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.
Step by Step Solution
There are 3 Steps involved in it
Step: 1
Get Instant Access to Expert-Tailored Solutions
See step-by-step solutions with expert insights and AI powered tools for academic success
Step: 2
Step: 3
Ace Your Homework with AI
Get the answers you need in no time with our AI-driven, step-by-step assistance
Get Started
Physics for Scientists and Engineers A Strategic Approach with Modern Physics
Authors: Randall D. Knight
4th edition
978-0134092508, 134092503, 133942651, 978-0133942651
