Il est intéressant de chercher qu’elle est l’ampleur occupée par les Mille et une nuits dans l’œuvre d’Aragon, le Fou d’Elsa, et de savoir ce que le poète français a pris de ce livre arabe afin de créer son long poème le Fou d’Elsa. Car nous pensons que ce n’est pas par un pur hasard que nous trouvons dans ces deux livres, des noms, des symboles, des éléments semblables, malgré la différence de langue, puisque l’un de ces ouvrages a été rédigé en arabe, l’autre en français.

          Ce chef d’œuvre arabe, les Mille et une nuits, est une flamme qui a illuminé les chemins littéraires de générations d’écrivains, d’artistes occidentaux. Ce livre magique des arabes joue et jouera encore un rôle très important non seulement dans la littérature arabe et occidentale mais aussi internationale. Car il est l’un des rares livres qui fait rêver les lecteurs de toutes les nations dans un monde idéal loin de la banalité, de la réalité quotidienne.

This paper presents a study of two commercial hollow-cathode lamps (HCLs) with the intention of demonstrating different phenomena in gas discharges. The optogalvanic effect in both HCLs is produced by a laser diode radiated at the wavelength that corresponds to neon transition 1s2–2p2 at 659.89 nm. The voltage–current characteristics of the lamps are explained using a classical theory of hollow-cathode discharge, while the optogalvanic signal is treated as a small perturbation of the discharge current. For certain values of voltage self-sustained current oscillations are observed in one of the HCLs. In the same HCL laser-induced optogalvanic dumped oscillations are detected. A phenomenological model that includes the effective circuit parameters of the discharge is used to explain the oscillation characteristics.

Assessment of airfoil aerodynamic characteristics is essential part of any optimal airfoil design procedure. This paper illustrates rapid and efficient method for determination of aerodynamic characteristics of an airfoil, which is based on viscous-inviscid interaction. Inviscid flow is solved by conformal mapping, while viscous effects are determined by solving integral boundary layer equations. Displacement thickness is iteratively added to the airfoil contour by alternating inviscid and viscous solutions. With this approach efficient method is developed for airfoil design by shape perturbations. The procedure is implemented in computer code, and calculation results are compared with results of XFOIL calculations and with experiment. Eppler E387 low Reynolds number airfoil and soft stall S8036 airfoil are used for verification of developed procedure for Reynolds numbers 200000, 350000, and 500000. Calculated drag polars are presented in this paper and good agreement with experiment is achieved as long as small separation is maintained. Calculated positions of laminar separation, reattachment, and turbulent separation closely follow experimental measurement. The calculations are performed in relatively short time, which makes this approach suitable for low Reynolds number airfoil design.