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### HW24

Course: AAE 334, Fall 2010
School: Purdue
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Word Count: 169

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334 AAE Fall 2011, Homework 24 Due Wednesday, November 9 at the beginning of class. 1. Using an oblique shock chart, answer these questions: a. What is the turning angle in degrees for an upstream Mach number of 2 and a wave angle of 40 degrees? b. What is the upstream Mach number for an oblique shock with turning angle of 15 degrees and wave angle of 53 degrees? c. What is the wave angle in degrees for the weak...

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334 AAE Fall 2011, Homework 24 Due Wednesday, November 9 at the beginning of class. 1. Using an oblique shock chart, answer these questions: a. What is the turning angle in degrees for an upstream Mach number of 2 and a wave angle of 40 degrees? b. What is the upstream Mach number for an oblique shock with turning angle of 15 degrees and wave angle of 53 degrees? c. What is the wave angle in degrees for the weak shock solution for an oblique shock at Mach 2.25 and turning of angle 10 degrees? d. What is the wave angle in degrees for the strong shock solution for an oblique shock at Mach 2.25 and turning angle of 10 degrees? 2. Using the Matlab functions such as OS_tw, OS_mw, OS_mt, or OS_mt_str, and the normal shock functions as needed, compute and plot the static pressure on the bottom of a flat plate airfoil in a Mach 2 flow versus angle of attack for 0 10 o . Plot in units of p 1 . Hand in hardcopies of your Matlab code and plot.
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Purdue - AAE - 334
AAE 334 Fall 2011, Homework 24 SOLUTIONS Due Wednesday, November 9 at the beginning of class. 1. Using an oblique shock chart, answer these questions: a. What is the turning angle in degrees for an upstream Mach number of 2 and a wave angle of 40 degrees?
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 25 Due Wednesday, November 16 at the beginning of class. 1. Compute manually (not using the PM_ Matlab functions) the pressure after a 10 degree expansion corner if the upstream flow is at Mach 2 and pressure of 100 kPa. T 2. C
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 25 SOLUTIONS Due Wednesday, November 16 at the beginning of class. 1. Compute manually (not using the PM_ Matlab functions) the pressure after a 10 degree expansion corner if the upstream flow is at Mach 2 and pressure of 100 k
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 26 Due Friday, November 18 at the beginning of class. Use the shock-expansion method to compute the lift and drag coefficients for the airfoil sketched below in a Mach 1.8 flow. Chord length is c and maximum thickness is at the
Purdue - AAE - 334
Nov. 22, 2011AAE 334 Fall 2011, Homework 26 Due Friday, November 18 at the beginning of class. Use the shock-expansion method to compute the lift and drag coefficients for the airfoil sketched below in a Mach 1.8 flow. Chord length is c and maximum thick
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 27 Due Monday, November 21 at the beginning of class. Derive an expression for the mass flow through a choked throat of a converging-diverging nozzle based on: knowledge of upstream stagnation condition conditions po and To , t
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 27 SOLUTIONS Due Monday, November 21 at the beginning of class. Derive an expression for the mass flow through a choked throat of a converging-diverging nozzle based on: - knowledge of upstream stagnation condition conditions p
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 28 Due Monday, November 28 at the beginning of class. 1. Solve for the mass flow through a choked throat of a converging-diverging nozzle with: - upstream stagnation condition conditions p o = 1MPa and T o =300K throat area of
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 28 SOLUTIONS Due Monday, November 28 at the beginning of class. 1. Solve for the mass flow through a choked throat of a converging-diverging nozzle with: - upstream stagnation condition conditions po = 1MPa and To =300K - throa
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 29 Due Wednesday, November 30, beginning of class. 1. A converging-diverging nozzle operates with an upstream stagnation pressure of 12 atmospheres. The ratio of exit area to throat area is 7.8. If the gas is calorically perfec
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 29 Solutions1. A converging-diverging nozzle operates with an upstream stagnation pressure of 12 atmospheres. The ratio of exit area to throat area is 7.8. If the gas is calorically perfect air, determine the back pressures at
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 39 Due Friday, December 2, beginning of class. Air flows through a converging diverging nozzle in a steady flow. The air entering the nozzle has stagnation conditions po 150 psi and To 500R . 1. The flow upstream of the throat
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 30 SOLUTIONS Due Friday, December 2, beginning of class. Air flows through a converging diverging nozzle in a steady flow. The air entering the nozzle has stagnation conditions po 150psi and To 500R . 1. The flow upstream of th
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 31. Due Monday, December 5 at the beginning of class.In Chapter 11, near Equation 11.13, Anderson writes, &quot;From Equation (8.33), we havea ao 2 2 12V2 ao 22 12u22v2(11.13)&quot;a 2 o 1 2 x y Yet Equation (
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 31 SolutionOn page 662, Anderson writes, &quot;From Equation (8.33), we havea a 2 2 o 12V a 2 2 o 12u2v22 a 2 x y 2 2 o 1 (11.13)&quot;Yet Equation (8.33) is from a one-dimensional flow analysis and thus is used imprope
Purdue - AAE - 334
AAE 334, Fall 2011 Homework 32. Due Friday, December 9 at the beginning of class.Solve for critical Mach number as an angle of attack for the following low-speed airfoil pressure data. Use the Prandtl-Glauert rule. List for each case the spanwise positio
Purdue - AAE - 334
AAE 334, Fall 2011 SOLUTION Homework 32. Due Friday, December 9 at the beginning of class.Solve for critical Mach number as an angle of attack for the following low-speed airfoil pressure data. Use the Prandtl-Glauert rule. List for each case the spanwis
Purdue - AAE - 334
AAE 334 Fall 2011 Mid-term #1NAME:_SOLUTIONS_One original hand-written formula sheet permitted. Calculator permitted. Phones, IPods, etc. turned off. Do your own work. Present neat and organized work leading to the correct answer for full credit. 1. [15
Purdue - AAE - 334
Midterm 2, AAE 334, Fall 2011 Name:_SOLUTION_ Exam ends at 10:20am regardless of starting time. All questions are for steady flows of air acting as a calorically perfect gas. Two original hand-written double-sided 8.5x11 inch formulas sheets are permitted
Purdue - AAE - 334
AAE 334 Fall 2011Quiz 1.SOLUTIONSCircle True or False or neither of the two. Points: +1 for correct, -1 for incorrect, 0 for blank. Ambiguous answers are scored as incorrect answers. All questions concern the classical thin airfoil theory which we have
Purdue - AAE - 334
AAE 334 Fall 2001, Quiz #2 The most important things to remember about steady normal shocks are covered on this quiz. The table below concerns the steady flow of air as an ideal gas through a normal shock wave. +1 point for correct answer, 0 for a blank,
Purdue - AAE - 334
AAE 334 Fall 2011, Quiz #3Name:_SOLUTIONS_Compressible, steady, perfect-gas, quasi-one-dimensional flow of air in a convergingdiverging nozzle. +1 point for correct answer, 0 for a blank, and -1 for wrong answer.Write the correct choice of &lt;1, =1, of &gt;
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Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 1Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 8/26; Due 9/2Reading Assignment:Chapter 1. Paper &quot;Eighty Years of Flight Control: Triumphs and Pitfalls of t
Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 2Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 9/2; Due 9/9Reading Assignment:Chapter 1 and the class material for the Laplace Transform.Problems1. Obtai
Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 3Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 9/9; Due 9/16Reading Assignment:Class material for the Laplace Transform; Sections 1,2,3, and 7 in Chapter 2
Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 5Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 9/23; Due 9/30Reading Assignment:Section 1 - 5 in Chapter 5.Problem 1Solve B-5-3, B-5-4, B-5-7, B-5-20, B-
Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 8Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 10/28; Due 11/07Reading Assignment: Sections 1-9 in Chapter 6.ProblemsSolve B-6-18, B-6-21, B-6-22, B-6-23,
Purdue - AAE - 364
AAE 364 Control Systems Analysis Problem Set 10Professor Inseok Hwang School of Aeronautics and Astronautics, Purdue University Fall 2011 Issued 12/21; Due 12/02Reading Assignment: Sections 3-9 in Chapter 7.ProblemsSolve B-7-8, B-7-12, B-7-18, B-7-19,
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Purdue - CS - 177
Chapter 1: Introduction to Computer Science andMedia Computation1Chapter Learning Objectives What is Computer Science all about? What do computers really understand,and where do Programming Languagesfit in? Media Computation: Why digitizemedia?
Purdue - CS - 177
Chapter 2: Introduction to Programming1Chapter Learning Objectives2Installation Installing JES and starting it up Go to http:/www.mediacomputation.org and get the version of JES foryour computer.If you know that you have a Java compiler (e.g., a J
Purdue - CS - 177
Chapter 3: Modifying Pictures using Loops1Chapter Learning Objectives2We perceive light differently fromhow it actually is Color is continuous Visible light is in the wavelengths between 370 and 730 nanometersThats 0.00000037 and 0.00000073 meters
Purdue - CS - 177
Chapter 4: Modifying Pixels in a Range1Chapter Learning Goals2Reminder: Pixels are in a matrix Matrices have two dimensions: A height and a width We can reference any element in the matrix with (x,y) We refer to those coordinates as index numbers o
Purdue - CS - 177
Chapter 5: Advanced Picture Techniques1Chapter Objectives2Color replacement You remember the increaseRed recipe:def increaseRed(picture):for p in getPixels(picture):value=getRed(p)setRed(p,value*1.2) And the function to calculate the distance be
Purdue - CS - 177
Chapter 6: Modifying Sounds Using Loops1Chapter Objectives2How sound works:Acoustics, the physics of sound Sounds are waves of airpressure Sound comes in cycles The frequency of a wave isthe number of cycles persecond (cps), or HertzComplex so
Purdue - CS - 177
Chapter 8: Making Sounds by Combining Pieces1Chapter Objectives2Making more complex sounds We know that natural sounds are often thecombination of multiple sounds. Adding waves in physics or math is hard. In computer science, its easy! Simply add