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EDISON_CFD

Study on Critical Mach Number According To Airfol Thickness Using EDISON_CFD

1

*,

1

,

1

1

Mach number

.

.

. , EDISON_CFD

.

Shock . EDISON_CFD

, .

Key Words : (Critical Mach Number), (Computational Fluid Dynamics),

(Thickness of Airfoil), (Transonic Flow)

1. 1.1 .

. . , , . .

1.2 EDISON

. NACA0012 NACA0016 , EDISON EDISON .

2.

2.1 .

A , A 1 . A

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Cp Mcr .

. ,

(2) (1) .

Fig.1

Fig.1 (1) (2) . (1) , . , (2) . .

2.2 EDISON_CFD SettingTable 1. CFD CFD

Airfoil NACA0012 NACA0016

20181

End Cell Space 0.0001

Stretching Types Sinh

Viscous Adiabatic Wall

Solver 2D_comp 2.0

Mach Number

1. 0.4~1(Step Size : 0.1)

2. Shock -0.1 ~ Shock

(Step Size : 0.01)

Reynolds Number 3.6510

6

AOA 0

Flow Type 1 : Turbulent Flow ( )

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NACA0012 NACA0016 . End Cell Space 0.0001 Streting Types sinh . , Solver Flow Type , . 0.4 0.1 1 Shock 0.01 .

2.3 EDISON_CFD

Table 2. CFD NACA0012 NACA0016

Mach Number 0.7

Max Mach Number 0.979

Mach Number 0.8

Max Mach Number 1.257

Mach Number 0.6

Max Mach Number 0.830

Mach Number 0.7

Max Mach Number 1.142

0.4 1 0.6 Shock

0.8 Shock .

0.7 0.8 .

0.4 1 0.6 Shock

0.7 Shock .

0.6 0.7 .

Mach Number 0.71

Max Mach Number 0.996

Mach Number 0.72

Max Mach Number 1.022

Mach Number 0.67

Max Mach Number 0.985

Mach Number 0.68

Max Mach Number 1.018

0.7 0.8 0.01

0.72 1

. Mcr=0.72

0.6 0.7 0.01

0.68 1

. Mcr=0.68

NACA0012 NACA0016 . .

2.4 (1) (2) NACA0012 . (1)

(2) Matlab . (2) NACA0012 0.43, NACA0016 0.53 . Fig.2 NACA0012 0.7371, NACA0016 0.6989. EDISON_CFD . EDISON_CFD 0.01~0.02 .

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Fig.2 Matlab

3. EDISON_CFD

. . . NACA0012 EDISON_CFD . EDISON_CFD .

. (2011-0020560) .

(1) , 2004.08.10, ,

(2) John D. Anderson, Jr., 2005.06, Fundamentals of Aerodynamics, Mcgraw.Hill

(3) Edison_CFD, edison.re.kr