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High Speed Aerodynamics 06: Transonic Aerodynamics: Sweep, Critical Mach Number and Drag Divergence

When the freestream Mach number approaches 1 from the subsonic side, a Critical Mach number can be defined, when, somewhere along the body, the local Mach number reaches 1. Beyond this freestream Mach number, supersonic flow occurs somewhere over the body, and terminates in shocks. The interaction of such shocks and the boundary layer can cause flow separation. The shocks and flow separation cause a sharp increase in drag as Mach number moves higher, leading to the notion of the "sound barrier".Please click to download pdf notes



Review of Low Speed Aerodynamics and Compressible Flow

The Full Potential Equation
Linearized Potential Equation and Subsonic Transformations.
Airfoils in Supersonic Flow
Wings and Bodies in Compressible Flow
Critical Mach number, drag divergence and Transonic aerodynamics
Compressible Boundary Layers

Summary of Compressible Aerodynamics

Transonic Flow Features
Transonic Small Disturbance Equation

Transonic Full Potential Equation

Supersonic Blunt Body Problem
Conical Flow
Introduction to Hypersonic Aerodynamics

Local Surface Inclination Approach

Hypersonic Small Disturbance Theory
Hypersonic Blast Wave Theory
Hypersonic Viscous Flow
High Temperature Effects in Hypersonic Gasdynamics