MAE 6530 - Propulsion Systems II

Assignments

Section 1: Method of Characteristics

Assignment 1.1
Date Assigned: Wednesday September 1, 2021
Date Due: Wednesday, September 8, 2021
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 8, 2021
Date Due: Monday September 20, 2021
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
Date Assigned: Wednesday September 15, 2021
Date Due: Wednesday October 6, 2021
Title: 2-D Delta II First Stage, Aerospike Replacement
- Num. of Points: 10
- PDF of Assignment: pdf
- RS-27A Conical Nozzle (Nominal Delta II Solution) Payload Analysis (Part 1) (pdf)
- Aerospike Design (pdf)
- RS-27A Truncated Aerospike Nozzle Payload Analysis (Part 1) (pdf)
USA Standard Atmosphere Table to 110 km

Section 2: Conical Shock Wave Analysis

Assignment 2.1Old
Date Assigned: Wednesday September 29, 2021
Date Due: Wednesday October 13, 2021
Title: 2-D D Supersonic Inlet design Comparisons
- Num. of Points: 12
- PDF of Assignment: Assignment 2.1
- Assignment Solution (pdf)

Section 3: Hybrid Rockets

Assignment 3.1
Date Assigned: Wednesday October 20, 2021
Date Due: Monday November 1, 2021
Title: N2O/HTPB Hybrid Rocket

Num. of Points: 10
PDF of Assignment: Assignment 3.1.pdf
Assignment 2.1 Solution:
Hybrid Homework 1 (Problem 3.1) (pdf)

Assignment 3.2
Date Assigned: Monday November 1, 2021
Date Due: Monday November 8, 2021
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
- Solution (pdf)
- Solution Review Video (mp4)
- Start Time: Nov 27, 2021 10:40 AM
- Meeting Recording:
  https://usu-edu.zoom.us/rec/share/O9l74_R6ff62m7YDWbWGHtiFAE144PsyypsKtsMPBYFFC4erIYavCKivaCzjPgIf.Y0lBH4uUTTvifo-G

Section 4: Introductory Airbreating Propulsion Topics

Assignment 4.1
Date Assigned: Monday November 15, 2021
Date Due: Monday November 29, 2021
Title: Ideal Jet Engine Cycle Efficiency Analysis

Num. of Points: 10
PDF of Assignment Part: Assignment 4.1.pdf
Assignment 4.1 Solution: (pdf)

Assignment 4.2
Date Assigned: Wednesday November 15, 2020
Date Due: Monday November 29, 2020
Title: JB-2 Loon Performance &
Supersonic Inlet Analysis Problems

Num. of Points: 10
PDF of Assignment Part: Assignment 4.2.pdf
Assignment 4.2 Solution: part1, part2
Only Part 1 was assigned, Part 1 Solution (pdf)

Section 5: The Turbojet Propulsion Cycle

Assignment 5.2
Date Assigned:
Date Due:
Title: Supersonic Inlet Turbojet Design Problem, Nozzle Optimization

Num. of Points: 10
PDF of Assignment Part: Assignment 5.2.pdf
Assignment 5.2 Solution: Not Assigned See Solution on November 20 Lecture
Solution (pdf)

Assignment 5.4
Date Assigned: November 20, 2021
Date Due: December 1, 2021
Title: Subsonic Inlet Turbojet Design Problem, Inlet Capture Area

Num. of Points: 10
PDF of Assignment Part: Assignment 5.4.pdf
Assignment 5.4 Solution: (pdf)

Section 6: The TurboFan Propulsion Cycle

Assignment 6.1
Date Assigned: December 6, 2021
Date Due: In Class, Oral Briefing During Final Exam Period, Monday, December 13, 3:30-5:30 PM
Title: TurboFan Cycle Analysis, Optimal ByPass Ratio

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

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