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Aim

Theory

Pretest

Procedure

Simulation

Posttest

References

Contributors

Feedback

Flow over a delta wing

Choose difficulty:

Beginner

Intermediate

Advanced

For the present experiment, the lift generation stalls at

a: α = 5^o Explanation

Explanation

b: α = 15^o Explanation

Explanation

c: α < 5^o Explanation

Explanation

d: α > 30^o Explanation

Explanation

In the range of 0° ≤ α ≤40°, the drag acting on the delta wing

a: increases with angle of attack Explanation

Explanation

b: decreases with angle of attack Explanation

Explanation

c: doesn’t change with angle of attack Explanation

Explanation

d: all the above Explanation

Explanation

The reason for high lift is

a: leading edge vortex. Explanation

Explanation

b: high pressure drag Explanation

Explanation

c: None of the above Explanation

Explanation

d: Both a and b Explanation

Explanation

The reason for stalling of lift generation at higher α is

a: high suction force Explanation

Explanation

b: low pressure drag Explanation

Explanation

c: adverse pressure gradient Explanation

Explanation

d: vortex breakdown Explanation

Explanation

The slope of C_M vs α in the range of 0° ≤ α ≤30° is

a: negative Explanation

Explanation

b: positive Explanation

Explanation

c: flat Explanation

Explanation

d: none of the above Explanation

Explanation

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