1. AAE 450 Spring 2008 Ricky Hinton March 27 th, 2008 Propulsion Group Nozzle, Test Facility (back-up slides)

2. Nozzle (specs and CAD)  Conical Nozzle –12° Conical Nozzle –Conical because of solid and hybrid propellants. –All stages have same nozzle  Sizing –Nozzle Dimensions based off of the exit area from MAT output –ε = 60; Throat Area and Throat Diameter are determined. CaseD throat (m) D exit (m) A throat (m^2) A exit (m^2) D stage (m) 5 kg Stage 10.1591.2350.02001.1981.839 Stage 20.00390.2990.00170.0700.817 Stage 30.0080.06180.000050.0030.275 1 kg Stage 10.0850.6600.00570.3421.126 Stage 20.0240.1890.000470.0280.567 Stage 30.0080.0620.000050.0030.290 200 g Stage 10.1070.8310.009050.5431.302 Stage 20.0290.2260.000670.040.674 Stage 30.0080.0620.000050.0030.272

3. Test Facilities Purdue (Zucrow High Pressure Laboratories)  Propellants/ Oxidizers currently tested: H 2 O 2, Liquid Hydrocarbon, LOX  For Hybrid test we need H 2 O 2, and (excluding 5 kg Stage1) all other engines can be tested at Purdue.  Table below shows Zucrow’s HPL capabilities.  Kelly Space and Technology  Up to 20,000 lbf (88,960 N) thrust stand capabilities.  Propellant tanks and data acquisition systems already at test site.  Located in San Bernardino, CA.  Can test our 5 kg: stage 1 engine at 75,073 Newtons of thrust. Maximum Capability ValueUnits Thrust44,480N Chamber Pressure4.137MPa Mass Flow Rate6.803kg/s

4. References  1 Scott Meyer, private meeting at Zucrow Test Laboratories. February 8 th, 2008. Test facility overview and private tour of the large rocket test stand.  2 Kelly Space and Technology. Jet and Rocket Engine Test Site (JRETS) URL: http://www.kellyspace.com/ [last updated Jan. 31 st 2008].  3 MAT Output file from AAE 450 course website. 5kg, 1kg, and 200 g cases https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2008/spring/large/3 _5kg/v125/5kg_MAT_out_v125.txt https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2008/spring/large/3 _5kg/v125/5kg_MAT_out_v125.txt AAE 450 Spring 2008