GATE AE · 2024 · AE
Question 35: Airfoils and Wings
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Question 35
AENAT1 markNeeds review
Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5° angle of attack in a uniform flow is __________ (rounded off to 2 decimal places).
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2024AE
GATE AE 2024 · Paper 1
Aerospace Engineering · Original paper archive
- Section
- Aerospace Engineering
- Question type
- Numerical answer (NAT)
- Marks
- 1 mark
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