if a 2000lb aircraft can reach 760mph at sealevel, how much thrust does it have?

Question

2,000ft runway, 2 minute time frame

Answer 1

I think it's clear that you're supposed to ignore wind resistance and weight changing as fuel burns. I'll also assume it doesn't point the nose up - just flies along at sea level. So my solution is:

760 mph * (88 ft/sec)/60 mph = 1115 ft/sec
(60 mph is equivalent to 88 ft/sec so the above exercise shows that 760 mph is equivalent to 1115 ft/sec)

V = a*t = 1115 ft/sec = a*120sec
a = (1115 ft/sec) / 120 sec = 9.3 ft/sec^2

Need the mass of the plane
w = m*g
m = 2000 lb / (32 ft/sec^2) just leave mass in this form
Now to calculate thrust
F = m*a = 2000 lb / (32 ft/sec^2) * 9.3 ft/sec^2
F = 581.25 pounds

Incidentally, it ran out of runway after 20.7 seconds.

Answer 2

Thrust = T = 133,000 pounds 591,610 newtons


From Wikipedia, the free encyclopedia
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For other uses, see Thrust (disambiguation).
Thrust is a reaction force described quantitatively by Newton's Second and Third Laws. When a system expels or accelerates mass in one direction the accelerated mass will cause a proportional but opposite force on that system.

Forces on an aircraftAn aircraft generates forward thrust when the spinning propellers blow air, or eject expanding gases from a jet engine to the back of the aircraft. The forward thrust is proportional to the (mass of the air) multiplied by (average velocity of the airstream).

Similarly, a ship generates thrust (or reverse thrust) when the propellers are turned to accelerate water backwards (or forwards). The resulting thrust pushes the ship in the equal and opposite direction to the sum of the momentum change in the water flowing through the propeller.

A rocket (and all mass attached to it) is propelled forward by a thrust force equal to, and opposite of, the time-rate of momentum change experienced by the exhaust mass accelerating out from the combustion chamber through the rocket nozzle. This is the exhaust velocity with respect to the rocket, times the time-rate at which the mass is expelled, or in mathematical terms:

T = M/t * v = 175 lb hr / mile * 760 miles / hr

T = 133,000 pounds


Where:

T = the thrust generated (Force units). POUNDS

M/t = fuel burn rate (Mass/to time units). 2000 lb aircraft/ (.3787 miles / .0333 hr) = 175 lb hr/ mile


v = exahust velocity. 760 mph

Of course, for a launch the thrust at lift-off should be more than the weight, and with a fair margin, because a "slow launch" would be very inefficient.

Each of the three Space shuttle main engines can produce a thrust of 1.8 MN, and each of its two Solid Rocket Boosters 14.7 MN, together 34.8 MN. Compare with the mass at lift-off of 2,040,000 kg, hence a weight of 20 MN.

The simplified Aid for EVA Rescue (SAFER) has 24 thrusters of 3.56 N each.

Answer 3

Incomplete Data
If we assume that at constant thrust T the 2000 lb aircraft accelerates to 760 mph in 2000 ft in 2 miniutes it is solvable. A constant weight of aircraft has to be assumed ( which is not true)
Constant acceleration has to be assumed. Then do the math

Answer 4

Impossible to say for sure without knowing the drag and lift coefficients for the particular aircraft.

Answer 5

its simple w=md, weight obviously equals mass times density check out what changes anything in sea level will have plug in your numbers and solve for the unknown. The sea level info should be in any major physics book.

Answer 6

15200.00