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HW7_solutions0
Course: AAE 364, Spring 2012School: Purdue
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Purdue - AAE - 364
Purdue - AAE - 364
AAE 364 Control Systems AnalysisProblem Set 8Professor Inseok HwangSchool of Aeronautics and Astronautics, Purdue UniversitySpring 2012Issued 3/23; Due 03/30Reading Assignment: Sections 6 - 9 in Chapter 6.ProblemsConsider the unity feedback system
Purdue - AAE - 364
AAE 364 Control Systems AnalysisProblem Set 9Professor Inseok HwangSchool of Aeronautics and Astronautics, Purdue UniversitySpring 2012Issued 4/6; Due 4/13Reading Assignment: Sections 1-2 of Chapter 7.ProblemsSolve B-7-3 and B-7-4 in Chapter 8.Pr
Purdue - AAE - 364
Introduction to SISO tool1. What is SISO tool?Matlab toolboxGraphical User Interface (GUI) to design single input / single output (SISO) compensatorsGraphically interacts with root locus, Bode, and Nichols plots of the open loop systemC: compensator
Purdue - AAE - 364
AAE 364: Control Systems AnalysisControl System Design Using Root LocusProfessor: Inseok HwangSpring 2006Improving Transient Time ResponseFigure 1a. Sample root locus,showing possibledesign point viagain adjustment (A)and desired designpoint th
Purdue - AAE - 364
Three of the infinite possible lead compensatorsolutionsImproving Steady State Time ResponseImproving steady state response:Adding poles at/near the origin1. PI-controller:2. Lag compensator:xx6Improving Steady-State Response:PI-controllerI-co
Purdue - AAE - 364
Control Systems AnalysisAAE 364Instructor: Prof. Inseok HwangSimplified description of a control systemExamples: ElevatorPhotos courtesy of United Technologies Otis Elevator.Examples: AircraftB777F22 RaptorExamplesAir traffic managementFormatio
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 364
Purdue - AAE - 334
Approx. MachNumber RangeM < 0.3DescriptionTheoryIncompressiblePotentialFlowIncompressibleThinAirfoilTheorySubsonicSubsonicLinearTheoryTransonicTSD eqn,FullPotentialSupersonicShockExpansionTheory1.2 < M < 5SupersonicSupersonicLine
Purdue - AAE - 334
Pb/P000.10.20.30.40.50.60.70.80.9100.10.20.3Shock atExitShock in nozzle0.4At/Ae0.50.6Choked(subsonic)OverexpandedNozzle Operating Map ( = 1.4)0.70.8UnderexpandedPerfectlyExpandedSubsonic(unchoked)0.91
Purdue - AAE - 334
Nozzle Flow AnalysisCase Descriptions: (i) Subsonic unchoked flow (ii) Subsonic choked flow (iii) Shock in the nozzle (iv) Shock at the nozzle exit (v) Overexpanded flow (shocks outsidenozzle) (vi) Perfectly expanded flow (vii) Underexpanded flow
Purdue - AAE - 334
Purdue - AAE - 334
Purdue - AAE - 334
AAE 334 Spring 2012Problem Set 6Due: Friday 3/2/20121. (This problem is worth two problems.)Consider a Mach 2 air stream at a pressure of 1 atm owing over a diamondshaped airfoil. The airfoil has a thickness to chord ratio t/c = 0.05, and themaximum
Purdue - AAE - 334
The tasks for this problem are as follows:(a) Download the data les. Plot the geometry of the airfoil using the x/c and y/cdata given in the les. (Make the scaling of the x and y axes the same so thatthe airfoil has its true shape. This can be done wit
Purdue - AAE - 416
AAE 416FINAL EXAMMay 3, 20107-9PMOpen Book/Notes1) A circular cross-section tube of length 2m and diameter 1cm, is subjected to a pressuredifference of 2 Pa. The fluid coming out the low pressure end of the tube is measured at49cc in one second and
Purdue - AAE - 416
AAE 416 Exam 1 Tues March 2, 2010 Open Book/Notes1) Consider a channel flow between two parallel walls at y=0 and y=2. The velocity in the x direction (parallel to the walls) is u=3*(y^2/4-1). Assume the viscosity and density are =1.5 and =0.2 , respecti
Purdue - AAE - 416
AAE 416Exam 2Tues April 20, 2010Open Book/Notes1) Consider a channel flow between two fixed parallel walls at y=0 and y=h. Initially thevelocity is 0 everywhere. At t=0 a constant pressure gradient is imposed dp/dx=-10 * .a. Write down the PDE + bou
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
AAE 416Final ProjectDue Mon May 3(first draft this may need some refinement later on)Consider the airfoil of HW 7 and 8At an angle of attack of 5deg and a chord Reynolds number of 3e6 (as in HW8)a) Find the solution according to XFOIL.b) Write a He
Purdue - AAE - 416
H omework 1Due: Fri Jan 221) Solve for the fully developed laminar f low in an annular space between an i nner cylinder of radius R1 and an outer cylinder of radius R2, driven by a p ressure gradient along the tube axis. Find the velocity profile , u(r)
Purdue - AAE - 416
Purdue - AAE - 416
AAE 416HW2January 28, 20111) You are given a prescribed flow field in the first quadrant of the x,y plane, x>0, y>0.(we assume planar symmetry for simplicity):u= 3 xv=-3 yp=-9 (x^2+y^2) : The pressure is measured from the origin (x=y=0).T=300 + 20
Purdue - AAE - 416
Purdue - AAE - 416
% Homework 4 Problem 1% Unsteady flow in a simple planar channel% The case done is fixed walls, constant pressure gradient,% and 0 initial conditionsH=0.01;nu=1.453e-5;dpdxbyrho=0.;Ny=81;dy=H/(Ny-1);y=linspace(0,H,Ny);tend=5;Nt=10000;dt=tend/(
Purdue - AAE - 416
Displacement thickness as a function of X for the two flowsMomentum thickness as a function of X for the two flowsWall Shear Stress as a function of X for the two flows
Purdue - AAE - 416
AAE 416 Spring 2010 - HW 6 Solutions1. The MATLAB code used to reproduce Fig 4-24 in White isattached below.% HW 6 Solution% Use Thwaites' method to perform boundary layer calculation% for flow past a circular cylinderR = 1.0; % radius of the circul
Purdue - AAE - 416
AAE 416 - Homework 7Solutions1 (a) The plots shown below were generated by running inviscid.m for various values ofthe variable aoa. The results are shown for angles of attack -10, -5, 0, +5, +10 degreesrespectively.Figure 1: Angle of attack : -10 de
Purdue - AAE - 416
4/19/10 8:51 AM%%%%%%\roger.ecn.purdue.edu\vayyaswa\pchome\.pcprefs\Desktop\main.m1 of 2main.m : M-file to use inviscid.m and Thwaites.mto compute boundary layer parametersand then use various correlation methodsto predict the transition locat
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416
Purdue - AAE - 416