Question
The NACA 64-412 is a cambered aerofoil with lift coefficient given by Cl = 0.11a + 0.3 when a is in degree units. What is
The NACA 64-412 is a cambered aerofoil with lift coefficient given by Cl = 0.11a + 0.3 when a is in degree units. What is the value of the constant pitching moment coefficient about the aerodynamic centre? Estimate the position of the centre of pressure for the aerofoil at an angle of attack of 5º. State all assumptions made in answering this question.
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Physics for Scientists and Engineers A Strategic Approach with Modern Physics
Authors: Randall D. Knight
4th edition
978-0134092508, 134092503, 133942651, 978-0133942651
