Yaw Angle Effect on Flow Structure over the Nonslender Diamond Wing

Yayla, Sedat; Canpolat, Çetin; Şahi̇n, Beşi̇r; Akıllı, Hüseyin

doi:10.2514/1.j050380

Cited by 22 publications

(11 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…이런 삼각형 날개와 람다 날개의 앞전 와류 구조 에 영향을 미치는 요소는 받음각(angle of attack, α, AOA), 앞전 형상, 앞전 후퇴각, 날개 두께, 그 리고 레이놀즈 수(Reynolds number)등이 있다 [7].…”

unclassified

“…옆미끄럼각이 있는 경우 날개 좌우의 앞전 와류가 비대칭적으로 생성되며, 이로 인해 더욱 복잡한 유동 특성을 보인다. Yayla 등은 40° 앞 전 후퇴각을 가진 다이아몬드 날개(diamond wing)를 옆미끄럼각 0° ~ 15° 범위에서 유동 가 시화 실험을 수행하였으며, 앞전 와류의 생성과 와류 붕괴(vortex breakdown) 위치에 대해 연구 하였다 [7]. Yayla 등의 결과에서 0°의 옆미끄럼각 에서는 좌우 날개의 앞전 와류가 대칭으로 관측 되었지만, 4° 이상의 옆미끄럼각에서는 와류 붕 괴가 바람이 가려지는 면(leeward side)에서는 뒷전 방향으로 이동하며, 바람을 맞는 면 (windward side)에서는 앞전으로 이동하는 것을 보였다 [7].…”

unclassified

“…그러 나 10° 이후의 받음각에서는 롤링 모멘트가 감소 하는 경향을 보여주고 있으며, 옆미끄럼각이 큰 조건에서는 롤링 모멘트의 급격한 변화를 확인할 수 있다 [9,10]. Figure 9~11은 람다 날개 형상의 받음각과 옆 미끄럼각 변화에 따른 비선형적인 모멘트 특성을 명확하게 보여주고 있으며, 이런 특성은 날개 좌 우의 유동 구조와 앞전 와류 생성 및 붕괴의 비 대칭으로 인해 발생한다 [7][8][9][10][11]16,17]. Figure 12는 실험 모형의 -20°와 0° 옆미끄럼 각 조건에서의 dCm/dCL 그래프를 보여주고 있 다. dCm/dCL < 0인 경우, 항공기는 정적으로 안 정한 경향을 보인다고 판단한다 [2,16].…”

unclassified

See 2 more Smart Citations

An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration

Shim

Park²,

Oh³

2015

Journal of the Korean Society for Aeronautical & Space Scie

View full text Add to dashboard Cite

An experimental study on aerodynamic coefficients of a lambda wing configuration was performed at the low speed wind tunnel of Agency for Defense Development. The main purpose of this study was to investigate the effects of sideslip angle on various aerodynamic coefficients. In the case of 0° sideslip angle, nose-up pitching moment rapidly increases at a specific angle of attack. This unstable pitching moment characteristic is referred to as pitch break or pitch up. As the sideslip angle increases, the pitch break is found to be generated at a higher angle of attack. Rolling moment is found to show similar behavior pattern to 'pitch break' style with angle of attack at non-zero sideslip angles. This trend gets severer at greater sideslip angles. Yawing moment also shows substantial variation of the slope and the unstable directional stability with sideslip angles at higher angles of attack. These characteristics of the three moments clearly implies the difficulty of the flight control which requires efficient control augmentation system.

show abstract

unclassified

See 1 more Smart Citation

An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration

Shim

Park²,

Oh³

2015

Journal of the Korean Society for Aeronautical & Space Scie

View full text Add to dashboard Cite

show abstract

“…In other words, structure of leading edge vortices looses their coherency, when condition of ≥  is satisfied. The location of vortex breakdown moves to the apex of all wing planforms when the angle of attack,  increases slightly 4,24 . Examining side-view dye visualization experiments, wings produce separation vortices like submerged obstacles in the flow field after a certain value of angle of attack,  4 .…”

Section: Resultsmentioning

confidence: 98%

Effects of Perturbation on the Flow over Nonslender Delta Wings

Canpolat

Şahi̇n

Yayla

et al. 2015

45th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

An experimental investigation is presented to reveal the flow physics and turbulence statistics of nonslender delta and diamond wings with a sweep angle of  = 40 under perturbation condition with the amplitude of α =  +αsinet = ±0.5 during Te=2/e= 0.5s. The experiments are carried out using the techniques of dye visualization and Stereoscopic Particle Image Velocimetry (stereo-PIV) on the plan view and cross flow plane for the cases of stationary and perturbed wing as the angle of attack is varied within 7 o ≤≤17 o . In order to perform a comparison based on the wing planform, diamond wing is designed from the composition of same shape of the delta wing and an attachment part mounted on its trailing edge. This study also provides information about effects of trailing edge attachment mounted on a generic nonslender delta wing under current test conditions. It can be concluded that perturbation is beneficial in the control of flow over both wings at relatively high angles of attack, .The duration required for occurrence of flow control increases for the current period and time of perturbation, when the trailing edge attachment (diamond wing case) is employed. Beyond this, trailing edge attachment takes role in attenuation of turbulence statistics, where leading edge vortex breaks down. Nomenclature  = angle of attack, deg  = mean angle of attack, deg e = angular velocity of wing perturbation, rad/s Te = period of wing perturbation, s fe = perturbation frequency of the wing, s a(t) = dynamic angle of attack of the wings, deg U = free stream flow velocity, mm/s C' = chord of delta wing, mm C = chord of diamond wing, mm Λ = sweep angle, deg Ψ = stream function ω = vorticity 1 *Assist. Professor, 2 t = time (s) TKE = turbulence kinetic energy wRMS = RMS of vertical velocity fluctuation Re = Reynolds number based on chords of the wings <> = time-averaged quantitiy x= distance from the wing apex measured in the free-stream flow direction y = distance from the chord axis in transverse direction

show abstract

“…Yayla et al [19] studied the structures of the leading edge vortex over the nonslender diamond wing experimentally. Their experiment focused qualitatively on the flow phenomenon using the dye visualization apparatus, specifically the vortex breakdown at various sideslips (0°-15°).…”

Section: Introductionmentioning

confidence: 99%

CFD Analysis of the Sideslip Angle Effect around a BWB Type Configuration

Chang

Sheen

et al. 2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

In this study, we conducted numerical simulations for a nonslender BWB type planform with a rounded leading edge and span of 2.0 m to analyze the effect of the sideslip angle on the planform at a freestream velocity of 60 m/s. The Reynolds number based on the mean chord length was 2.9×106, and we considered the angle of attack ranging from -4° to 16° and sideslip angles up to 20°. We used an unstructured mesh with a prism layer for the boundary layer with 1.11×107 grid points, and the k−ω SST turbulence model. We analyzed force and moment coefficients with respect to variation of angle of attack and sideslip angles. Side force and rolling/yawing moment coefficients had highly nonlinear relationships with the sideslip angle while lift and drag coefficients were not significantly affected. We interpreted the mechanism of these aerodynamic characteristics based on pressure and skin friction contours. Suction pressure near the leading edge had a marked effect on the pitching and rolling moment. We identified five flow types on the blunt leading edge swept wing by skin friction lines and off-body streamlines at a high angle of attack and sideslip angles.

show abstract

Yaw Angle Effect on Flow Structure over the Nonslender Diamond Wing

Cited by 22 publications

References 18 publications

An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration

An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration

Effects of Perturbation on the Flow over Nonslender Delta Wings

CFD Analysis of the Sideslip Angle Effect around a BWB Type Configuration

Contact Info

Product

Resources

About