“the use of vsaerocfd tool in the uav aerodynamic project“

DIASPMeeting #6

Turin 4-5 February 2003

““The Use of The Use of VSAeroVSAero CFD Tool in the UAV CFD Tool in the UAV Aerodynamic ProjectAerodynamic Project ““

Alberto PORTO – Massimiliano FONTANAPorto Porto Ricerca Ricerca FDSFDS

Giulio ROMEO - Enrico CESTINO – Giacomo FRULLAPolitecnico di Torino, Dept. of Aerospace Eng.

Porto RicercaDIASP

S.n.c.Monza, (Milano)

Italy

• Providers of CFD Software• Engineering Research • Consulting Services

DIASP Flow Analysis ComponentsGRID

GENERATIONAMIGRID

SPINGRIDALL

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

FLOW SOLUTION

VSAEROUSAEROMGAERONSAERO

POST PROCESSINGOMNIPLOT

OMNI3DTECPLOT

CAD

DIASP VSAEROSubsonic, Quasi-Steady Flow

Integral Panel/Boundary Layer Method

Complex Geometries Thick and Vortex Lattice Surfaces

Wake Modeling

Performance

Stability and Control

Boeing 727-200

• Lateral Symmetry• 4100 Body Panels• 3900 Wake Panels• 1 Wake Iteration• 3 Viscous Iterations• CPU Requirement:

SGI 4D/35 (R3000) 1.5 Hours

SGI (R10000) 5 Minutes

Boeing 727-200

Akron - AirshipDIASP

the modified Stratford criteria the modified Stratford criteria of Mendenhall35 have been of Mendenhall35 have been

added to VSAERO to find the added to VSAERO to find the cross flow separation line.cross flow separation line.

DIASP Akron - Airship

Racing car

LANGLEY FULL SCALE WIND TUNNEL LFST CFD analysis during the designee

process research

Wing tunnel drag coefficient: 0.372

CFD drag coefficient prediction: 0.358

Drag coefficient error: 4%

VICTORY Challenge Americas Cup Sailboat

CFD analysis during the designed process research

-2

-1

0

1

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0 0.5 1 1.5 2 2.5 3 3.5

S p e e d

Dif. Vs aero

0.94

0.95

0.96

0.97

0.98

0.99

1

1.01

1.02

0 1 2 3 4 5 6 7 8 9 10S p e e d

AC-b aseAC-2 VsaeroAC-2 Tank tes t

% error in drag

vs. speed for the

an upwind

case

Percentage difference in drag on

two different Americas

Cup yachts calculated

with VSAERO and tested in a towing

tank.

CFD Wave height calculation

ASI & EC (Helinet) projects

Span:73m; TOGM:750kg; Mass PL:100kgPower PL:1kW; Req. Power=6 kW; TAS=71 km/h; Altitude: 17km;Endurance: 6 monthsEffic. s.c.:20%; Effic. f.c.+elect:60%

Heliplat® Solar-powered UAV

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Heliplat®

CASA Space- EADS POLITO / ARCHEMIDE

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Heliplat®

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

DIASP

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino

Heliplat®

Preliminary wing - optimization

In the preliminary wing analysis we have tested with VSAERO three airfoils on wing solo configuration

MH32, E216, FX63137

E216 show a better E216 show a better compromise between the compromise between the

airfoil Drag and the airfoil Drag and the induced wing Drag induced wing Drag

DIASP Heliplat®Wing airfoil geometry–2D XFOIL optimization

thickness effect

camber effect

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino

combined effect

Heliplat®

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

By Using XFOIL, the optimal airfoil HPF118 has been designed instead of E216.The good performances of HPF118 are also demonstrated by experimental investigation in the Laminar Wind Tunnel in Stuttgart.

Aerodynamics Efficiency

30

32

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50

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

CL

E Rectangular Wing- FX 63137

PIANTA0- FX 63137

PIANTA0- E216

PIANTA0- HPF118

PIANTA8- HPF118

PIANTA8 twisted- HPF118 family

The optimization of wing planform have the intention to minimize induced drag. Indeed it was found that some wing planforms increase the friction drag more than the induced drag reduction. Each wing have constant span and equal surface, i.e. AR=cost.

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Heliplat®

DIASP

Why we have choose to use Vsaero panel methods technology?

• Contain the right physics

• Handle complex & arbitrary geometry

• Resolve all important physical & geometric length scale

• Reliably accurate numerics

• Timely

• Properly validated

• Can be run many, many times

CP Cf visualization all over the Airplane

Heliplat®DIASP

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Accurate pressure distribution on Heliplat complete configuratioAccurate pressure distribution on Heliplat complete configuration n CP Station cutCP Station cut

CP CP buttline buttline cutcut

Heliplat®

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Heliplat®The geometry panels are divided into several groups in order to identify

the single part contribution to the total DRAG and LIFT coefficient

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

® Trademark of Dept. of Aerospace Engineering of Politecnico di Torino

Heliplat®Propeller - analysis

Skin friction coefficient

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Aileron Stabilizer Rudder

Static derivatives Cm_δe ; CL_δe ; CFy_δa ; Cl_δa ; Cn_δa ; CFy_δr ; Cl_δr ; Cn_δr

Derivatives study

Heliplat®DIASP

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

Derivatives study

Roll rate p

Heliplat®DIASP

Pitch rate q

Dynamic derivatives (p q r): Cl_p ; Cn_p ; Cy_p; CL_q ; Cm_q ; Cn_r ; Cy_r ;Cl_r

Property of Dept. Of Aerospace Eng., Politecnico di Torino. All rights reserved

DIASPConclusions

• Vsaero is an excellent tool in order to design the best package to fulfil the design targets.

• Good correlation between numeric and experimental data.

• calculation quickness