15th Aerospace Sciences Meeting 1977
DOI: 10.2514/6.1977-205
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Implicit finite-difference computations of unsteady transonic flows about airfoils, including the treatment of irregular shock-wave motions

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Cited by 35 publications
(16 citation statements)
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“…result in LCO. This reminds one of the famous oscillatory flap solutions of Tijdeman [14,15] in transonic flow, where a steady strong shock will result in small (unsteady) shock excursion (type A) and weak shocks will result in large-amplitude (unsteady) shock excursions (types B and C − Morph Angle Effect The flutter/LCO speeds increases with increased Γ, in spite of M = 0.9 or 0.95. Increasing Γ will enhance the wing torsional stiffness, leading to the large flutter dynamic pressure (see Table 1).…”
Section: Continuous Dynamic Simulation Of a Moving Flap With Prescribmentioning
confidence: 99%
“…result in LCO. This reminds one of the famous oscillatory flap solutions of Tijdeman [14,15] in transonic flow, where a steady strong shock will result in small (unsteady) shock excursion (type A) and weak shocks will result in large-amplitude (unsteady) shock excursions (types B and C − Morph Angle Effect The flutter/LCO speeds increases with increased Γ, in spite of M = 0.9 or 0.95. Increasing Γ will enhance the wing torsional stiffness, leading to the large flutter dynamic pressure (see Table 1).…”
Section: Continuous Dynamic Simulation Of a Moving Flap With Prescribmentioning
confidence: 99%
“…In this work we are concerned essentially with treating the shock using spectral methods. One may modify the spectral scheme to be implicit in time, and compare the results to an implicit scheme using the Murman-Cole switch [3], or the Engquist-Osher one [16]. …”
Section: Discretization In Time and Space (A) Discretization In Timementioning
confidence: 99%
“…. -3 -Since the Shuman filter may reduce the accuracy of the scheme, we removed the two filters mentioned above for a few iterations (1)(2)(3)(4)(5)(6)(7)(8)(9)(10) It turns out that we got the location of the shock very accurately, regardless of the number of iterations for which we have removed the two filters applied until reaching a steady state. The location of the shock agrees with that prescribed by the E -0 scheme using a grid which is four times finer in the E -0 scheme.…”
mentioning
confidence: 99%
“…During the last few years many numerical calculations using these equations have been presented (see [1], [2], [6], [8], [12] and the bibliographies in these papers).…”
mentioning
confidence: 99%
“…In this way it has been possible to avoid most nonphysical shocks and to keep the shock front sharper than in the case of uniform schemes. Variants of the Cole-Murman difference scheme [12] have been the basis for many successful calculations (see [1], [6], [8]). However, in [6] it is pointed out that the Cole-Murman scheme does admit entropy violating shocks as solutions, and furthermore in [1] and [8] instabilities are reported even if the schemes should be stable according to linear stability analysis.…”
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confidence: 99%