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Unformatted text preview: er Figure 1.17 from the textbook. 3. For an angle of attack of
, calculate the lift and drag coefficients
aerofoil having normal and axial force coefficients as
Refer Equation 1.18 and 1.19 from the textbook. and
. of an ME 471.3
Introduction to Aerodynamics
Department of Mechanical Engineering
Instructor – Rajat Chakravarty Quiz 2
Instructions: Write all solutions on this page itself. No additional paper will be provided.
1. An airfoil has a center of pressure at a distance of
from the leading with respective
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- Winter '14
- Mechanical Engineering