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Design of two Airfoils for a Canard Airplane

Martin Hepperle

 

For the airplane-project 'YAKA' (a development of the Ecole Nationale Supériore at Toulouse, France) two airfoils have been developed: Section MH 200 for application in the main wing and section MH 201 for the canard wing.

All results were obtained by using the Eppler-Code [1] for design and analysis of the airfoils. The design method of this code is based on conformal mapping while the analysis of various flap deflections is performed by a higher order panel method. Once the velocity-distribution is known, the drag-coefficients are calculated using an integral boundary layer analysis method. The lift- and momentum-coefficients from the potential theory are corrected for boundary layer effects (especially separation).

Section MH 200

The airfoil MH 200 has been designed to surpass the aerodynamic characteristics of the NACA 631-412 section while conserving maximum lift coefficient, momentum coefficient and at least retaining the thickness of 12 percent.

The results show some improvements:

Section MH 201

The airfoil MH 201 was intended to replace the NASA GA(W)-2 airfoil. The airfoil shows a smoother drag polar at the same or lower drag coefficients than the GA(W)-2. Flap deflections are more effective when compared to the NASA airfoil.

Bibliography

[1] R.Eppler, D.Somers: ‘A Computer Program for the Design and Analysis of Low-Speed Airfoils’, NASA TM-80210, 1980.

[2] R.J.Mc Ghee, W.D.Beasley: ‘Low Speed Aerodynamic Characteristics of a 13 Percent thick Airfoil Section designed for General Aviation Applications’, NASA TM X-72697, 1975.

Appendix:  Figures

3-View drawing of the YAKA project.

Figure 1:  Three view drawing of the ‘YAKA’ project.

 

Aerodynamic characteristics of the NACA 631-412.

Figure 2: Velocity distributions and drag polars of NACA 631-412, smooth surface.

 

Aerodynamic characteristics of the MH 200.

Figure 3: Velocity distributions and drag polars of MH 200, smooth surface.

 

Aerodynamic characteristics of the rough NACA 631-412.

Figure 4: Drag polars of NACA 631-412, rough surface.

 

Aerodynamic characteristics of the rough MH 200.

Figure 5: Drag polars of MH 200, rough surface.

 

Aerodynamic characteristics of the MH 200 with 5° flaps.

Figure 6: Drag polars of MH 200 with a flap deflection of +5°, smooth surface.

 

Aerodynamic characteristics of the rough MH 200 with 5° flaps..

Figure 7: Drag polars of MH 200 with a flap deflection of +5°, rough surface.

 

Aerodynamic characteristics of the MH 200 with -5° flaps.

Figure 8: Drag polars of MH 200 with a flap deflection of -5°, smooth surface.

 

Aerodynamic characteristics of the rough MH 200 wth -5° flaps.

Figure 9: Drag polars of MH 200 with a flap deflection of -5°, rough surface.

 

Aerodynamic characteristics of the NASA GAW-2.

Figure 10: Drag polars of NASA GA(W)-2, smooth surface.

 

Aerodynamic characteristics of the MH 201.

Figure 11: Drag polars of MH 201, smooth surface.

 

Aerodynamic characteristics of the MH 201 with +5° flaps.

Figure 12: Drag polars of MH 201 with a flap deflection of +5°, smooth surface.

 

Aerodynamic characteristics of the MH 201 with -5° flaps.

Figure 13: Drag polars of MH 201 with a flap deflection of -5°, smooth surface.


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