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### HW15

Course: AAE 334, Fall 2010
School: Purdue
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Word Count: 134

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334, AAE Fall 2011, Homework 15 Due Monday, September 17, at the beginning of class. Work the problems in the system of units in which they are posed. Show units throughout your work for #2 through #4. No partial credit on such easy problems. 1. What is the specific gas constant (as given by the textbook for a and b) for air in units of J a. Joules per kilogram per degree Kelvin? kg K ft lb b. per...

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334, AAE Fall 2011, Homework 15 Due Monday, September 17, at the beginning of class. Work the problems in the system of units in which they are posed. Show units throughout your work for #2 through #4. No partial credit on such easy problems. 1. What is the specific gas constant (as given by the textbook for a and b) for air in units of J a. Joules per kilogram per degree Kelvin? kg K ft lb b. per Foot-pounds slug per degree Rankine? slug oR ft lbf c. Foot-pounds per pound mass per degree Rankine? lbm oR 2. Air at 101 kPa pressure and temperature of 23 Celcius has what density? 3. Air at 14.7 psi pressure and temperature of 72 Fahrenheit has what density in slugs per cubic feet? 4. Air at 3.7 psi and temperature of -50 Fahrenheit has what density in pound-mass per cubic foot?
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Purdue - AAE - 334
AAE 334, Fall 2011, Homework 15 SOLUTIONSDue Monday, September 17, at the beginning of class. Work the problems in the system of units in which they are posed. Show units throughout your work for #2 through #4. No partial credit on such easy problems. 1.
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 16 Due Wednesday, September 19, at the beginning of class.We will see shortly that for compressible flow of an ideal gas, the ratio of stagnation (or total) pressure to static pressure is related to Mach number and gas proper
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 16 SOLUTION Due Wednesday, September 19, at the beginning of class.We will see shortly that for compressible flow of an ideal gas, the ratio of stagnation (or total) pressure to static pressure is related to Mach number and g
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 17 Due Monday, October 24, at the beginning of class.1. How fast must air at 70 Fahrenheit and 14.7 psi static pressure move for Bernoulli's equation to give a 10% error in total pressure? A supply tank for a supersonic wind
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 17 SOLUTION Due Monday, October 24, at the beginning of class.1. How fast must air at 70 Fahrenheit and 14.7 psi static pressure move for Bernoulli's equation to give a 10% error in total pressure? 1 1 p 2 1 p Bernoulli: po,
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 18 Due at beginning of lecture, Wednesday, October 26, 2011Consider the steady flow in the test section of a Mach 4 wind tunnel. The stagnation temperature is 20oC. For some optical diagnostic techniques, such as the Laser Di
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 18 SOLUTIONS Due at beginning of lecture, Wednesday, October 26, 2011Consider the steady flow in the test section of a Mach 4 wind tunnel. The stagnation temperature is 20oC. For some optical diagnostic techniques, such as th
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 19 Due at beginning of lecture, Friday, October 28, 2011A series of Matlab functions has been created to aid compressible flow students. They can be downloaded from Blackboard as one zipped file. A users guide is included in
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 19 SOLUTIONS Due at beginning of lecture, Friday, October 28, 2011A series of Matlab functions has been created to aid compressible flow students. They can be downloaded from Blackboard as one zipped file. A users guide is in
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 20 Due at beginning of lecture, Monday, October 31, 2011Consider a pitot-static probe in a supersonic flow. The streamline on centerline passes through a normal shock before stagnating isentropically. The streamline adjacent
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 20 SOLUTIONS Due at beginning of lecture, Monday, October 31, 2011Consider a pitot-static probe in a supersonic flow. The streamline on centerline passes through a normal shock before stagnating isentropically. The streamline
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 21 Due Wednesday, November 2 at the beginning of class. We wish to find the value of upstream Mach number for which the downstream Mach number is one half of the upstream Mach number. Perform this work numerically: 1. Use the f
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 21 SOLUTIONS Due Wednesday, November 2 at the beginning of class. We wish to find the value of upstream Mach number for which the downstream Mach number is one half of the upstream Mach number. Perform this work numerically: 1.
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 22 Due Friday, November 4 at the beginning of class. In lecture and Chapter 9 we are learning that the static thermodynamics through a steady oblique shock are the same formulae as for the steady normal shock if we use the upst
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 22 SOLUTIONSDue Friday, November 4 at the beginning of class. In lecture and Chapter 9 we are learning that the static thermodynamics through a steady oblique shock are the same formulae as for the steady normal shock if we us
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 23 Due Monday, November 7 at the beginning of class. The oblique shock chart in the test is difficult to read at times. You can create your own quite simply with use of the Matlab routines supplied on Blackboard this semester.
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 23 SOLUTIONDue Monday, November 7 at the beginning of class. The oblique shock chart in the test is difficult to read at times. You can create your own quite simply with use of the Matlab routines supplied on Blackboard this s
Purdue - AAE - 334
AAE 334 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 i
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,