Discussion
A wing section has \(c_l = 0.6\) at \(4^\circ\) and \(c_l = 0.8\) at \(6^\circ\). Its lift curve slope per degree is
Answer: A
Correct answer: 0.10
The slope is the change in lift coefficient per degree: \[ a_0 = \frac{0.8 - 0.6}{6 - 4} = \frac{0.2}{2} = 0.10\ \text{per degree.} \] This is close to the thin airfoil value, since \( 2\pi \) per radian is about 0.11 per degree. Real sections fall a little below it because the boundary layer displacement slightly decambers the effective shape.
No comment is present. Be the first to comment.
Loading…
Post your comment
Please log in or register to post a comment.
Examination Categories
- SSC Exams
- Banking Exams
- Teaching Exams
- Civil Services Exams
- Railways Exams
- Engineering Recruitment Exams
- Defence Exams
- State Government Exams
- Police Exams
- Insurance Exams
- Nursing Exams
- Other Government Exams
- NRA CET
- PG Entrance Exams
- Campus Placement
- MBA Entrance Exams
- CUET and UG Entrance
- Judiciary Exams
- Regulatory Body Exams
- Software Development