some mass data

diff --git a/rockets/research/2017-test-12.mdwn b/rockets/research/2017-test-12.mdwn
index 58d441195ce3e4ca5778b464b41dcc5b629ab940..24ebc6af4de2bdace173cc9309d5f18ae26509e8 100755 (executable)
--- a/rockets/research/2017-test-12.mdwn
+++ b/rockets/research/2017-test-12.mdwn
@@ -19,15 +19,15 @@ Simulation says this is a 57% L-1366 with 3804 Ns total impulse, 797 psi max,
 </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 1, 590g gross, 574g net, trimmed to 4.5" long
+* Grain 2, 594g gross, 578g net, trimmed to 4.5" long
+* Grain 3, 592g gross, 576g net, trimmed to 4.5" long
+* Grain 4, 584g gross, 568g net, trimmed to 4.4375" long
+* Grain 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 ##