X-Git-Url: https://git.gag.com/?p=web%2Fgag.com;a=blobdiff_plain;f=rockets%2Fresearch%2F2017-test-03.mdwn;h=45f788f089e64affb0cd50091845abefe3778eb4;hp=0c04dc0278ef17a3a593e95d7b9e5803809d5e6e;hb=7b3e268527a3c8214f810a2a625fddd792e99fde;hpb=a9d00113cf376036dfcd78067d8b03835e708242

diff --git a/rockets/research/2017-test-03.mdwn b/rockets/research/2017-test-03.mdwn
index 0c04dc0..45f788f 100755
--- a/rockets/research/2017-test-03.mdwn
+++ b/rockets/research/2017-test-03.mdwn
@@ -4,7 +4,12 @@
 a Tripoli Colorado launch in Hartsel on 21 May 2017.
 
 With a 10.250" liner, 8.9mm nozzle throat, buna-n o-rings, simulation says
-this is a 25% J-432, 763 Ns, with about a 1.6 sec burn
+this is a 25% J-432, 763 Ns, with about a 1.6 sec burn:
+
+<!--Begin motor 54mm 3-grain Sorbitol HTML export from MotorSim-->
+<table class='motor' style='text-align: left; border: 1px solid black'><tr><th colspan='6' class='title'>54mm 3-grain Sorbitol</th></tr><tr class='summary'><th>Rating:</th><td>25% J-432</td><th>Max Pressure:</th><td>7.04 MPa (1021 psi)</td></tr><tr class='summary'><th>Total Impulse:</th><td>763 Ns</td><th>Specific Impulse:</th><td>135 s</td></tr><tr class='summary'><th>Max Thrust:</th><td>557 N</td><th>Volume Loading:</th><td>71%</td></tr><tr class='summary'><th>Average Thrust:</th><td>432 N</td><th>Fuel Mass:</th><td>578 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=0,1.77,0,557.22&chxr=0,0,1.77|2,0,557.22|4,0,125.27&chd=t:0,0,0,0,0,0,0.01,0.01,0.01,0.01,0.01,0.03,0.08,0.14,0.23,0.36,0.55,0.82,1.23,1.58,1.72,1.77|0,25.05,49.43,74.06,96.77,117.34,136.23,153.5,169.22,183.49,196.41,334.56,373.53,397.84,430.72,474.56,525.08,557.22,510.06,104.85,0.5,0.14&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 54mm 3-grain Sorbitol-->
+
 
 * Grain 2017-01-01, 176.1g gross, ?g net
 * Grain 2017-01-03, 187.6g gross, ?g net