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DEPARTMENT OF AERONATICAL ENGINEERING COURSE SYLLABUS
AE 412: Compressible Flow
COURSE TITLE ENGLISH
CODE/NO
ARABIC CODE/NO.
CREDITS Th. Pr. Tr. Total Compressible Flow AE 412 214 ط ـه 3 1 - 3
Pre-requisites: AE 311, AE 302
Course Role in Curriculum (Required/Elective): Required Course Catalogue Description:
Principles from Thermodynamics. Conservation laws governing compressible flow. Generalized flow in nozzles. Isentropic flow. Normal shock relations. Nozzle flow with shock waves. Oblique shock waves and expansion waves. Normal and Mach reflection. Airfoils in supersonic flow. Shock expansion method. Thin airfoil theory. Unsteady gas dynamics. Moving shock waves and expansion waves. Shock tube theory. Aerodynamic facilities. Design of wind tunnels
Textbooks:
(Author, Title, Pub., year) John D. Anderson Jr., “Modern Compressible Flow with Historical Perspective”, 3rd edition, McGraw-Hill, 2004.
Supplemental Materials: John J. and Keith T., "Gas Dynamics”, 3nd Edition, Pearson International Edition, 2006.
W. Liepmann and A. Roshko, “Elements of Gasdynamics”, Dover Publications, 2002.
Saad, M. A., “Compressible Fluid Flow”, Prentice Hall, 2nd edition, 1993.
Compressible flow calculator:
www.dept.aoe.vt.edu/~devenpor/aoe3114/calc.html
Course Learning Outcomes:
1. Describe the generalized ideal compressible fluid flow equations; such as isentropic flow equations and normal shock relations using previous knowledge of fluid mechanics and thermodynamic while demonstrating the difference between compressible and incompressible flow
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Analyze isentropic flow in nozzles, including phenomena such as chocking, the utilization of a convergent-divergent nozzles.
3. Solve problems associate with the presence of standing shock waves within non-isentropic nozzle, while demonstrating supersonic inlets and supersonic diffusers.
4. Analyze nozzle flow problems s using packages like GAMBIT, FLUENT and TECPLOT and, validate computed results with analytical results.
5. Describe supersonic flow turning (or wall deflection) and associated oblique shock waves and expansion waves including shock detachment, Mach reflection. Shock-shock intersection shock-expansion interaction. Also, perform numerical simulations for oblique shock problems using FLUENT, analyze using TECPLOT package and validate computed results with analytical results.
6. Obtain the lift and the drag coefficient of simple airfoils in supersonic flow using shock
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Topics to be Covered: Duration in
Weeks 1. Review of Thermodynamics and Fluid Mechanics and Introduction to
Compressible Flow
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2. One-Dimensional Isentropic Flow 1
3. Nozzle Flow with shock waves 2
4. Oblique Shocks and Isentropic Waves 2
5. Lift and Drag in Supersonic Flow 2
6. Unsteady One-Dimensional Compressible Flow 1
7. Contemporary issues 1
8. Design of Supersonic Wind Tunnels (Course Capstone Design) 4
Key Student Outcomes addressed by the course: (Put a sign)
(a) an ability to apply knowledge of mathematics, science, and engineering
(b) an ability to design and conduct experiments, as well as to analyze and interpret data (c) an ability to design a system, component, or process to meet desired needs within realistic
constraints such as economic, environmental, social, political, ethical, health and safety, manufacturability, and sustainability
(d) an ability to function on multidisciplinary teams
(e) an ability to identify, formulate, and solve engineering problems
(f) an understanding of professional and ethical responsibility
(g) an ability to communicate effectively
(h) the broad education necessary to understand the impact of engineering solutions in a global, economic, environmental, and societal context
(i) a recognition of the need for, and an ability to engage in life-long learning
(j) a knowledge of contemporary issues
(k) an ability to use the techniques, skills, and modern engineering tools necessary for engineering practice.
Key Student Outcomes assessed in the course: (c), (e) and (j)
Instructor or course coordinators: Dr. Amjad Pasha Last updated: May 2015
expansion method and approximate methods of Prandtl-Meyer function and thin airfoil theory
7. Derive the moving shock wave and expansion wave’s relations to describe unsteady devices such as shock tubes and shock tunnels.
8. Design supersonic wind tunnel (course design project):
Design convergent divergent nozzle using method of characteristics with tool MATLAB
Test your nozzle Mach number distribution using FLUENT.
Determine the suggested minimum tunnel compression ratio, which establishes the minimum allowable operating pressure.
Determine the mass flow rate
Determine the required heating to prevent liquefaction.
9. Demonstrate the ability to engage as a team member in a course capstone design
