چند مسئله حل شده با روش های عددی همراه با مقایسه با نتایج ازمایشگاهی

تاريخ : شنبه هفتم مرداد ۱۳۹۱

منبع:http://www.grc.nasa.gov/WWW/wind/valid/archive.html

The cases of the archive include:

Mach	Grid	Gas	Description
0.00	SG	IG	Sod's Shock Tube
0.05	SG	IG	Incompressible Driven Cavity
0.10	SG	IG	Blasius Incompressible Laminar Flat Plate
0.13	SG	IG	Driver-Seegmiller Incompressible Backward-Facing Step
0.15	SG	IG	Fraser Subsonic Conical Diffuser
0.20	SG	IG	Incompressible, Buice Axisymmetric Diffuser
0.20	OG	IG	NLR Airfoil with Flap
0.20	SG,UG	IG	Incompressible, Turbulent Flat Plate
0.20	SG	IG	Laminar Flow over a Circular Cylinder
0.20	SG	IG	Ejector Nozzle
0.21	SG	IG	Low-Subsonic S-Duct
0.30	SG	IG	Steady, Inviscid Flow in a Converging-Diverging Verfication (CDV) Nozzle
0.30	SG	IG	Subsonic Annular Duct
0.40	SG	IG	Square Jet Injection
0.46	SG,UG	IG	Sajben Transonic Converging-Diverging Diffuser
0.73	SG	IG	RAE 2822 Transonic Airfoil
0.80	SG	IG	MADIC 2D Axisymmetric CD Boattail Nozzle
0.80	SG	IG	MADIC 3D CD Boattail Nozzle
0.84	SG	IG	Transonic, ONERA M6 Wing
0.97	SG,UG	IG	Acoustic Reference Nozzle with Mach 0.97, Unheated Jet Flow
1.30	SG	IG	Normal shock at Mach 1.3
1.82	SG	CH	Hydrogen-Air Combustion in a Channel
2.00	SG, UG	IG	Mach 2.0 Flow over a 15-Degree Wedge
2.00	SG, UG	IG	Seiner Nozzle with Mach 2.0, Heated Jet Flow
2.22	SG	IG	Supersonic Axisymmetric "submerged" Jet Flow
2.35	SG	IG	Conical shock on a 10 degree cone at Mach 2.35
2.44	SG	CH	Dual-Stream Hydrogen-Air Mixing
2.50	SG, UG	IG	Oblique shock on a 15 degree wedge at Mach 2.5
2.50	SG, UG	IG	Prandtl-Meyer 15 Degree Expansion Corner at Mach 2.5
4.50	SG,UG	IG	Mach 4.5 Flow over a Flat Plate
5.00	UG	IG	Mach 5.0 Shock Boundary Layer Interaction
7.00	SG	IG	Mach 7, Laminar 15-degree Ramp
15.00	SG	IG	Hypersonic Cylinder