Stereoscopic Particle Image Velocimetry Flowfield Investigation of an Unmanned Combat Air Vehicle

Roosenboom, Eric; Konrath, Robert; Schröder, Andreas; Pallek, Dieter; Otter, Dirk; Morgand, Stephane; Gilliot, Anne; Monnier, Jean-Claude; Roy, J. F. Le; Geiler, Claude; Pruvost, Jacques

doi:10.2514/1.c031587

Cited by 18 publications

(6 citation statements)

References 19 publications

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“…The nonlinear aerodynamic contribution of the vortices is well predicted. However, refinement of the mesh (case of mesh 3) allows to well predict the overshoot of the pitching moment coefficient between 15 and 16° of AoA -this has been also observed by DLR tests [14]. This phenomenon is due to the onset of thickness vortex.…”

Section: A Clean Configurationmentioning

confidence: 79%

“…With slat a new vortex can be seen, three vortices develop therefore on the upper surface. The values of the axial velocity in apex and slat vortices reach about 0,2 ∞ U , this low value indicates that sudden vortex breakdown may appear [13] [14]. The combination of high suction peak and high axial velocity close to the leading edge indicates that the cross section is close to the onset of the third vortex.…”

Section: Figure 13b Cp Distribution On Upper Surface On Saccon Confimentioning

confidence: 92%

“…For a detailed description of the topology of the flow (separation effects, vortex flow interaction), readers may refer to publications [1][8] [14]. …”

Section: A Clean Configurationmentioning

confidence: 99%

See 2 more Smart Citations

Static and Dynamic Derivatives on generic UCAV without and with leading edge control

Roy¹,

Morgand²,

Farcy³

2014

32nd AIAA Applied Aerodynamics Conference

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The present paper is devoted to low speed aerodynamics on a 53° swept and twisted blended wing body. The geometry considered is the SACCON configuration, intensively studied in the STO-AVT 161 and 201 working groups. It includes flow control investigations aiming at reducing longitudinal as well as lateral instabilities on one hand, determination of dynamic derivatives focusing on the influence of the rotation point on the other hand. The physical analysis is based on both numerical and experimental data, including static and dynamic tests carried out in two wind tunnels at Onera-Lille. It shows that leading-edge slats are very efficient to minimize the natural pitch-down/up phenomenon occuring beyond 13° AoA for this configuration. Numerical simulations were carried out with the elsA software, solving RANS equations with the Spalart-allmaras turbulence model, for various computational grid refinements; they show a good agreement with experimental data and give insight on the flow physics. It appears that phenomena such as the re-formation of leading-edge vortices, vortex breakdown, shear layer instabilities appears to be a feature of nonslender wings. The vortical flows develop at very low angles of attack, and form close to the wing surface. A non negligible sensitivity to center of rotation location on damping derivatives in pitch have also been experimentally and numerically identified and it appears therefore important to superimpose the center of rotation and the MRP during dynamic tests and computations. Nomenclature b = Wing span [ONERA model 1.0 m] c = Chord length [0.311 m] c R = Root chord [0.690m] S = Reference area, [0.3255m 2 ] U ∞ , V = Freestream velocity q ∞ = Dynamic pressure C p = Pressure coefficient, = (p-p ∞ )/q ∞ Cx,y,z = Aerodynamic force coefficients in body axis frame (axial, side and normal) Cmx,my,mz = Aerodynamic rolling, pitching and yawing moment coefficients in body axis frame (also named Cl, Cm, Cn). Reference lengths used in scaling Cmx, Cmy and Cmz coefficients are respectively b/2, c and b/2 dt = Time step f = Frequency f* = Reduced frequency, f*=f.c/V M = Mach number MRP = Model Reference Point for expression of moments-x/c R = 0.5656 CoR = Center of Rotation -2 locations are considered: x/c R = 0.809, x/c R = 0.635 1 Engineer, ONERA-DAAP/MMHD, jean-francois.le_roy@onera.fr. 2 Phd, ONERA-DAAP/MMHD, stephane.morgand@neuf.fr. 3 Engineer, ONERA-DCSD/QSV, dominique.farcy@onera.fr. Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org |

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Section: A Clean Configurationmentioning

confidence: 79%

Section: Figure 13b Cp Distribution On Upper Surface On Saccon Confimentioning

confidence: 92%

See 1 more Smart Citation

Static and Dynamic Derivatives on generic UCAV without and with leading edge control

Roy¹,

Morgand²,

Farcy³

2014

32nd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

show abstract

“…With LESs, a new vortex can be seen; three vortices therefore develop on the upper surface. The values of the axial velocity in the apex and slat vortices reach about 0.2U ∞ ; this low value indicates that the sudden vortex breakdown may appear [28,30]. The combination of a high suction peak and high axial velocity close to the leading edge indicates that the cross section is close to the onset of the third vortex.…”

Section: Evaluation Of Leading-edge Slats By Oneramentioning

confidence: 97%

Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Tormalm

Roy

Morgand

2018

Journal of Aircraft

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“…In AVT-161 the Stability and Control prediction capabilities using CFD methods have been investigated for the configuration without control devices. The research group provided an extended experimental data base for computer code validation purposes 12,13 to analyze the flow physics, aerodynamic behavior as well as the S&C parameters. The results are presented in the final report of the AVT-161 Task Group.…”

mentioning

confidence: 99%

Static and dynamic numerical simulations of a generic UCAV configuration with and without control devices

Schütte

Huber

Boelens

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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Stereoscopic Particle Image Velocimetry Flowfield Investigation of an Unmanned Combat Air Vehicle

Cited by 18 publications

References 19 publications

Static and Dynamic Derivatives on generic UCAV without and with leading edge control

Static and Dynamic Derivatives on generic UCAV without and with leading edge control

Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Static and dynamic numerical simulations of a generic UCAV configuration with and without control devices

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