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How much thrust is needed to take off?
For an airplane, normal takeoff, you need about 70 pounds of thrust (rule of thumb 5:1). As the plane accelerates past stall speed, the power required to maintain flight is a lot less than for take-off.
What is minimum thrust?
Consequently we can see that the minimum thrust required occurs when L/D is a maximum. Again, since L = W, the maximum value of L/D occurs when drag is a minimum. Hence the minimum thrust required occurs at the minimum drag flight condition which is the same as the maximum L/D flight condition.
How many pounds of thrust does a 737 have?
Boeing 737 Specs Table for Original and Classic.
| FAMILY | ORIGINAL | CLASSIC |
|---|---|---|
| Variant | 737 100 | 737 400 |
| Type | 7 | C-1 |
| Thrust | 64.4Kn 14,000lb | 104.5Kn 23,500lb |
| Dimensions |
Will humans be able to fly?
Humans are not physically designed to fly. We cannot create enough lift to overcome the force of gravity (or our weight). It’s not only wings that allow birds to fly. Air sacs inside their bodies make birds lighter, which enables smoother motion through air.
How to calculate minimum thrust required for given weight?
Maximum takeoff weight (MTOW) is the maximum weight at which the pilot of the aircraft is allowed to attempt to take off. How to Calculate Minimum Thrust required for given weight?
What are the factors for take off thrust?
The factors for take-off thrust are: Runway length: Short runways need more excess thrust for faster acceleration. Runway elevation: Higher places have less dense air, so more speed is needed to get airborne, and less thrust is available from the engines than at sea level. Runway slope.
How much thrust do you need to fly an airplane?
You need at least enough thrust to keep the airplane flying at the speed of minimum drag. This is quite a bit higher than the minimum flight speed, so you should add something to quicken the acceleration to this point.
How to calculate the thrust of a wing?
To calculate Minimum Thrust required for given weight, you need Dynamic Pressure (P dynamic), Reference Area (S), Zero-lift drag coefficient (C D,0), Weight (W), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR).
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