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.
MAE 360 Fall 2012 Homework 3 Solutions
Table 1. Cl and Cd at given angles of attack
-0.862856017 -0.44087317 0.0001081156 0.4410018026 0.8628114475 1.2498647081 1.5976168178
MAE 360, HW#5 Pt. 2 Solutions
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
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
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.
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
MAE 360 Homework # 2 Solution
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