Aerospace Engineering > GATE 2013 > Thin Airfoil Theory
Circulation theory of lift is assumed for a thin
symmetric airfoil at an angle of attack α. Free stream velocity is U.
If the circulation at the quarter chord (c/4) of the airfoil is Γ1 the normal velocity is zero at
If the circulation at the quarter chord (c/4) of the airfoil is Γ1 the normal velocity is zero at
Explanation
Correct : b
Similar Questions
What is the worst-case time complexity of insertion in an AVL tree?
Which operations on a binary search tree have O(h) complexity?
Compare search complexities of sorted array vs balanced BST.