X-Git-Url: https://git.gag.com/?p=web%2Fgag.com;a=blobdiff_plain;f=rockets%2Fresearch%2F2017-test-12.mdwn;h=ba35937b2a8ca188c6a2447bb508b3dd7294d3c2;hp=81f314f18a6e8fb525b1a1372c2888895686c12e;hb=2045150506d8f63d150c97bba4a407b3b97546b4;hpb=3e16c14fa8347986b349ee98b7705a5ab6368e85

diff --git a/rockets/research/2017-test-12.mdwn b/rockets/research/2017-test-12.mdwn
index 81f314f..ba35937 100755
--- a/rockets/research/2017-test-12.mdwn
+++ b/rockets/research/2017-test-12.mdwn
@@ -9,24 +9,32 @@ ring plus 0.25" inside liner, with two o-rings, one pushing against liner.
 
 Liner 23.125" long with about 22.25" available for fuel load.
 
-Had to trim grains to fit.  Four just required squaring up the ends and 
-trimming excess casting tube away.  Fifth one was cut in miter box with saw.
+Simulation says this is a 57% L-1366 with 3804 Ns total impulse, 797 psi max, 
+76% volume loading, and about 2.6 seconds burn time.
 
-O-rings made forward closure a *very* snug fit.
+<!--Begin motor CTI mod Sorbitol HTML export from MotorSim-->
+<table class='motor' style='text-align: left; border: 1px solid black'><tr><th colspan='6' class='title'>CTI mod Sorbitol</th></tr><tr class='summary'><th>Rating:</th><td>57% L-1366</td><th>Max Pressure:</th><td>5.5 MPa</td></tr><tr class='summary'><th>Total Impulse:</th><td>3804 Ns</td><th>Specific Impulse:</th><td>131 s</td></tr><tr class='summary'><th>Max Thrust:</th><td>1706 N</td><th>Volume Loading:</th><td>76%</td></tr><tr class='summary'><th>Average Thrust:</th><td>1366 N</td><th>Fuel Mass:</th><td>2958 g</td></tr><tr><td colspan='4' class='thrust'><img src='http://chart.apis.google.com/chart?chxt=x,x,y,y,r,r&chs=400x200&cht=lxy&chco=3072F3&chds=0,2.78,0,1705.86&chxr=0,0,2.78|2,0,1705.86|4,0,383.49&chd=t:0,0,0,0,0,0,0.01,0.01,0.01,0.01,0.01,0.04,0.09,0.18,0.31,0.49,0.77,1.18,1.4,1.8,2.55,2.77,2.78|0,91.36,178.73,267.59,350.09,424.37,491.87,553.42,609.32,659.92,705.6,1075.86,1095.99,1121.65,1280.52,1398.83,1549.03,1685.96,1705.86,1637.7,490.86,0.61,0.48&chxl=1:|s|3:|N|5:|lbf&chxp=1,50|3,50|5,50' width='400' height='200' alt='null' /></td></tr></table>
+<!--End motor CTI mod Sorbitol-->
 
 </p>
 
 Neglected to re-weigh grains after trimming and before epoxying into the 
-liner.
+liner.  These were the pre-trim masses:
 
-* Grain , g gross, g net, 4.5" long
-* Grain , g gross, g net, 4.5" long
-* Grain , g gross, g net, 4.5" long
-* Grain , g gross, g net, 4.4375" long
-* Grain , g gross, g net, 4" long
+* Grain 2017-7-1, 590g gross, 574g net, trimmed to 4.5" long
+* Grain 2017-7-2, 594g gross, 578g net, trimmed to 4.5" long
+* Grain 2017-7-3, 592g gross, 576g net, trimmed to 4.5" long
+* Grain 2017-7-4, 584g gross, 568g net, trimmed to 4.4375" long
+* Grain 2017-7-5, 580g gross, 564g net, cut to 4" long
 
-Total of g propellant, vs g simulated.
+Total propellant load thus somewhat less than 2860g.
 
 ## Results ##
 
-Flight data logged as ? sn ?, flight ?.
+Had to trim grains to fit.  Four just required squaring up the ends and 
+trimming excess casting tube away.  Fifth one was cut in miter box with saw.
+
+O-rings made forward closure a *very* snug fit.
+
+Flight data logged as sn 3121, flight 3 on 2017-10-08.  8353 ft apogee, Mach 0.7, 3.4 sec boost.
+