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| AERO0001-1 | Aerodynamics, 30h Th, 30h Exc
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| Duration : | 30h Th, 30h Pr |
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| Credits/ECTS : |
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| Holder(s) : | Jean‑André Essers |
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| Substitute(s) : | Grigorios Dimitriadis |
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| Language : | Langue française |
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| Course contents : | General description
This course presents the following most fundamental aspects of low speed (incompressible flow) and high speed aerodynamics.
- Incompressible potential flow over lifting airfoils : law of Kutta and Joukowsky. Lift, drag and polar. Aerodynamic centre and pitching moment. Unsteady building up of circulation. Airfoil calculation by conformal mapping. Numerical panel method generalized to compressible subsonic flow.
- Laminar incompressible boundary layers. Prandtl equations. Self-similar velocity profiles and exact solutions of Blasius and Falkner-Skan. Calculation by integral methods (Von Karman-Pohlhausen). Stability and transition. Factors influencing the transition turbulence, the boundary layer separation and the airfoil stall. Compressible boundary layers. Reynolds analogy. Kinetic heating in high speed aerodynamics. Stanton number. Recovery temperature. Crocco boundary layers for a unit Prandtl number. The transformation of Howarth and Dorodnitsyn.
- The calculation of lifting wings. Modelling of the vortex sheet. Induced drag. The optimal wing. The Prandtl lifting line theory for wings with a large aspect ratio.
- Calculation of thin airfoils and slender bodies by a small disturbance theory : linear subsonic and supersonic regimes, transonic flow, the Prandtl-Glauert approach for the calculation of subsonic airfoils and wings. The Ackerett's simplified method of characteristics for airfoils in a supersonic flow. The optimal airfoil. Yawed wings.
- Calculation of supersonic potential flow by the non-linear method of characteristics (the lattice method). Supersonic flow over airfoils : shock-expansion method, isentropic approximation, Busemann's method.
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| Course objective : | Aim of the course
The analytical or numerical study of gas flows over bodies; evaluation of aerodynamic forces and moments. Application to the aerodynamic calculation of airplane wings. |
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| Prerequisites : | Required background
- Properties of functions with one complex variables. Residuals Laurent series expansions. Conformal mapping (see course MATH007-0 Analyse mathématique II - Prof. Schneiders)
- Cours MECA025-0 Mécanique des fluides - Prof. Essers.
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| Workshops : | Exercise sessions and laboratories
They are organized during the second quadrimester. They are made of exercise sessions (during the first 8 weeks) and of works by groups of 3 or 4 students. These group works consist in a round tunnel laboratory and in the writing of a computer programme for wing calculation by the lifting line theory.
One day is devoted to the visit of a high level research center in fluid dynamics (Von Karman Institute at Rhode-Saint-Genèse). |
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| Organization : | Organisation
during the first 8 weeks of the second quadrimester, as described in the general course schedule. |
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| Written notes : | Course notes
Made photocopies taken out of different text books.
Contact Prof. Essers |
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| Assessment : | Evaluation
Oral exam on the theory : 50%
Written exam : 30%
Group works : 20%
The exams are organized during the sessions of June and September. |
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| Contacts : | Contact
Teacher : Prof. J.-A. ESSERS
Tél. +32(0)4 366 9359
e-mail : JA.Essers@ulg.ac.be
Assistant : M. Mario BASILE
Tél. +32(0)4 366 9439
e-mail : M.Basile@ulg.ac.be
Secretary : Mme Leroy (monday and thursday)
Tél. +32(0)4 366 9353
Fax +32(0)4 366 9136
http://www.ulg.ac.be/aerodyn |
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