# Motor Data From RocketReviews.com
# http://www.rocketreviews.com/estes-c6.html
# C6 dia 18.0000 mm; length 70.0000 mm; delays 0,3,5,7 s; propellant 10.8000 g; total mass 23.1000 g; manuf Estes
table 22
0.0    0.0
0.0310 0.9460
0.0920 4.8260
0.1390 9.9360
0.1920 14.0900
0.2090 11.4460
0.2310 7.3810
0.2480 6.1510
0.2920 5.4890
0.3700 4.9210
0.4750 4.4480
0.6710 4.2580
0.7020 4.5420
0.7230 4.1640
0.8500 4.4480
1.0630 4.3530
1.2420 4.0690
1.3030 4.2580
1.4680 4.3530
1.6560 4.4480
1.8340 2.9330
1.8470 1.3250
1.8600 0.0000
# av thrust = 4.74 N over 1.86 s burning 10.8 g
# F Dt = D(mv) = v Dm => v = F Dt/Dm = 4.74 1.86 / 10.8e-3 = 855.96
constant 855.96 # alpha: F = -alpha dm/dt cf F Dt=D(m u_x) => F = u_x dm/dt => alpha = u_x