Discussion
A cambered section has a zero-lift angle of \(-3^\circ\). At a geometric angle of attack of \(4^\circ\), thin airfoil theory gives a lift coefficient of about
Answer: D
The effective angle is measured from the zero-lift line, so it is \(4 - (-3) = 7^\circ\), which is 0.1222 rad. Then \(c_l = 2\pi \times 0.1222 = 0.77\). Using the geometric angle alone would give 0.44 and understate the lift.
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