MAE 112 SECOND EXAM March 11, 2008 Do all three problems in eighty minutes. Open books and notes. Calculator allowed. I. Consider a turboprop engine that flies at a Mach number of 0.45 with ambient conditions at 298 K and one atmosphere of pressure.
MAE 112 Propulsion Homework Assignment #6 Due: February 27, 2009
1)
Suppose we had two parallel flows with equal mass flow rates, one at a stagnation temperature of 1800R and the other at 2400R. Each flow had a stagnation pressure of fifteen atmosph
MAE 112 PROPULSION FIRST MIDQUARTER EXAM February 7, 2008
Do all three problems in eighty-five minutes. Books, notes and calculators can be used freely. I. Consider a liquid-propellant rocket engine where one hundred kilograms per second of liquid o
MAE 112 PROPULSION FIRST EXAM February 11, 2009
Do all three problems in one-hundred-and-ten minutes. Books, notes and calculators (without wireless communication capability) can be used freely.
1. Consider a liquid-propellant rocket engine where li
MAE112, Winter 2009 Schedule Class meets Tuesday & Thursday (ET 204), 2 3:20 pm, and Wednesday (ICF 103), 2-3:50 pm. Tuesday and Thursday classes will usually be lectures and Wednesday classes will usually be discussion sessions. The exceptions incl
MAE 112 Propulsion Homework Assignment #7 Due: March 6, 2009 1. Consider a turbofan engine flying at a Mach number of 0.8 with an ambient pressure of one atmosphere and an ambient temperature of 500R. The intake has .98 polytropic efficiency. The air
Due: February 20, 2009 MAE 112 Homework Assignment #5
1. Do problem #8 on page 211 of Hill and Peterson text. 2. Do problem #9 on pages 211-12 of Hill and Peterson text. 3. Consider a turbine stage that has a polytropic efficiency of 0.97 for the st
Due: February 6, 2009 MAE 112 Homework Assignment #4 1. Do Problem 18, Pages 214-5, Hill & Peterson. Note that specific thrust is defined as thrust per unit mass flow of air. It is used to normalize and to be able to compare engines of different size
Due: January 30, 2009
MAE 112 Winter 2009 Homework Assignment #3
1. Consider a jet engine flying at a Mach number of 1.5. A normal shock sits at the entrance of the divergent diffuser. The diffuser entrance cross-sectional area is 3.0 ft2. The ambi
Due: January 23, 2009 MAE 112 Winter 2009 Homework Assignment #2 1. Consider a rocket engine that uses liquid oxygen and liquid ethanol (C2H5OH) fuel aka ethyl alcohol. The oxygen mass-flow rate is 2.00 times greater than the fuel massflow rate. Etha
Due: January 16, 2009 MAE 112 Winter 2009 Homework Assignment #1
1.
(a) Calculate AF at stoichiometric condition (AFst) for methyl alcohol CH3OH (aka methanol) burning in air. AF is the ratio of mass flow of air to mass flow of fuel. Also, calculat
MAE 112 PROPULSION Winter 2009 Catalog Data:
Application of thermodynamics and fluid mechanics to basic flow processes and cycle performance in propulsion systems: gas turbines, ramjets, scramjets, and rockets. Prerequisite: MAE135. (Design units: 1
MAE 112 PROPULSION FINAL EXAM March 20, 2008 Do all four problems in 120 minutes. Books, notes and calculators can be used freely. The exam questions extend to the reverse side of this page. I. Consider a ramjet in flight at a Mach number of 2.3 with