more data from notepad used in Argonia

diff --git a/rockets/research/test10.mdwn b/rockets/research/test10.mdwn
index 0c9a937d4ce572edb5ce583124d0119bc562575e..fa5d60a2e8fdd650dcfb31a068d4bfc5db1f20e0 100755 (executable)
--- a/rockets/research/test10.mdwn
+++ b/rockets/research/test10.mdwn
@@ -6,10 +6,14 @@ These grains were cast on 30 August 2015.
 
 ## Results ##
 
-* Grain 1, ?g net
-* Grain 2, ?g net
-* Grain 3, ?g net
-* Grain 4, ?g net
+* Grain 1, 55.11g gross, ?g net
+* Grain 2, 56.60g gross, ?g net
+* Grain 3, 55.03g gross, ?g net
+* Grain 4, 53.82g gross, ?g net
 
 ## Observations ##
 
+438g motor pre-flight, 220g post-flight.
+1210g airframe pre-flight, 984g post-flight.
+
+Nozzle throat post-flight 0.330 inches.

diff --git a/rockets/research/test11.mdwn b/rockets/research/test11.mdwn
index da4080731e0a49e7163077119161a598ef52686a..6a5eda9d759419521845a7f5fc4d55dcbb12dfce 100755 (executable)
--- a/rockets/research/test11.mdwn
+++ b/rockets/research/test11.mdwn
@@ -9,7 +9,7 @@ centering.
 The formula used is the same we've been using with sorbitol, but in an 875g
 batch this time:
 
-* 65% KNO3, 568.75g
+* 65% KNO3, 568.75g, taken from the big bucket this time
 * 35% Sorbitol, 306.25g
 * 1% red iron oxide, 8.75g, added after melt
 * 10 drops Polystep-B1, added before pour using eye dropper
@@ -18,16 +18,38 @@ Robert noted that tamping down the material in the grains required a tweak
 to his process for 38mm, since the larger casting tubes and greater propellant
 mass meant having to hold everything together more solidly.  We also noted
 that there was some variation (a mm or so?) in my casting tube lengths, so
-getting them uniformly filled was a bit fiddly.
+getting them uniformly filled was a bit fiddly.  Our calculations led us to 
+use a fill line 76.118mm from the bottom or 6.431mm from the top of the 
+casting tubes.  On a couple of the shortest-cut casting tubes, this led to a
+small amount of propellant contacting the inside of the pipe cap.  Try harder
+to cut precisely next time!
 
 These grains were cast on 1 September 2015.
 
 ## Results ##
 
+Dropped one grain at home, big chunk missing and maybe cracks.  Decided not
+to use it.  That left us with three "good" grains.  
+
+The case, nozzle, and closure combination used left me cutting the liner to 
+10.250 inches, while Loki specifies 10.375 for their 3-grain case.  The total
+available propellant length was 9.459", so I had to trim the three grains 
+slightly to fit.  The gross masses below were post-trim.  Calculating net
+masses will require approximation based on the overall casting tube length
+that remained.
+
 * Grain 1, ?g net
-* Grain 2, ?g net
-* Grain 3, ?g net
-* Grain 4, ?g net
+* Grain 2, 204.0g gross, ?g net
+* Grain 3, 199.3g gross, ?g net
+* Grain 4, 198.6g gross, ?g net
+
+10.250" liner, 8.3mm nozzle throat, buna-n o-rings.
+
+calculated as a 39% J-477, 843 Ns, ~1.5 sec burn
 
 ## Observations ##
 
+1250g pre-launch motor mass, 664g post-flight motor mass.
+
+4830g pre-launch airframe mass.
+

diff --git a/rockets/research/test9.mdwn b/rockets/research/test9.mdwn
index 9e96e05f159e6b1b0dc83cd25fdac03dba4a2fdc..ea08ddc4200016ea418074811412c7d8e544e9ec 100755 (executable)
--- a/rockets/research/test9.mdwn
+++ b/rockets/research/test9.mdwn
@@ -6,10 +6,16 @@ These grains were cast on 29 August 2015.
 
 ## Results ##
 
-* Grain 1, ?g net
-* Grain 2, ?g net
-* Grain 3, ?g net
-* Grain 4, ?g net
+* Grain 1, 57.04g gross, ?g net
+* Grain 2, 52.88g gross, ?g net
+* Grain 3, 54.14g gross, ?g net
+* Grain 4, 53.97g gross, ?g net
 
 ## Observations ##
 
+Motor 434g pre-flight, 220g post-flight.
+
+Fat-Boy igniter.
+
+Rocket post-flight mass was 984g.  Nozzle throat was 0.334 post-flight.
+