Question about the upthrust of a rocket

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The discussion focuses on calculating the thrust and resultant force of the Saturn V rocket at lift-off. The thrust was initially calculated as 33 MN using the exhaust velocity of 1.0 x 10^4 m/s, but it was later corrected to 1.1 x 10^4 m/s. The resultant force was debated, with one participant consistently arriving at 3 MN instead of the expected 3.6 MN. The confusion stemmed from differing values for gravitational acceleration, with the book suggesting to use 10 m/s² instead of 9.81 m/s². Ultimately, the participant resolved their calculations and confirmed their understanding.
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Homework Statement



The Saturn V rocket which launched the Apollo space missions had the following specifications: mass at lift-off = 3.0 x 10^6 kg velocity of exhaust gases = 1.0 x 10^4 m/s initial rate of fuel consumption at lift-off = 3.0 x 10^3 kg/s 1.(a) Calculate: (i) the force (thrust) produced at lift-off (ii) the resultant force acting on the rocket at lift-off

Homework Equations



Ft = mv

The Attempt at a Solution



i got the force exerted by the exhaust gases by rearranging the equation to F = mv/t. Upthrust was 33MN. But then i have no clue how to figure the second part out, the solution page says it is 3.6MN, i keep getting 3MN, any help would be greatly appreciated!
 
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I don't see how you got the thrust value of 33 MN from the given information, notr how they arrived at 3.6 MN for the resultant force. Check the given value for the exhaust velocity: Was it perhaps a bit higher than 1.0 x 104 m/s?
 
My bad, it's 1.1*10^4 m/s
 
ThatOneMidget said:
My bad, it's 1.1*10^4 m/s
Does that resolve your issues?
 
I'm still getting 3MN for the net force, and 33MN for the upthrust
 
It seems like the book used 9.81 as a value for g although it stated to use 10 = g, anyways I've got it :D
 
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