X-Git-Url: https://git.gag.com/?p=web%2Fgag.com;a=blobdiff_plain;f=rockets%2Fresearch%2F2017-batch-04.mdwn;h=99be728525139359f0da5d9a276a8eea59d7d127;hp=3d2ca0ab618ef23c95eddca7c573558baa86e9ab;hb=b50b20d3988c7bf1ae74ed2df21ad9cd36a9f5ad;hpb=5887e26bcb0519507d93ebae190f09eed05c0b8b

diff --git a/rockets/research/2017-batch-04.mdwn b/rockets/research/2017-batch-04.mdwn
index 3d2ca0a..99be728 100755
--- a/rockets/research/2017-batch-04.mdwn
+++ b/rockets/research/2017-batch-04.mdwn
@@ -37,6 +37,8 @@ Simulation says:
 
 Average casting tube mass 1.25g.
 
+29mm grains
+
 * Grain 1, ?g gross, ?g net
 * Grain 2, ?g gross, ?g net
 * Grain 3, ?g gross, ?g net
@@ -47,3 +49,14 @@ Total of ?g propellant, vs 122g simulated.
 With a 7.40" liner, 14/64" nozzle throat, buna-n o-rings, simulation says
 this reload will be a 99% G-180, 159 Ns, with about an 0.8 sec burn.
 
+54mm grains
+
+* Grain 5, ?g gross, ?g net
+* Grain 6, ?g gross, ?g net
+* Grain 7, ?g gross, ?g net
+* Grain 8, ?g gross, ?g net
+* Grain 9, ?g gross, ?g net
+* Grain 10, ?g gross, ?g net
+
+Total of ?g propellant, vs 122g simulated.
+