MAE 5420 - Compressible Fluids
MAE 5420 Links to Recorded Lectures, Fall 2020
Guest login for live lectures: connect.usu.edu/swhitmore
-
Covid-19 Operating Procedures Introductory Lecture
- Lecture 1, August 31 2020
- Course Introduction and Overview
- Covid-19 Intro Lecture
- DeLaval Nozzle and Supersonic Flow
- Mach Tuck
- Starting Expression for the Speed of Sound in a Gas
- Lecture 2, September 2 2020
- Course Overview (Concluded)
- Speed of Sound (continued)
- Thermodynamics Review
- Equation of State
- Conservation of Energy (First Law of Thermodynamics)
- Second Law of Thermodynamics
- Adiabatic and Isentropic Processes
- Working Formula for Speed of Sound
- Molecular Weight and Specific Heats of a Mixed Gas
- Lecture 3, September 4 2020
- State Equation and Thermodynamics Review Summary
- Sonic Booms and Shock Waves
- Section 2 Preview
- Homework 1 Assignment
- Lecture 4, September 9 2020
- Thermodynamics Review (continued)
- Introduction to the Integral Forms of the Conservation Equations for Inviscid, Compressible Flow
- Conservation of Mass
- Conservton of Mopmentum
- Conservation of Energy
- A Simple Application of the 1-D Conservation Equations
- Lecture 5, September 11 2020
- A Simple Application of the 1-D Conservation Equations (Concluded)
- Thrust Equation
- Newton's Second Law and the Thrust Equation
- The Rocket Equation and Specifc Impulse
- Eaxmple Calculation
- Homework 2 Assignment
- Lecture 6, September 14 2020
- Further applications of 1-D Equations of Motion
- One-Dimensional Comprssible Flow Analysis
- Why the Shape of a Rocket Nozzle?
- Stagntion Temperature and pressure definitions
- Effects of Stagnation Heating
- Stagnation Pressure
- Lecture 8, September 16, 2020
- One-Dimensional Comprssible Flow Analysis
- Stagnation Temperature Review
- Characteristic Mach number and other invariant Sonic flow properties
- Flow Choking pressure rato
- Massflow Equations
- Lecture 8, September 18, 2020
- Massflow Equations
- A/A* Equation Introducton
- SSME Example
- Lecture 9, September 20 2020
- One-Dimensional Comprssible Flow Analysis
- Numerical Solution of A/A* Equation
- Convergence Analysis
- Initial Conditions
- Example Calculations
- Lecture 10, September 22 2020
- One-Dimensional Comprssible Flow Analysis
- Effect of pressure ratio on Nozzle performance
- Choked and Unchoked Compressible Massflow Equations
- Isentropic Choked Flow Solutions
- Lecture 11, September 24 2020
- Introduction to Normal Shock Waves
- Applying the conservation equations
- Mach Number across Shock Wave
- Calculating the Changes in Density, Pressure, and Temperature
- Stagnation pressure loss and the increase in Entropy across shock
- Second law and Impossibility for Rarefaction shockwave
- Lecture 12, September 27 2020
- Introduction to Non-Isentropic Nozzle Model
- Shockwaves in Quasi-1D Nozzle
- Explicit Formula for Exit Mach Number
- Example calculations
- Lecture 13, September 29 2020
- Example calculations, Continued
- Critical pressure ratio
- Shuttle launch Video revisited
- Introduction to the Optimal Nozzle
- Thrust Coefficient and the Optimal Nozzle Properties
- Lecture 14, October 2 2020
- Thrust Coefficient and the Optimal Nozzle Properties
- Thrust Coefficient and the Optimal Nozzle Properties
- Atlas V Example
- Atlas V first stage thrust as a function of altitude
- Optimal exit pressure criterion
- SSME and RSRM Examples
- Aerospike Nozzle Configuration as a Compensating Nozzle Solution
- Lecture 15, October 5 2020
- Project 1 Preview
- Quasi 1-D Flow with Heat Addition
- Combustor Analysis
- Lecture 16, October 7 2020
- Quasi 1-D Flow with Heat Addition (concluded)
- Combustor Model Review
- Derivation of the Rayleigh Equations
- Example Calculations
- Ramjet as a Braytion Cycle
- Lecture 17, October 9 2020
- Homework 4 Review
- Project hints
- Venturi problem review,
- Introduction to airspeed measurements
- Lecture 18, October 12 2020
- Static and Total Pressure
- Incompressible and Compressible Bernoulli Equation
- Standard Atmospherse and the Hydrostatic Equation
- Airspeed Measurements and Definitions
- Lecture 19, October 14 2020
- Airspeed Measurements and Definitions
- Rayleigh Pitot Equation
- CpMax and the Compressible Bernoulli Equation
- Example Calculations
- Lecture 20, October 16 2020
- Equivalent Airspeed Revisited
- Rayleigh Pitot Equation Examples
- Project 1 Review
- Lecture 21, October 26, 2020
- Introduction to Oblique Shock waves
- Shock wave equations,
- beta-theta-mach diagram
- Lecture 22, October 28, 2020
- beta-theta-mach diagram
- Numerical Solutions of the Beta-Theta-Mach Equation
- Newton;s Method
- Cubic Polynominal Solution
- Calculation Example
- Detached Shock Wave Discussion
- Lecture 23, October 30, 2020
- HW 6.1 Preview and Discussion
- Prandtl-Meyer Solution ot Conservation Equations
- Prandtl-Meyer Function and Mach Characteristic Lines
- Prandtl-Meyer Expansion Analysis
- Lecture 24, November 2, 2020
- Prandtl Meyer Integral Revisited
- Solving for Flow Properties across Prandtl Meyer Fan
- Maximum Allowable Convex Turning Angle
- Prandtl Meyer Expanson Summarized
- Example Calculation
- Practical Example, Shadowgraph Image Analysis
- Lecture 25, November 4, 2020
- Supersonic Flow over Flat plate at Incidence Angle
- Definitons of Lift and Drag Coefficient
- Supersonic Flat Plate Example
- Lecture 26, November 6, 2020
- HW 6 (Inlet problem) Soluton Hints
- Supersonic Flat Plate Example, revisited
- Lift, Drag, Coefficient
- Pitching Moment and Aerodynamic Center
- Mach Tuck Explained
- Finite thickness supersonic airfoil section
- Lecture 26, November 9, 2020
- HW 6.1 Review
- Finite thickness supersonic airfoil section
CL, CD for wedge airfoil
- Effect of angle of attack on Compressive lift, drag
- Incviscid L/D Profile
- Lecture 27, November 11, 2020
- Effects of Wing Sweep
- Contrasting Subsonic and Supersonic Wing Sections
- Vortical Lift and the Delta Wing
- Critical Mach Number and Divergence Drag Rise
- Compressability
Corrections
- Prandtl-Glauret
- Karman-Tsien
- Laitone'sbRule
- Ackeret's Rule
- Effect of Wing Thickness on Critical Mach Number
- Example Calculation for Critical Mach Number
- Effect of Wing Sweep on Critical Mach Number
- https://connect.usu.edu/pc6ule56hep6/
- Lecture 28, November 13 2020
- Lecture 29, November 16, 2020
- Introduction to Boundary Layers
- Laminar / Turbulent Boundary Layer Overview
- Momentum Thickness and the Laminar Boundary Layer Depth
- Closure Equation for Laminar Bondary Layer
- Viscosity and Reynold's Number
- Parabolic vs. Blasis Model for Laminar Skin Friction
- Erratic Internet Connection, backup Lecture from November 2018
- Lecture 35, November 18, 2020
- Boundary Layers Continued
- Momentum Thickness and the Turbulent Boundary Layer Depth
- Lecture 36, November 18, 2020
- Boundary Layers Continued
- Momentum Thickness and the Turbulent Boundary Layer Depth
- Turbulent Bundary Layer
- Schoenherr Plot
- Transitional Boundary Layer
- Lecture 37, November 23, 2020
- Lecture 38, November 30, 2020
- Incompressible Boundary Layer Review
- Compresible Bounday Layer, Introduction
- Correction for Compressibility Using Southerlunds Law
- Energy Equation and Boundry Layer Heating
- Recovery Factor and Prandtl Number
- Mean Boundary Layer Temperature
- Lecture 38, December 2, 2020
- Boundary layers concluded
- Final project assignment
- Lecture 39, December 4, 2020
- HW 6, 7 Review
- Funal Project Tips and Hints
- Detached Shock waves
- 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
- Detached Shock Waves (continued)
- Shock Wave Stand-Off Distance
- Approximate Description of Stagnation Point Flow Field
- Sonic Line
- Shock Wave Stand-Off Distance
- Approximate Surface Pressure Model
- Modified Newtonian Flow
- Airfoil Drag due to Blunt Leading Edge