Lift enhancement study for upper surface blowing technology of blended wing-body layout aircraft
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摘要:
针对翼身融合布局飞机翼上内埋发动机矩形喷口方案，提出了基于喷口修型的控制策略，采用雷诺平均Navier-Stokes（RANS）方程对翼身融合布局飞机流场进行数值模拟，分析了喷流落压比、襟翼偏角、襟翼前缘半径、喷口上偏襟翼及组合襟翼等参数对增升效能的影响。结果表明：当襟翼偏角为40°，落压比较大时，襟翼前缘负压峰值减小，喷流在襟翼前缘过早分离；增大襟翼前缘半径有助于减小喷流偏转所需要的向心力，促进喷流附着；发动机喷口上偏襟翼及组合襟翼设计，削弱了右侧涡流和表面横流对喷流附着的不利影响，促进喷流在大落压比和较大襟翼偏角下的附着，组合襟翼设计相较于喷口无修型构型，在喷流落压比为1.45、迎角为0°时，净推力平均偏转角可达56.10°，升力系数增加0.16，且在计算迎角范围内保持稳定。
Abstract:Considering the scheme of the rectangular nozzle of the engine embedded on the wing of the blended wing-body layout aircraft, a control strategy based on the modification of the engine nozzle was proposed. The flow fields of blended wing-body layout aircraft were simulated numerically based on Reynolds average Navier-Stokes equation. The effects of jet pressure ratio, flap deflection angle, flap leading edge radius, upward deflection flaps and combined flaps on the lift-enhancing effect of blended wing-body layout aircraft were analyzed. The results showed that when the flap deflection angle was 40° and the jet drop pressure ratio was large, the negative pressure peak of the leading edge of the flaps decreased and the jet flow separated prematurely at the leading edge of the flap. Increasing the leading edge radius of the flap could help reduce the centripetal force required for deflection and promote jet adhesion. The design of upward deflection flaps and combined flaps at the engine nozzle weakened the influence of the right vortex and surface cross flow on the jet adhesion, which can promote the adhesion of the jet under large drop pressure ratio and large flap angle. Compared with the unmodified nozzle configuration, the combined flap design can achieve an average net thrust deflection angle of 56.10° and the lift coefficient increased by 0.16 when jet drop pressure ratio was 1.45 and angle of attack was 0°, and the lift coefficient increment was kept stable within the range of the calculated angle of attack.
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Key words:
- blended wing-body layout /
- upper surface blowing /
- Coanda effect /
- aerodynamic design /
- powered lift
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图 3 HiLiftPW-1计算结果和试验结果对比
Figure 3. Comparison of calculated and experimental results of HiLiftPW-1
图 4 内吹式襟翼结合前缘下垂设计
Figure 4. Internally blown flap combined with leading edge drooping flap design
图 6 基础构型升力系数随迎角变化曲线
Figure 6. Variation curve of lift coefficient of original configuration with angle of attack
图 8 上表面吹气模型二维剖面示意图
Figure 8. Schematic diagram of two-dimensional cross-section of upper surface blowing model
图 9 升力系数随迎角变化曲线（R/h=1.5）
Figure 9. Variation curve of lift coefficient with angle of attack （R/h=1.5）
图 10 不同襟翼偏角Y=0.45 m剖面马赫数云图和流线图（α=12°）
Figure 10. Mach number contour and streamlines of wing Y=0.45 m profile with different flap deflection angles （α=12°）
图 11 不同襟翼偏角Y=0.45 m剖面喷流出口至襟翼弦向表面压力系数对比（α=12°）
Figure 11. Comparison of chordwise surface pressure coefficients from jet outlet to flap of wing Y=0.45 m profile with different flap deflection angles （α=12°）
图 12 旋涡图、马赫数为0.4的等值面和流线图（α=12°）
Figure 12. Vortex, Mach number of 0.4 isosurface and streamline map （α=12°）
图 13 内翼段襟翼弦向中线位置沿展向表面压力系数对比（α=12°）
Figure 13. Comparison of spanwise surface pressure coefficients at chordwise midline position of flaps （α=12°）
图 14 升力系数随迎角变化曲线（$ {\delta _{\text{f}}} $=40°）
Figure 14. Variation curve of lift coefficient with angle of attack （$ {\delta _{\text{f}}} $=40°）
图 15 不同襟翼前缘半径Y=0.45 m剖面喷流出口至襟翼弦向表面压力系数对比（α=12°）
Figure 15. Comparison of chordwise surface pressure coefficients from jet outlet to flap of wing Y=0.45 m profile with different flap leading edge radiuses （α=12°）
图 16 不同襟翼前缘半径Y=0.45 m剖面马赫数云图和流线图（α=12°）
Figure 16. Mach number contour and streamlines of wing Y=0.45 m profile with different flap leading edge radiuses （α=12°）
图 17 不同上偏襟翼偏角示意图
Figure 17. Schematic diagram of different upper flap deflection angles
图 18 不同上偏襟翼偏角构型的气动特性对比（$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
Figure 18. Comparison of aerodynamic characteristics of different upper flap deflection angles configurations （$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
图 19 不同上偏襟翼偏角构型Y=0.45 m剖面马赫数云图和流线图（λ=1.45，α=12°）
Figure 19. Mach number contour and streamlines of wingY=0.45 m profile of different upper flap deflection angles configurations （λ=1.45，α=12°）
图 20 不同上偏襟翼偏角构型旋涡图、马赫数为0.4的等值面和流线图（λ=1.45，α=12°）
Figure 20. Vortex, Mach number of 0.4 isosurface and streamline map of different upper flap deflection angles configurations （λ=1.45，α=12°）
图 21 不同上偏襟翼偏角构型表面压力系数对比（λ=1.45，α=12°）
Figure 21. Comparison of surface pressure coefficients of different upper flap deflection angles configurations （λ=1.45，α=12°）
图 23 不同上偏襟翼长度构型的气动特性对比（$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
Figure 23. Comparison of aerodynamic characteristics of different upper flap lengths configurations （$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
图 24 不同上偏襟翼长度构型Y=0.45 m剖面马赫数云图和流线图（λ=1.45，α=12°）
Figure 24. Mach number contour and streamlines of wing Y=0.45 m profile of different upper flap lengths configurations （λ=1.45，α=12°）
图 25 不同上偏襟翼长度构型旋涡图、马赫数为0.4的等值面和流线图（λ=1.45，α=12°）
Figure 25. Vortex，Mach number 0.4 isosurface and streamline map of different upper flap lengths configurations （λ=1.45，α=12°）
图 26 不同上偏襟翼长度构型表面压力系数对比（λ=1.45，α=12°）
Figure 26. Comparison of surface pressure coefficients of different upper flap lengths configurations （λ=1.45，α=12°）
图 28 组合襟翼构型的气动特性对比（$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
Figure 28. Comparison of aerodynamic characteristics of combination flaps （$ {\delta _{\text{f}}} $=40°，R/h=2.0，λ=1.45）
图 29 组合襟翼构型的马赫数云图和流线图（λ=1.45，α=12°）
Figure 29. Mach number contour and streamlines of combination flaps （λ=1.45，α=12°）
图 30 内翼段襟翼弦向中线位置沿展向表面压力系数对比（λ=1.45，α=12°）
Figure 30. Comparison of spanwise surface pressure coefficients at chordwise midline position of flaps （λ=1.45，α=12°）
图 31 不同构型净推力平均偏转角对比
Figure 31. Comparison of average deflection angles of net thrust of different configurations
表 1 模型基本参数
Table 1. Model basic parameters
参数 数值 机身/m 3.5 展长/m 2.2 前缘后掠角/（°） 40 平均气动弦长/m 1.291 半模参考面积/m2 1.952 展弦比 2.5 力矩参考点/m （0.879，0，0） 
下载: 导出CSV
表 2 净推力平均偏转角对比（λ=1.45）
Table 2. Comparison of average deflection angle of net thrust （λ=1.45）
构型 $\Delta \mu $/（°） 喷口无修型 20.75 喷口组合襟翼 56.10
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