2. (Outcome #2) The gure shows an aircrafts drag polar. The aircraft is a large commercial transport. Its weight is 2.8
x105 N, and it is ying at an altitude of 5,000 In (,0 = 0.7364 kg/m3) at a speed of 200 m/s. The wing area is 380 1112.
Aircraft Drag
MAE 360 Fall 2012 Homework 3 Solutions
Table 1. Cl and Cd at given angles of attack
NACA0012
NACA2412
NACA4412
AOA
Cl
Cd
Cl
Cd
Cl
Cd
-8
-4
0
4
8
12
16
-0.862856017 -0.44087317 0.0001081156 0.4410018026 0.8628114475 1.2498647081 1.5976168178
0.0087777473 0
MAE 360, HW#5 Pt. 2 Solutions
Part 1:
In the first part of the homework a plot of Cdi/CL^2 vs. taper ratio was generated
for a symmetric airfoil with a constant aspect ratio of 7. The value of Cdi/CL^2 was
found by using the liftingline10.m MATLAB script-
Homework 3 Solution Guide
Part 1-3
For this part of the assignment students were to obtain flow results using the NACA 0012,
NACA 2412, and the NACA 4412 airfoils at varying angles of attack. Each airfoil then needed to be
plotted using MATLAB along with
MAE 360, HW#4 Solution Guide
Parts 1&2:
In this first part of the lab, flow results were generated for the NACA 0006 and
the 0018 airfoils. Once the results were generated MATLAB was used to generate the
coefficients of lift and drag for each of the airfo
MAE 360 Homework #1 Partial Solution
The following shows the pressure coefficient distribution on a NACA 0012 airfoil at = 3 . The pressure
data is given in the homework assignment.
NACA0012AirfoilatAngleofAttack=3degrees
LowerSurface
UpperSurface
0.1
0.0
0lu+foo$
MAE 360. Aerodynamics.
Midterm Exam #1. October 25, 2012.
This is a closedbook exam. You may use ve pages of notes written in your own hand writing. N0
photocopies are allowed. You may use a calculator. No mobile phones, PDAs, computers or any ot
Autumn 2012
MAE 360 Homework # 2 Solution
Part 1
For this part, the Overflow code was ran through MATLAB using the TACAA program. The
Reynolds number used was 10^6 and a Mach number of 0.1.
NACA 0012 Velocity Contour Plot
NACA 0012 Cp Plot
Autumn 2012
NAC