Section 8: Non-Ideal Supersonic Flow Conditions

Boundary Layers and Detached Shock Waves

• Supersonic Wings with Skin Friction
  • Boundary Layer Overview
  • Differences between Laminar/Turbulent Boundary Layers
  • Velocity Profiles
  • Displacement and Momentum Thickness
  • Friction Induced Drag Coefficient
  • Reynolds Number and Boundary Layer Thickness
  • Simple Turbulent Skin Friction Model

Lecture2 Notes:................... (pdf )

• Effects of Compressibility on Skin Friction
  • Boundary Layer Reynold's Number
  • Compressible Boundry layer heating
  • Adiabatic Wall Model
    • Dissipation and rRecovery Ractor
    • Effect of Prandtl Number
  • Non Adiabtic Wall
  • Example Calculations
  • Effects of Skin Friction on Supersonic Airfoil Performance
    

******************************************************
Five degree supersonic wedge airfoil L/D max (pdf)
******************************************************

Lecture3 Notes: .................. (pdf )

• Supersonic Flow Around a Blunt Body
  • beta-theta-Mach Plots
  • Criterion for Detached Shock Wave, Maximum Deflection Angle
  • Approximate Description of Stagnation Point Flow Field
    • Sonic Line
    • Shock Wave Stand-Off Distance
    • Approximate Surface Pressure Model
  • Modified Newtonian Flow
  • Empirical Examples
  • Airfoil Drag Due to Blunt Leading Edge
• Appendix: Space Shuttle Thermal Protection System (pdf)
• SpaceX Starship Thermal Protection System (https://www.youtube.com/watch?v=-Lsbi-bVfk0l)

Final ProjectAssignment ...... (L/Dmax on Supersonic Diamond Airfoil) (pdf)

• Assigned Wednesday December 1, 2021
• Due Wednesday December 15, 2021, 11:59 PM, via Via Dropbox or USU Box before that time
• Submission File Naming Protocol: <First>.<Last>.MAE5420.Final.Project.<Date>.pdf

Project 2 Solution ......

Project 2: --> 25% of Final Grade:

• Project Scoring Elements
• Proper Writeup Format All Required Elements: 20 pts Max
  • Template for Required Project Format (.pdf)
  • Template for Required Project Format (.docx)
• Laminar Compressibility Correction Derivation: 20 Points Max
  • Compressibility Correction
  • Average Boundary layer Temperature
• Inviscid L/D Plots and Supporting Analysis: 20 Points Max
  • Pressure Distributions vs Alpha
  • CL, CD vs Alpha
  • L/D Max Vs Mach Number
• Viscous L/D Plot: 1/7th Power Law, Turbulent Skin Friction Only: 20 Points Max
  • CL, CD vs Alpha
  • L/D Max Vs Mach Number, Altitude
• Transitional flow (laminar, transitional, and/or turbulent: 20 Points Max
  • L/D max vs Mach and Reynlds Number Plot
  • Transition Points Identified

---------------------------------------------------------

• 1976 US Standard Atmosphere table: (html)
• Project 2 Code Example, Uneditable C++ Code Images
• Example Code for Calcuating the Inviscid CL, CD, and L/D

Section 8 Appendices:

• Supplemental Boundary Layer Notes: Effect of Pressure Gradient on Boundary layer Thickness and Skin Friction: .................. (pdf )
  
• Exact (Blasius) Solution for Incompressible Flat Plate Boundary Layer

Back to MAE 5420 Homepage