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CFD Computations

 

The calculations have been supported by CFD computations. CFD has been performed on a computer cluster of four i7 processors with 8 cores each. A typical mesh size had about 10^7 computational cells assuring refined computations. Appropriate turbulence models have been selected in order to ensure the accuracy of the numerical solution. The propeller has been also modeled by adopting specific techniques for pressure increase areas. Various flight conditions have been modeled, ranging from negative to positive angles of attacks, different altitudes and a wide range of flight velocity. The drag polar of the UAV has been derived.

A cross-check for the drag and lift aerodynamic coefficient, together with the lift-to-drag ratios, have been performed by comparing the results from the CLASS I and CLASS II computations and the ones obtained by the CFD computations. 

 

  • Pressure contours on the surface of the HCUAV
  • Flow development in the propeller zone
  • Section view of the HCUAV mesh
  • Mesh around the HCUAV payload
  • Mesh detail around the main wing
Pressure contours on the surface of the HCUAV

Pressure contours on the surface of the HCUAV

Flow development in the propeller zone

Flow development in the propeller zone

Section view of the HCUAV mesh

Section view of the HCUAV mesh

Mesh around the HCUAV payload

Mesh around the HCUAV payload

Mesh detail around the main wing

Mesh detail around the main wing

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