Compressible Flow II
£6.00
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Compressible Flow II
£6.00
Part 2 of 3 in the Compressible Flow series. Topics in this product include the theta-beta-M relation and shock polars, Mach reflection, supersonic inlet and nozzle design, shock-expansion theory for supersonic aerofoils, and Prandtl-Meyer expansion theory.
This is a 19-page PDF scan of handwritten notes, featuring clickable PDF bookmarks so you can jump straight to any page in a PDF viewer such as Adobe Acrobat. Complete page-by-page contents can be found below so you know exactly what's inside before you buy.
AerodynamicsPage-by-page contents
Aerodynamics
Page-by-page contents
- 01Oblique shock, expansion fan, conservation equations
- 02Oblique shock relations, θ-β-M relation, shock polars
- 03Mach wave vs oblique shock, attached vs detached shock, shock wave reflection
- 04Mach reflection, shock absorption, wave reflection and intersection, lambda shocks
- 05Supersonic jet engine inlets, variable geometry inlet, aerospike, inlet design, nozzle exit
- 06Finite strength isentropic waves, expansion wave/fan, pressure change across Mach wave
- 07Expansion fan equation derivation, solving for expansion wave properties
- 08Supersonic airfoil, shock-expansion theory, lift-drag of supersonic airfoil
- 09Weak oblique shocks, Ackeret theory, L vs R running shock waves, linear expansion theory
- 10Flow past curved body, lift and drag according to linear theory
- 11Wave reflection of weak waves, wave intersection or weak waves
- 12Example questions
- 13Left vs right running waves
- 14Second year recap: compressibility, Mach number, Euler equations, stagnation
- 15Stagnation (total) quantities
- 16Isentropic 1D variable area duct flow, example of choked converging duct
- 17Stationary normal shocks, examples
- 18Stationary oblique shocks, regular reflection, Mach reflection, example
- 19Prandtl-Meyer expansions, supersonic expansion theory, linear supersonic theory