GATE AE 2021 Paper 1 — page 9

Questions 25–27 of 65. Imported answers require review unless explicitly marked reviewed.

Paper practice 65 questionsPage 9 of 22

Which of the following statement(s) is/are true with regards to Kutta condition for flow past airfoils?

Your answerSelect all correct options. You can choose more than one.

It is utilized to determine the circulation on an airfoil.

It is applicable only to airfoils with sharp trailing edge.

The trailing edge of an airfoil is a stagnation point.

The flow leaves the trailing edge smoothly.

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According to the thin airfoil theory, which of the following statement(s) is/are true for a cambered airfoil?

Your answerSelect all correct options. You can choose more than one.

The lift coefficient for an airfoil is directly proportional to the absolute angle of attack.

The aerodynamic center lies at quarter chord point.

The center of pressure lies at quarter chord point.

Drag coefficient is proportional to the square of lift coefficient.

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______ (round off to nearest integer).

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2021 · Paper 1