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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.
- 322 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.
- 328 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.
- 325 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.
- 358 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.
- 444 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.
- 431 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.
- 424 views
- 1 answers
- 0 votes
For a given set of free-stream conditions and angle of attack, the lift per unit span for a given airfoil is 200 pounds per foot (lb/ft). The location of the center of pressure is at 0.3c, where c is the chord length; c = 5 ft.
For a given set of free-stream conditions and angle of attack, the lift per unit span for a given airfoil …
Aircraft performance

Airplane design

airspeed

Worldtech Asked on 9th November 2023 in Flight mechanics.
- 472 views
- 1 answers
- 0 votes
Determine the differential equation for small oscillations about a circular orbit when the attractive force is -K/r².
Determine the differential equation for small oscillations about a circular orbit when the attractive force is -K/r².
space

transfer orbit

Worldtech Asked on 8th November 2023 in Space dynamics.
- 559 views
- 1 answers
- 0 votes
The satellite orbit is characterized by e = 0.508 and a/R = 3.34, and its launch point was r0/R = 2.0, Θ = 62°23′.
The satellite orbit is characterized by e = 0.508 and a/R = 3.34, and its launch point was r0/R = …
space

transfer orbit

Worldtech Asked on 8th November 2023 in Space dynamics.
- 375 views
- 1 answers
- 0 votes

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