Calculation of three-dimensional flows of ideal gas without a plane of symmetry

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

“…The successful implementation of that approach is also based on the successful combining of the difference schemes [10,11] using the determination of smooth solutions and the shock-capturing technique in regions with internal shock waves. In principle, by means of constructing adequate euristic approximations in any zone one can attain any desirable accurate modeling of the given standard dependences.…”

“…The importance of the calculation formulas of type (3.2) derived on the basis of the invariant relations (1.1) consists in their obvious simplicity and applicability to the effective optimization of a qualitative routine engineering analysis of the effect of the varied governing parameters on the main aerodynamic characteristics of the axisymmetric noses of flight vehicles, for example, of the semi-vertex angle of the circular cone θ c and the Mach number M ∞ on utmost wide ranges of their variation 0 ≤ θ c ≤ 90 ∘ and 0 ≤ M ∞ < ∞. Analogously to (3.2), after the corresponding verifications have been performed, the ranges of the practical applicability of other approximate calculation formulas derived in Section 2 can also be refined for the purpose of filling up the practically used libraries [8][9][10][11][12] of specialized applied mathematical software.…”