Airfoil Selection-1 Online Exam Quiz
Airfoil Selection-1 GK Quiz. Question and Answers related to Airfoil Selection-1. MCQ (Multiple Choice Questions with answers about Airfoil Selection-1
A symmetric airfoil is operating with flow velocity of 350m/s. The lift produced by the airfoil is 21 N at 0.008 rad AOA. If chord is c m then, what will be the pressure difference across the airfoil?
Options
A : 21/c Pa
B : 21c/2 N
C : 21 Pa
D : 21c N
Aerofoil affects the performance parameters of aircraft.
Options
A : TRUE
B : FALSE
C : -
D : -
Airfoil is a streamline shape.
Options
A : TRUE
B : FALSE
C : -
D : -
An aerofoil is operating with flow velocity of 100m/s. Aerofoil is symmetric and is at 0? AOA. Determine lift produced by this aerofoil.
Options
A : 10.5 N
B : 0 N
C : 50 N
D : 100N
An aircraft is cruising with lift of 150N. Find the weight of aircraft.
Options
A : 0.150KN
B : 150KN
C : 123N
D : 15KN
An airfoil is subjected to the flow with temperature of 288.16K and flow is ideal. The velocity at the leading edge is __
Options
A : 0m/s
B : 250m/s
C : 288.16m/s
D : 16.882m/s
Consider a NACA 2812 airfoil. It is operating with flow velocity of 900m/s with chord of 1m. What should be the maximum thickness of this airfoil?
Options
A : 0.12m
B : 0.21m
C : 0.9m
D : 28.12m
Find location of aerodynamic centre from leading edge if, chord is 10m and airfoil has flow velocity of 0.2 M.
Options
A : 2.5 m
B : 0.2 m
C : 5 m
D : 10 m
If an airfoil has lift of 200 N at 10? AOA, then what is induced drag produced by airfoil at that AOA?
Options
A : 0 N
B : 100
C : 0
D : 100 N
Load factor is defined as ___
Options
A : ratio of lift produced to the weight of aircraft
B : aerodynamic efficiency
C : thrust loading
D : power to weight ratio
Aerodynamic Coefficients more Online Exam Quiz
Aerodynamics - Parasite (Zero-Lift) Drag and Drag due to Lift
Conceptual Sketch Sizing - Empty-Weight Estimation