airfoilcambered camber (% ch)3 thickness (% ch)8 chord (m)2 span (m)10 surface area (m2) 20 angle of...
TRANSCRIPT
-4
-2
0
2
Lower Surface
Upper Surface
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
-5
Atmosphere Std. Earth
Cp DistributionAirfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient -0.216
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Pressure Distribution
P > Pamb
P < Pamb
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
-3.75
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient -0.068
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-4
-2
0
2
Lower Surface
Upper Surface
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
-3.17
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.0
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
Lower Surface
Upper Surface
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
-2.5
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.079
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-4
-2
0
2
Lower Surface
Upper Surface
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
-1.25
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.227
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-4
-2
0
2
Lower Surface
Upper Surface
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
0
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.374
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-4
-2
0
2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
1.25
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0. 552
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
2.5
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.669
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
3.75
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.816
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
5.0
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 0.963
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
6.25
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 1.109
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
7.5
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 1.254
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-10
-8
-6
-4
-2
0
2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
8.75
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 1.399
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
RESCALE
-10
-8
-6
-4
-2
0
2
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
10
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 1.544
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
0.4
0.5
-0.4 -0.2 0 0.2 0.4 0.6 0.8 1 1.2
-10
-8
-6
-4
-2
0
2
Airfoil Cambered
Camber (% Ch) 3
Thickness (% Ch) 8
Chord (m) 2
Span (m) 10
Surface Area (m2)
20
Angle of attack (deg)
11.25
Atmosphere Std. Earth
Airfoil Parameters
Altitude (m) 0
Density (kg/m3) 1.224
Pressure (Pa) 101261
Temperature (C) 15
Lift Coefficient 1.674
Airspeed (km/hr) 150
Dynamic Pressure (Pa)
1036.5
Mach 0.12
cl vs.
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2
-5 -2.5 0 2.5 5 7.5 10 12.5 15 17.5 20
Cp Distribution
Pressure Distribution
P > Pamb
P < Pamb