Yes, but how much fuel (kg) did you carry at departure? And what are the astronuts doing duning 8 months to Mars ... without toilets? And showers?
What kind of humans are aboard?
Please, read the Rules of the Challenge http://heiwaco.com/chall2.htm and do not change the subject!
Topic is not propellant per second. I am interested in fuel used for the whole trip ... carried at departure.
Re: "Maybe you need to mention to your doctor you are having trouble with your memory." ... you sound mentally deranged.
You really should take a look at this again.
Saturn V
Individual stage Total vessel
STAGE Total mass Dry mass Total mass Dry mass Isp Delta-v
1 LOX/RP-1 2,300,000 131,000 2,900,000 731,000 263s 3554.2 m/s
2 LOX/LH 480,000 36,000 600,000 156,000 421s 5561.5 m/s
3 LOX/LH 120,800 10,000 120,800 10,000 421s 8796.2 m/s
--------------
17911.9 m/s
Masses are in kg
Does not include delta-v calculations for the lunar lander, but assumes the GVM of the Saturn V.
kg of propellant per second= Thrust in Newtons/ISP in meters per second
Stage 1:
34,020,000/2580= 13,186 kg per second
164 second burn time.
Saturn V TWR:
5 F-1 engines with 6.672.000 N thrust each=33,360,000 N
2 896 895 kg gross rocket mass
(6,672,000N*5)/(2,896,895*9. 8 )=1.17 TWR
Explanation of methodology used:
http://www.braeunig.us/space/index.htmDo you know what the difference between dry and total mass is?
You also do not seem to really understand the subject matter. This is not the first time you asked a question the above could answer with very simple calculations.
In this case subtracting one number from another will give you the answer to your question about the amount of propellant.
Being an engineer I assume you can take it from there. If not let me know I will do it for you.