NOZZLE VALIDATION ANALYSIS More Information 

Nozzle has been validated using over 45 test cases from
the literature and text book examples. Presented here is one
test case using Example 33 on page 56 from Rocket Propulsion
Elements, Edition 6, by George P. Sutton. The problem is
for the design of a nozzle for an ideal rocket motor operating
with no shocks (PCRIT3). To use Example 33 as a validation
of the Nozzle program, it is more meaningful to start
with the dimensions of the nozzle and then determine the thrust,
mass flow rate and exit velocity of the rocket motor. Nozzle
computes mass flow rate, thrust, and the remaining properties
directly from the nozzle geometrical data. The exit velocity
is computed from the following equation: Thrust = Mass Flow Rate
* Exit Velocity + (Exit Pressure  Atmospheric Pressure) * Exit
Area. In this example the Exit Pressure is equal to the Atmospheric
Pressure for an ideal nozzle where no shocks are present and
the flow exhausts directly into the atmosphere.
Nozzle 3.7 Input Data Nozzle 3.7 Output Data For more information about Nozzle please contact AeroRocket.  MAIN PAGE  PRODUCTS  CONSULTING  MISSION  RESUME  