update index

[web/gag.com] / rockets / research / 2017-test-12.mdwn

diff --git a/rockets/research/2017-test-12.mdwn b/rockets/research/2017-test-12.mdwn
index 24ebc6af4de2bdace173cc9309d5f18ae26509e8..ba35937b2a8ca188c6a2447bb508b3dd7294d3c2 100755 (executable)
--- a/rockets/research/2017-test-12.mdwn
+++ b/rockets/research/2017-test-12.mdwn
@@ -21,11 +21,11 @@ Simulation says this is a 57% L-1366 with 3804 Ns total impulse, 797 psi max,
 Neglected to re-weigh grains after trimming and before epoxying into the 
 liner.  These were the pre-trim masses:
 
-* 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
+* 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 propellant load thus somewhat less than 2860g.
 
@@ -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.
+