MAE 6530 - Propulsion Systems II

Assignments

Section 1: Method of Characteristics

Assignment 1.1
Date Assigned: Wednesday August 31, 2022
Date Due: Wednesday, September 7, 2022
Title: Method of Characteristics Unit Processes
Num. of Points: 5
PDF of Assignment: Assignment1.1.pdf
Also Ensure A/A*, and Prandtl-Meyer Solvers are working
- Assignment 1.1 Solution:
  - (pdf)

Assignment 1.2 (pdf)
Date Assigned: Wednesday September 7, 2022
Date Due: Monday September 19, 2022
Title: 2-D Method of Characteristics (M.O.C.) Grid Solver Development
Num. of Points: 10
- Code and Verify subroutines or scripts for
  - Initial Data Line along Expansion Section Wall

Link and Sequence Unit Process Modules to Calculate M.O.C Grid
- Solve Problem 11.1 in Anderson, page 429. (See Section 1.1 Notes for Example)
  - ... Minimum Length Nozzle with Maximum Turning Angle -- infinitesimal expansion section
  - ... Mexit = 2.0
  - ... D* = 2.0 cm
    - ... Assume Gamma = 1.4
    - ... Repeat with Gamma = 1.2

Solve Problem 11.2 in Anderson, Page 430 but with ...
- ... Finite expansion section radius of Curvature equal to 1.5 x throat radius
- ... Mexit = 2.0
- ... D* = 2.0 cm
  - ... Assume Gamma = 1.4
  - ... Repeat with Gamma = 1.2
for all parts
- Plot nozzle half-contours
- Plot nozzle Mach number profile along upper wall and along centerline
- Compare to Mach number profile calculated using A/A* equation

For each of the 4 Nozzle Contours above
- Use the approximate Mapping technique to solve for P,Q,S, and T of the Parabolic Contour
- Plot Contours against the derived M.O.C contours, comare shapes
- Use M.O.C for Theta_max, Nozzle length, and Rc of the expansion section for these calculations
- Be sure to show Calculations for Xn, Yn, etc.
- Assume Nozzle exit angle is zero for each case
  - Homework 1.2, M.O.C. Minimum Length Nozzle, Review and Analysis
    - Assignment 1.2 Solution: (pdf)

Assignment 1.3, Part1, Part2, Part3, Part4
Date Assigned: Wednesday October 5, 2022
Date Due: Monday October 17, 2022
Title: 2-D Delta II First Stage, Aerospike Replacement
- Num. of Points: 10
- PDF of Assignment: pdf
USA Standard Atmosphere Table to 110 km

Section 2: Conical Shock Wave Analysis

Assignment 2.1
Date Assigned: Assignment deferred to end of Course
Date Due:
Title: 2-D D Supersonic Inlet design Comparisons
- Num. of Points: 12
- PDF of Assignment: Assignment 2.1
- Assignment Solution: (part 1) ... (part2)

Section 3: Hybrid Rockets

Assignment 3.1
Date Assigned: Wednesday October 12, 2022
Date Due: Wednesday October 26, 2022
Title: N2O/HTPB Hybrid Rocket

Num. of Points: 10
PDF of Assignment: Assignment 3.1.pdf
Hybrid Homework 1 Solution (Problem 3.1)

Assignment 3.2
Date Assigned: Wednesday October 19, 2022
Date Due: Monday October 31, 2022
Title: GOX/ABS Hybrid Rocket, Effects of Injector Compressibility

Num. of Points: 10
GOX ABS CEA Spreadsheet
Extended Pressures GOX/ABS_Spreadsheet
PDF of Assignment: Assignment 3.2.pdf
- Hybrid Homework 2 Solution (Problem 3.2)

Section 4: Introductory Airbreating Propulsion Topics

Assignment 4.1
Date Assigned: Wednesday November 2, 2022
Date Due: Monday November 14, 2022
Title: Ideal Jet Engine Cycle Efficiency Analysis

Num. of Points: 10
PDF of Assignment Example: Assignment 4.1.pdf, Example
- Work Through Example, 4.1
  - Allow for Variable Compression Ratio
  - All other Parameters Fixed as in Example 4.1
  - Plot vs. Compression Ratio from PR = 8-to-16
    - Thrust
    - Required Compressor Power Input
    - Required Turbine Power Output
    - Combustor (Assume JP4, hf = 42.7 MJ/Kg)
      - Required Combustor Heat Input
      - Required Fuel Massflow
    - Efficiencies
      - Propulsive efficiency
      - Thermal Efficiency
      - Total Efficiency
      - Compare Ts-Diagram for PR=8 to that for PR=16.
    - What can you conclude about the effect of Compression Ratio on Engine Performance?

Section 5: The Turbojet Propulsion Cycle

Assignment 5.1
Date Assigned: Monday November 21, 2022
Date Due: Wednesday November 30, 2022
Title: Subsonic Inlet Turbojet Compressor, Matching Problem

Num. of Points: 10
PDF of Assignment Part: Assignment 5.1.pdf
- J85-Compressor Map, Surge/Choke/RMP(%) Lines (.xlsx)
Assignment 5.1 Solution: (pdf)

Section 6: The TurboFan Propulsion Cycle

Assignment 6.1
Date Assigned: December 5, 2022
Date Due: On or before end of Finals Week, Friday, December 15, 2022.
Title: TurboFan Cycle Analysis, Optimal ByPass Ratio

Num. of Points: 10
PDF of Assignment Part: Assignment 6.1.pdf
Assignment 6.1 Solution:

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