Homework Help is Here – Start Your Trial Now!
Math
Advanced Math
For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.

For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.

Advanced Engineering Mathematics
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
See similar textbooks
icon
Related questions
Question
For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.
Transcribed Image Text:For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient about the quarter-chord at -8° AOA are found to be -0.598 and -0.0466, respectively. At 6° AOA, these coefficients are found to be 0.858 and -0.0354, respectively. Giving reasons for your method, calculate the zero lift AOA and the location of the aerodynamic centre.
a) The mean camber line of an aerofoil is defined by the relations: X X 17²7 ( 29 - *) * 2 * ² 2 q с C с Zc m C Zc C m (1-q)² ≤q, X (1-9)²-( \ / -9 9 C Given that, c is the aerofoil chord, m = 0.025, q = 0.45, and using thin aerofoil theory estimate:
Transcribed Image Text:a) The mean camber line of an aerofoil is defined by the relations: X X 17²7 ( 29 - *) * 2 * ² 2 q с C с Zc m C Zc C m (1-q)² ≤q, X (1-9)²-( \ / -9 9 C Given that, c is the aerofoil chord, m = 0.025, q = 0.45, and using thin aerofoil theory estimate:
Expert Solution
steps

Step by step

Solved in 3 steps with 1 images

SEE SOLUTIONCheck out a sample Q&A here
Blurred answer
Similar questions
Recommended textbooks for you
Advanced Engineering Mathematics
Advanced Engineering Mathematics
Advanced Math
ISBN:
9780470458365
Author:
Erwin Kreyszig
Publisher:
Wiley, John & Sons, Incorporated
Numerical Methods for Engineers
Numerical Methods for Engineers
Advanced Math
ISBN:
9780073397924
Author:
Steven C. Chapra Dr., Raymond P. Canale
Publisher:
McGraw-Hill Education
Introductory Mathematics for Engineering Applicat…
Introductory Mathematics for Engineering Applicat…
Advanced Math
ISBN:
9781118141809
Author:
Nathan Klingbeil
Publisher:
WILEY
Mathematics For Machine Technology
Mathematics For Machine Technology
Advanced Math
ISBN:
9781337798310
Author:
Peterson, John.
Publisher:
Cengage Learning,
Basic Technical Mathematics
Basic Technical Mathematics
Advanced Math
ISBN:
9780134437705
Author:
Washington
Publisher:
PEARSON
Topology
Topology
Advanced Math
ISBN:
9780134689517
Author:
Munkres, James R.
Publisher:
Pearson,
SEE MORE TEXTBOOKS