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145 results on '"Afgan, Imran"'

3. Derivation of a Condensation Heat Transfer Model for Light Water Reactor Applications Using Machine Learning Techniques

Author

Albdour, Samah A., Addad, Yacine, Afgan, Imran, Chaari, Fakher, Series Editor, Gherardini, Francesco, Series Editor, Ivanov, Vitalii, Series Editor, Haddar, Mohamed, Series Editor, Cavas-Martínez, Francisco, Editorial Board Member, di Mare, Francesca, Editorial Board Member, Kwon, Young W., Editorial Board Member, Tolio, Tullio A. M., Editorial Board Member, Trojanowska, Justyna, Editorial Board Member, Schmitt, Robert, Editorial Board Member, Xu, Jinyang, Editorial Board Member, Shams, Afaque, editor, Al-Athel, Khaled, editor, Tiselj, Iztok, editor, Pautz, Andreas, editor, and Kwiatkowski, Tomasz, editor

Published
2024
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4. A CFD Approach to Mimic the Molten Corium-Concrete Interaction Phenomena: Effects of the Thermal Boundary Conditions

Author

Khurshid, Ilyas, Afgan, Imran, Addad, Yacine, Chaari, Fakher, Series Editor, Gherardini, Francesco, Series Editor, Ivanov, Vitalii, Series Editor, Haddar, Mohamed, Series Editor, Cavas-Martínez, Francisco, Editorial Board Member, di Mare, Francesca, Editorial Board Member, Kwon, Young W., Editorial Board Member, Tolio, Tullio A. M., Editorial Board Member, Trojanowska, Justyna, Editorial Board Member, Schmitt, Robert, Editorial Board Member, Xu, Jinyang, Editorial Board Member, Shams, Afaque, editor, Al-Athel, Khaled, editor, Tiselj, Iztok, editor, Pautz, Andreas, editor, and Kwiatkowski, Tomasz, editor

Published
2024
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39. Low speed aerodynamic characteristics of non-slender delta wing at low angles of attack

Author

Mohamed, Mohamed Ali, Afgan, Imran, Hefny Salim, Mohamed, Mohamed, Ibrahim K., Mohamed, Mohamed Ali, Afgan, Imran, Hefny Salim, Mohamed, and Mohamed, Ibrahim K.

Abstract

Low-speed wind tunnel experiments are conducted to study the aerodynamic performance of a half-span delta wing with 45° leading-edge sweep at subsonic flow regime. The experiments are carried out at a Reynolds number of 8.37 × 105, a free-stream Mach number of 0.1 and angles of attack up to 25°, in steps of 5°. The test model was designed with thirty-two pressure taps fixed on its surfaces (sixteen on each side). Multi-tube manometers were connected to these taps using long tubes to enable recording the pressure readings. Surface pressure distributions and aerodynamic characteristics were calculated at different span-wise locations along the non-dimensional chord-wise distance. Results exhibited that most lift on the studied wing is generated in the region close to the leading edge for all the studied incidence angles. Additional lift is created in the region close to the root chord rather than the tip chord, whereas drag forces increases from tip to root. This can be attributed to the formation of trailing edge vortexes due to the flow separation at the wing leading edge that produces more drag, hence suppressing lift. The study showed also that angle of attack increases the drag coefficient from tip to root, especially at high angle of attack, indicating unfavourable behaviour for manoeuvring. Moreover, the angle of attack increased the pitching moment coefficient up to 10° before it drops sharply until it reaches the tip of the wing model., Peer Reviewed

Published
2022

50. Orthogonal blade-vortex interaction on a helicopter tail rotor

Author

Filippone, Antonio and Afgan, Imran

Subjects
Turbulence -- Properties, Rotors (Helicopters) -- Properties, Vortex-motion, Aerospace and defense industries, Business
Abstract

The orthogonal blade-vortex interaction has been simulated using unsteady Reynolds-averaged Navier-Stokes equations with turbulence closure equations. The cases investigated are relative to an interaction between a lifting blade at a high angle of attack and an orthogonal vortex that travels either head-on or at 45 deg to the leading edge. The numerical simulations have been performed at a Reynolds number of Re = 1.85 x [10.sup.5] and a vortex Reynolds number of [Re.sub.v] = [10.sup.5.] The impact parameter is equal to 8, which places the interaction in the weak vortex regime. The initial axial velocity of the vortex is zero, but as the vortex travels a self-induced velocity causes the vortex to move axially well before the impact on the blade. The analysis is carried out on the vortex dynamics and on the blade aerodynamics. The data investigated include the behavior of the pressure field as the vortex advances, the distribution of vorticity, the interaction of the vortex with the blade and the wake, the flow separation at the blade surface, and the path lines of the flow. A comparison between the case of straight and oblique blade-vortex interaction indicates that the blade-vortex interaction pressure peak is less severe in the latter case. A comparison is also made for the corresponding aerodynamic force coefficients (lift and drag and normal force).

Published
2008

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