulation of this principle leads to a technique of searching for equivalent bodies [9] for the purpose of justifiably reducing the unsteady calculation problem to a steady one.…”

Section: Methods Of Equivalent Bodies For Calculating Unsteady Aerodynmentioning

confidence: 99%

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Study of the damping characteristics of sectional flight vehicles of different length

Antonets¹,

Shmanenkov²

2004

Fluid Dyn

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The dependence of the damping characteristics of axisymmetric tri-sectional flight vehicles executing plane oscillations about the zero angle of attack on their geometric parameters is investigated on the supersonic range of uniform oncoming air flow Mach numbers. Systematic data are obtained using the least laborious approach, namely, by calculating the steady-state inviscid flow past equivalent bodies determined from the principle of the local similarity of force interaction. Ranges of the vehicle design parameters on which the dependence of the damping moment coefficient in pitch on the length of the conical or cylindrical-conical stabilizer of the vehicle is nonmonotonic are found. Typical viscosity effects on the characteristics under study are estimated using a method based on the assumptions of the linear theory for finite-thickness bodies. It is established that the damping coefficient increases monotonically with decreasing Reynolds number; moreover, even transition to oscillation antidamping regimes is possible when the sign of the damping coefficient changes.Keywords: supersonic flow past bodies, sectional flight vehicle, damping moment coefficient in pitch, method of equivalent bodies, viscous effects, linear theory for finite-thickness bodies.

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Section: Methods Of Equivalent Bodies For Calculating Unsteady Aerodynmentioning

confidence: 99%

Section: Methods Of Equivalent Bodies For Calculating Unsteady Aerodynmentioning

confidence: 99%

Study of the damping characteristics of sectional flight vehicles of different length

Antonets¹,

Shmanenkov²

2004

Fluid Dyn

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“…Provided that the "locality law" holds, in particular, in the case of hypersonic continuum flows, the following assertion was validated in [1]: if there exists a basis of N ≥ 2 standard bodies (flight vehicle noses) with the known parametric dependences of their l-th aerodynamic characteristics on the relevant parameters (the angle of attack α, the flight Mach number M ∞ , etc.) of the form C lν (α, M ∞ ,... ), ν = 1, 2,... , N, then the corresponding characteristics C l0 (α, M ∞ ,... ) of a certain flight vehicle (generally of three-dimensional configuration or, as in our case, a body of revolution) with the given generator shape r 0 (x, ϕ) ≡ r 0 (x) in the body-fitted cylindrical reference frame (x, r, ϕ) can be calculated from the formula…”

Section: Basic Relationsmentioning

confidence: 99%

Application of the method of invariant relations in analyzing the parametric dependences of the aerodynamic parameters of the classical axisymmetric noses of flight vehicles

Antonets

2015

Fluid Dyn

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The method of invariant relations rigorously validated under the conditions of "local mechanical interaction" is applied to the derivation of approximate formulas for calculating the aerodynamic parameters of axisymmetric flight vehicles, whose generators represent combinations of rectilinear and ogive-shaped sections, on a basis of three canonical vehicle shapes with the same mid-sections in reduced coordinates. These are the circular disk, the spherical segment, and the sharp circular cone tangent to the segment along the contour of its mid-section, with the semi-vertex angle 0 ≤ θ k < 90 ∘ .Keywords: stationary aerodynamic parameters, aerodynamic drag coefficient, method of invariant relations, theory of local mechanical interaction, basis of standard bodies. r k2 = R b.sp.s cos θ k ; ρ 3 (η) = 0, 0 ≤ η < 1 : for the sharp circular cone r k3 = r k2 tangent to the basic spherical segment.

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A method of calculating the aerodynamic characteristics of bodies on the basis of invariant relations of the theory of local interaction

Cited by 2 publications

References 0 publications

Study of the damping characteristics of sectional flight vehicles of different length

Study of the damping characteristics of sectional flight vehicles of different length

Application of the method of invariant relations in analyzing the parametric dependences of the aerodynamic parameters of the classical axisymmetric noses of flight vehicles

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