SOURCE PANEL METHOD

Computational Pressure coefficient distribution result for angle of attack of 3°

Pressure coefficient distribution plotted from the values posted on Moodle

0 0.2 0.4 0.6 0.8 1 1.2

-1.5

-1

-0.5

0

0.5

1

1.5

Pressure coefficient distibution

x/c

Cp

The results between the computational pressure coefficient distribution are similar but at trailing edge of the airfoil the pressure distribution in the computation assignment is bigger because we assume inviscid incompressible

Computational Pressure coefficient distribution result for angle of attack of 0°

Pressure coefficient distribution plotted from the values posted on Moodle

0 0.2 0.4 0.6 0.8 1 1.2

-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

Chart Title

Conclusion

The results between the computational pressure coefficient distributions are similar but at trailing edge of the airfoil the pressure distribution for the computational assignment is bigger because we assume inviscid incompressible and in reality viscous forces are high at the trailing edge due its sharpness.