Course Meeting Times
Lectures: 3 sessions / week, 2 hours / session
Labs: 1 session / week, 2 hours / session
16.100 is a course about aerodynamics, i.e. the study of the flow of air about a body. In our case, the body will be an airplane, but much of the aerodynamics in this course is relevant to a wide variety of applications from sail boats to automobiles to birds. 16.100 has a set of learning objectives which you should always keep in your thoughts as the semester progresses. The entire course is structured to (hopefully) help you achieve these objectives. Specifically, students graduating from 16.100 will be able to:
- Formulate and apply appropriate aerodynamic models to predict the forces on and performance of realistic three-dimensional configurations;
- Assess the applicability of aerodynamic models to predict the forces on and performance of realistic three-dimensional configurations and estimate the errors resulting from their application;
- Perform a computational and experimental aerodynamic analysis and design together with members of a team.
Comment on Aerodynamic Models
An aerodynamic model is simply a method to estimate the aerodynamic performance (e.g. the lift or drag) of an object (e.g. an airfoil, wing, or airplane). An aerodynamic model could be based on experiments, computation or theory but often lies in the middle ground using a judicious combination of all three approaches. For example, an aerodynamic model might be incompressible thin airfoil theory; or, an aerodynamic model might be incompressible thin airfoil theory with a skin friction drag estimate; or, an aerodynamic model might be a wind tunnel experiment at low speed with theoretical corrections for wall effects and higher speed flight conditions. In 16.100, a variety of aerodynamic models will be covered which could then be combined to produce a more complex model as dictated by the application. Specific aerodynamic models that students will encounter may vary slightly from semester-to-semester but will generally include: 2-D/3-D potential flows (incompressible to supersonic) including panel and vortex lattice methods; boundary layer methods including the effects of transition and turbulence; coupled inviscid-viscous models; 2-D/3-D Euler and Navier-Stokes computations; wind tunnel testing.
Students graduating from 16.100 will be able to:
- Apply flow similarity, non-dimensional coefficients such as the lift and drag coefficient, and non-dimensional parameters such as the Mach number and Reynolds number in aerodynamic modeling of realistic configurations (homework, team project reports, exams).
- Apply integral momentum conservation and streamline curvature arguments to explain the relationship between flow turning, the generation of lift on an airfoil, and the subsequent loss of lift upon stall (homework, exams).
- Explain the sources of friction, induced, wave, and pressure drag (homework, exams).
- Explain the motion and deformation of a fluid element using kinematics including the definition of shear strain, normal strain, vorticity, divergence, and the substantial derivative (homework, exams).
- (a) Explain the concept of a laminar boundary layer including the definition of the displacement thickness, the momentum thickness, and the skin friction coefficient, and the importance of the Reynolds number in determining the presence and behavior of a boundary layer (homework, exams), and (b) Apply the integral boundary layer equations to describe the qualitative evolution of a laminar boundary layer including separation and to quantitatively estimate the local thickness and skin friction (homework, exams).
- Explain the onset of turbulence in a boundary layer (i.e. transition) and the qualitative effects of turbulence on boundary layer evolution including the impact on velocity profile, skin friction coefficient, boundary layer thickness, and separation (homework, exams).
- Estimate friction drag on 2-D and 3-D configurations by decomposing the geometry into patches and assuming appropriate local values of skin friction coefficients including the possibility of laminar or turbulent boundary layer conditions (homework, team project reports, exams).
- Explain the basic elements (see Comment on basic elements below) of 2-D panel methods and 3-D vortex lattice methods (homework, exams).
- Explain the basic elements of coupled inviscid-viscous models for 2-D airfoils (homework, exams).
- (a) Explain the basic elements of thin airfoil potential flow models for 2-D subsonic and supersonic flows (homework, exams), and (b) Apply thin airfoil potential flow models to estimate the forces on airfoils in 2-D subsonic and supersonic flows (homework, written exam).
- (a) Explain the basic elements of the lifting line model for high aspect ratio wings (homework, exams), (b) Describe the dependence of lift and induced drag on geometry and performance parameters (e.g. aspect ratio, twist, camber distribution, wing loading, flight speed, etc.) using the lifting line model (homework, exams), and (c) Apply the lifting line model to estimate lift, induced drag, and roll moments on high aspect ratio wings (homework, written exam).
- Explain the basic elements of the finite volume approximation to the compressible Euler and Navier-Stokes equations (homework, exams).
- (a) Explain the relationship between sound propagation and shock waves (exams), (b) Describe the qualitative change in flow conditions (Mach number, pressure, temperature, total pressure, etc.) across shocks and expansion fans (exams), (c) Estimate the change in flow conditions across shocks and expansion fans using shock-expansion theory (homework, written exam) (d) explain transonic drag rise including the critical Mach number and the use of wing sweep to delay drag rise (homework, exams).
- Explain the use of wind tunnel testing in aerodynamic modeling focusing on the importance of flow similarity in scale testing and on the typical corrections (e.g. wall corrections) required to simulate flight conditions (homework, team project reports, exams).
- Assess the ability and limitations of an aerodynamic model to estimate lift and drag (separated into friction, induced, wave, and pressure drag contributions) for a specific application (homework, team project reports, exams).
- Contribute substantially as an individual to the design and execution of a computational and experimental aerodynamic analysis of realistic 3-D configuration together with members of a team (team project reports).
Comment on Basic Elements
The basic elements of a model includes the critical features which produce a valuable predictive method. For example, consider a 2-D panel method. The basic elements would include: all of the underlying assumptions of incompressible, potential flow; the discretization of an airfoil geometry into a set of line segments on which potential flow solutions are distributed; the satisfaction of flow tangency at panel control points; the global influence of an individual panel on all other panels; the imposition of the Kutta condition; etc. However, the basic elements would not include the more detailed aspects of the method which while important, are not critical to understanding how the method works. In the 2-D panel method example, it would not include the details of the calculation of the influence coefficient of a general source/vortex/doublet panel; the solution of the large linear system of equations; etc.
General Pedagogy and Assessment Strategy
The skills to be gained in this course are basically of three types:
- Quantitative or Analytical Skills
- Qualitative or Conceptual Skills
- Integrative Skills
For each skill, a different pedagogical and assessment strategy is used. Analytical skills are taught and/or assessed through the textbook reading, homework assignments, the written exams, and, to a lesser extent, the team project. Conceptual skills are taught and/or assessed through in-class conceptual questions, the oral exams, and, to a lesser extent, the project and the written exams. Integrative skills are taught and/or assessed through the project and written exams, to a lesser extent, the homework and oral exams.
Grades will be based upon the following weightings:
|Exams (The Written and Oral Part of each Exam are 15% each)||60%|
|Project (Assignments are 10% Total and the Design Report is 10%)||20%|
Roughly, the final letter grades will be assigned as follows:
Reading, Homework Assignments and Late Policy
Students are expected to complete assigned reading prior to discussion of the topics in class. The homework will be largely based on the assigned reading material with some problems based on difficult material from previous reading and lectures. The homeworks are individual efforts; while students are encouraged to discuss homework problems with each other, what is turned in must represent the student’s own understanding of the material.
Past-due homework will generally not be accepted. For unusual circumstances, exceptions could be permitted.
Team Projects and Labs
Students will participate in an integrative team project developed with The Boeing Company concerning the aerodynamic analysis and design of a Blended-Wing Body (BWB) aircraft. During the first two months of the semester, students will complete assignments to learn the basic skills necessary to analyze the BWB aircraft. In the final month of the semester, teams of approximately three students will complete a redesign of the BWB. These teams will be responsible for completing the design project and documenting their results in a design report.
The weekly Labs on Wednesdays from 3-4 pm and 4-5 pm will be held in the electronic classroom. Students will be assigned to one of the sessions on the first day of class based as much as possible on preference. During the first two months of the semester, the staff will guide the students through the completion of the assignments. These assignments will be completed in pairs that the students can select, however, the pairs must be different for each of the assignments. Then, in the final month, the Labs will be dedicated to the teams working on the design project with staff in attendance to provide guidance. The students will be assigned to the design teams by the staff. Attendance will be taken for all lab sessions.
The total individual student grade on the design project will be based on a team project grade (20%) and an individual contribution grade (80%). The individual contribution will be assessed from three sources:
- Instructor interactions with the teams throughout the semester including work session attendance,
- Written (emailed) evaluations after each milestone by all team members of the contributions of each team member (including self-evaluations), and
- Delineation within the written reports of an individual’s contributions.
The exams will have a take-home written portion and an oral portion. Students will have a few days to complete the written exam (see the calendar section for the specific sessions, the take-home exams will be distributed and due). The written exams will then be followed by an oral exam. The oral exams will be largely, though not exclusively, based on the questions from the written exam. The oral exam will be 30 minutes in length, conducted by Prof. Darmofal. The written exam questions will be similar to homework questions focusing mainly on quantitative and integrative abilities. The oral exams will focus on conceptual understanding.