AA210 HOMEWORK 1 SOLUTION
2015-2016 Spring
September 30, 2015
Problem 1.2 (10 points)
Assumptions: steady, incompressible, 2D ow
Under the assumptions, we can relate velocity to the streamline height from mass conservation. Using
continuity equation,
m =

AA 210A: Fundamentals of Compressible ow
Homework 3 Solutions
2015-2016
N. Harell, M. L. Wong
Problem 3.1 (10 pts)
Working in Cartesian coordinates and using index notation, we would like to prove the following vector identities :
1.
(F ) = F
We have :

AA 210: Fundamentals of Compressible ow
Homework 6 Solutions
2015-2016
N. Harell, M. L. Wong
Blasius ODE Problem (10 pts)
Use Mathematica or Matlab to reproduce the Blasius boundary layer solution presented in Chapter 8 section 8.5.1
and Figure 8.7.
In or

AA210A Homework 9 2015 - 2016
Due Thursday December 3
Read Chapters 13 and 14
Chapter 13 - Problems 2, 3, 8, 9 and 10
Problem - The figure below shows supersonic flow of Air over a 60 circular arc bump
at a free stream Mach number M 1 = 20 . Oblique shock

AA210A Homework 7, 2015 - 2016
Due Thursday November 12
Suggested viewing: Take 35 minutes and watch the lm CHANNEL FLOW OF A
COMPRESSIBLE FLUID on the MIT website or on YouTube.
Read Chapters 10 and 11
Chapter 10 Problems 4 and 5
Chapter 11 Problems 2, 3

AA210A Homework 5 2015 -2016
Due Thursday October 29
Read Chapter 8 Sections 8.1 to 8.7
Chapter 8 - Problems 2, 3 and 4
Problem A zero pressure gradient, incompressible, boundary layer has a velocity
profile of the form
U
y
= g .
Ue
The wall shear stre

AA210A Homework 6 2015 -2016
Due Thursday November 5
Read: Chapter 8 Sections 8.8 to the end, Chapter 9
Problem - Use Mathematica or Matlab to reproduce the Blasius boundary layer solution
presented in Figure 8.8.
Chapter 8 - Problem 6
Chapter 9 Problems

AA210A Homework 4 2015 -2016
Due Tuesday October 20
Read Chapter 6 and Chapter 7
Chapter 6 Problem 1
Chapter 7 Problems 2, 3 (correction - Figure 7.1 not Section 7.5) and 4
Problem (from a recent midterm) The figure below shows the path of a fluid element

AA210A Homework 2 2015 -2016
Due Tuesday October 6
Read: Chapter 2
Problem 1 The figure below shows an adiabatic vessel with its internal volume split into
two equal volumes. Initially the volume on the left is filled with helium at the pressure and
tempe

AA210A Homework 3 2015 -2016
Due Tuesday October 13
Read: Chapters 3, 4 and 5
Chapter 3 - Problems 1, and 6
Chapter 4 - Problems 1 and 2
Problem Assume the stream function in problem 1.8 corresponds to an inviscid, incompressible flow.
Does a pressure fie

AA 210A: Fundamentals of Compressible ow
Homework 2 Solutions
2015-2016
N. Harell, M. L. Wong
Problem 1.8 (5 pts)
Question 1
The mass of the gas in the left partition is
m.
Because the right vessel is at vacuum, the mass is zero. We will
assume that the g

AA 210A: Fundamentals of Compressible flow
Homework 9 Solutions
2015-2016
N. Harell, M. L. Wong
Problem 13.2 (10 points)
In the shock tube example 13.7.1 you are asked to determine the stagnation pressure of the gas in regions (2) and
(3) in both the labo

AA 210: Fundamentals of Compressible ow
Homework 4 Solutions
2015-2016
N. Harell, M. L. Wong
Midterm Problem (20 points)
Question 1 (10 points)
In this problem, we will assume that air is an ideal gas. The problem states that the path from 0 to 1 is adiab

AA 210A: Fundamentals of Compressible flow
Homework 7 Solutions
2015-2016
N. Harell, M. L. Wong
Problem 10.4 (20 points)
We are considering a supersonic wind tunnel which uses Helium. A large plenum contains the gas at a constant
stagnation pressure and t

AA 210: Fundamentals of Compressible ow
Homework 8 Solutions
2015-2016
N. Harell, M. L. Wong
Problem 12.4
Assumptions :
Calorically perfect gas
Ideal gas
Very weak shock => isentropic
p p
1
2
2 u
cp =
q =
=
p p
q
1
u2
2
With
p = RT
we get :
q =
1
1 p

AA210A Homework 8 2015 - 2016
Due Thursday November 19
Suggested viewing: Watch the lm WAVES IN FLUIDS on the MIT website
Read Chapter 12
Chapter 12 Problems 4, 5, 8, 9 and 13
Problem 13 reads as follows note the text is missing the questions below the im