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The GE J-79 turbojet produces a thrust of 10,000lbs at sea level. The inlet diameter is 3.19 ft.
The GE J-79 turbojet produces a thrust of 10,000lbs at sea level. The inlet diameter is 3.19 ft. If an …
Aircraft performance

Airplane design

Worldtech Asked on 7th December 2023 in Aeronautics.
- 374 views
- 1 answers
- 0 votes
The Anglo-French Concorde supersonic transport has an ogival delta wing with an aspect ratio of 1.7. Assuming a triangular planform shape, estimate the low-speed lift coefficient for this wing at an angle of attack of 25°.
The Anglo-French Concorde supersonic transport has an ogival delta wing with an aspect ratio of 1.7. Assuming a triangular planform …
Aircraft performance

Airplane design

Worldtech Asked on 30th November 2023 in Aeronautics.
- 370 views
- 1 answers
- 0 votes
Consider a wing with a thin, symmetric airfoil section in a Mach 2 airflow at an angle of attack of 1.5°. Calculate the lift coefficient
Consider a wing with a thin, symmetric airfoil section in a Mach 2 airflow at an angle of attack of …
Aircraft performance

Airplane design

flight mechanics

Worldtech Asked on 29th November 2023 in Aeronautics.
- 374 views
- 1 answers
- 0 votes
Using Helmbold’s relation for low-aspect-ratio wings, calculate the lift coefficient of a finite wing of aspect ratio 1.5 with an NACA 2412 airfoil section. The wing is at an angle of attack of 5°.
Using Helmbold’s relation for low-aspect-ratio wings, calculate the lift coefficient of a finite wing of aspect ratio 1.5 with an …
Aircraft performance

Airplane design

Worldtech Asked on 13th November 2023 in Aeronautics.
- 410 views
- 1 answers
- 0 votes
Consider a finite wing of aspect ratio 4 with an NACA 2412 airfoil; the angle of attack is 5°. Calculate (a) the lift coefficient at low speeds (incompressible flow) using the results of Prandtl’s lifting line theory, and (b) the lift coefficient for \(M_{\infty}\). Assume that the span efficie
Consider a finite wing of aspect ratio 4 with an NACA 2412 airfoil; the angle of attack is 5°. Calculate …
Aircraft performance

Airplane design

lift and drag

Worldtech Asked on 13th November 2023 in Aeronautics.
- 494 views
- 1 answers
- 0 votes
Consider an NACA 2412 airfoil with chord of 1.5 m at an angle of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions, calculate the lift and drag per unit span.
Consider an NACA 2412 airfoil with chord of 1.5 m at an angle of attack of 4°. For a free-stream …
Aircraft performance

airfoil

Airplane design

airspeed

drag force

Worldtech Asked on 13th November 2023 in Aeronautics.
- 486 views
- 1 answers
- 0 votes
The Boeing 777 has a wing planform area of 4605 square feet (ft2). Assuming at akeoff weight of 506,000 lb and a takeoff velocity of 160 mi/h, calculate the lift coefficient at takeoff for standard sea-level conditions.
The Boeing 777 has a wing planform area of 4605 square feet (ft2). Assuming at akeoff weight of 506,000 lb …
Aircraft performance

Airplane design

airspeed

Worldtech Asked on 13th November 2023 in Aeronautics.
- 492 views
- 1 answers
- 0 votes
How urban air mobility work?
How urban air mobility work?
Airplane design

flight mechanics

techAir Asked on 13th December 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
What are form drag and profile drag?
What are form drag and profile drag?
drag

drag coefficient

drag force

lift and drag

Kumar59 Asked on 8th September 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
A finite wing with an elliptical lift distribution has an aspect ratio of \(6\). The airfoil of the wing has a lift slope of \(0.15\) per degree. Find and compare the lift slopes for a straight wing and a swept wing with a half-chord line sweep of \(30^{\circ}\).
A finite wing with an elliptical lift distribution has an aspect ratio of \(6\). The airfoil of the wing has …
airfoil

lift coefficient

swept wing

Worldtech Asked on 12th August 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes

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