Weight and Balance | Python Fiddle

#!/usr/bin/env python

print ("Welcome to Weight and Balance Calculator for C172 by C.Baker")
print ("Follow the on screen prompts.")

aew = input ("Aircraft empty weight in lbs -->  ")
aea = input ("ARM -->  ")
aem = input ("Moment / 1000 -->  ")
pw = float (input ("Pilot weight in kg -->  "))
paw = float (input ("Passenger weight in kg -->  "))
rp = float (input ("Rear passengers weight in kg -->  "))
la1 = float (input ("Luggage area 1 weight in kg -->  "))
la2 = float (input ("Luggage area 2 weight in kg -->  "))
fuel = float (input ("Fuel in USG -->  "))
fudf = float (input ("Fuel used in flight USG -->  "))

#Change these variable for diffrent aircraft
#Pilot passenger arm
ppa = 37.0
#Rear passenger arm
rpa = 73.0
#Luggage area 1 arm
la1a = 95.0
#Luggage area 2 arm
la2a = 123.0
#Fuel arm
fuela = 47.8

#Pilot + passenger weight in lbs
ppw = ((float(pw) + float(paw)) * 2.20462)
#Rear passenger weight in lbs
rpw = (float(rp) * 2.20462)
#Luggage area 1 weight in lbs
la1w = (float(la1) * 2.20462)
#Luggage area 2 weight in lbs
la2w = (float(la2) * 2.20462)
#Pilot + Passenger moment
ppm = ((float(ppw) * float(ppa)) / 1000.0)
#Rear passengers moment
rpm = ((float(rpw) * float(rpa)) / 1000.0)
#Luggage area 1
la1m = ((float(la1w) * float(la1a)) / 1000.0)
#Luggage area 2
la2m = ((float(la2w) * float(la2a)) / 1000.0)
#Fuel weight in pounds
fuelw = (float(fuel) * 6)
#Fuel moment
fuelm = ((float(fuelw) * float(fuela)) / 1000.0)
#Fuel used in flight in pounds
fudfw = (float(fudf) * 6)
#Used fuel moment
fudfm = ((float(fudfw) * float(fuela)) / 1000.0)

#Take off weight
tow = (float(aew) + float(ppw) + float(rpw) + float(la1w) + float(la2w) + float(fuelw))
#Take off moment
tom = (float(aem) + float(ppm) + float(rpm) + float(la1m) + float(la2m) + float(fuelm))
#Take off arm
toa = ((float(tom) * 1000.0) / float(tow))
#Landing weight
ldw = (float(tow) - fudfw)
#Landing moment
ldm = (float(tom) - float(fudfm))
#Landing arm
lda = ((float(ldm) * 1000.0) / float(ldw))
#Pause
input ("Press <Enter>")

#data change set
aews = str(aew)
aeas = str(aea)
aems = str(aem)
ppws = str(round(ppw))
ppas = str(round(ppa))
ppms = str(round(ppm))
rpws = str(round(rpw))
rpas = str(round(rpa))
rpms = str(round(rpm))
la1ws = str(round(la1w))
la1as = str(round(la1a))
la1ms = str(round(la1m))
la2ws = str(round(la2w))
la2as = str(round(la2a))
la2ms = str(round(la2m))
fuelws = str(round(fuelw))
fuelas = str(round(fuela))
fuelms = str(round(fuelm))
tows = str(round(tow))
toas = str(round(toa))
toms = str(round(tom))
fudfws = str(round(fudfw))
fudfms = str(round(fudfm))
ldws = str(round(ldw))
ldas = str(round(lda))
ldms = str(round(ldm))

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