X-Git-Url: https://git.gag.com/?p=web%2Fgag.com;a=blobdiff_plain;f=rockets%2Fresearch%2F2017-test-12.mdwn;h=ba35937b2a8ca188c6a2447bb508b3dd7294d3c2;hp=58d441195ce3e4ca5778b464b41dcc5b629ab940;hb=2045150506d8f63d150c97bba4a407b3b97546b4;hpb=6978aa924dc360f0c0616c833e103f58583bc88c

diff --git a/rockets/research/2017-test-12.mdwn b/rockets/research/2017-test-12.mdwn
index 58d4411..ba35937 100755
--- 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 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 ##
 
@@ -36,4 +36,5 @@ 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 ?, flight ?.
+Flight data logged as sn 3121, flight 3 on 2017-10-08.  8353 ft apogee, Mach 0.7, 3.4 sec boost.
+