Diamant A Performance Analysis

  Stage 3 Stage 2 Stage 1 Units
Oxidizer  Ammonium Perchlorate Nitric Acid -
Fuel  Polyurethane/Aluminum Turpentine -
Payload 242 1986 8379 lbs
OF Ratio 3.3 3.3 3.6 -
Oxidizer Density 107.7 107.7 93.66 lbs/cuft
Fuel Density 58.1 58.1 51.5 lbs/cuft
Avg Density 96.165 96.165 84.495 lbs/cuft
Avg Propellant Isp 273 273 251 seconds
Target Delta V 11229.94 8018.46 9573.558 fps
Body:Fuel Mass Ratio 0.217 0.275 0.136 -
Payload Ratio 0.139 0.311 0.268 -
Structural Coefficient 0.178 0.215 0.120 -
Propellant Mass Ratio 0.822 0.785 0.880 -
Mf/Me Ratio 3.591 2.492 3.272 -
Propellant Mass 1433 5016 27560 lbs
Oxidizer Mass 1099.744 3849.489 21568.696 lbs
Fuel Mass 333.256 1166.512 5991.304 lbs
Oxidizer Volume 10.211 35.743 230.287 cuft
Fuel Volume 5.736 20.078 116.336 cuft
Stage Weight 1744 6393 31310 lbs
MT 311 1377 3750 lbs
Me 553 3363 12129 lbs
Mf 1986 8379 39689 lbs
Cumulative Delta V 11229.94 19248.40 28821.96 fps

Note: Based on values published in Flight International, 28 June 1962
 

In the simulation for the above vehicles, I used the following values for the runs:

1st stage Isp (Sea Level) 206 seconds
1st stage Isp (Vacuum) 237 seconds
2nd stage Isp (Vacuum) 273 seconds
3rd stage Isp (Vacuum) 273 seconds

The following table represents the ascent coefficient of drag