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CN103419933A - Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices - Google Patents

Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices Download PDF

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Publication number
CN103419933A
CN103419933A CN201310313422XA CN201310313422A CN103419933A CN 103419933 A CN103419933 A CN 103419933A CN 201310313422X A CN201310313422X A CN 201310313422XA CN 201310313422 A CN201310313422 A CN 201310313422A CN 103419933 A CN103419933 A CN 103419933A
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lift
wing
outlet
nozzle
acceleration section
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CN103419933B (en
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顾瑞
徐惊雷
龚成
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Abstract

本发明公开了一种基于新型增升装置的前后翼布局垂直起降飞行器，包括机身，机身的前部、后部对应地配置前部增升装置、后部增升装置，所述前部增升装置、后部增升装置均包括配合使用的喷管和升力翼，喷管为在喷管出口配设扁平形加速段的扁平形喷管，且喷管的出口与升力翼的吸力面正对。因此，本发明采用的喷管为在喷管出口配设扁平形加速段的扁平形喷管，使得喷管出口的气流进一步膨胀加速并以扁平形的出口截面高速射出，同时由该扁平形加速段排出的排气射流正对升力翼的吸力面，致使气流流过升力翼吸力面的面积更大，在与压力面共同作用下，获得更大的升力分量。

Figure 201310313422

The invention discloses a vertical take-off and landing aircraft with a front and rear wing layout based on a novel high-lift device. Both the front increasing device and the rear increasing device include nozzles and lift wings for use in conjunction with the nozzle. face to face. Therefore, the nozzle used in the present invention is a flat nozzle equipped with a flat acceleration section at the outlet of the nozzle, so that the air flow at the outlet of the nozzle further expands and accelerates and shoots out at a high speed with a flat outlet section, and is accelerated by the flat section at the same time. The exhaust jet flow discharged from the section is facing the suction surface of the lift wing, so that the area of the airflow flowing through the suction surface of the lift wing is larger, and under the joint action with the pressure surface, a greater lift component is obtained.

Figure 201310313422

Description

Front and back wing layout vertically taking off and landing flyer based on novel high lift device
Technical field
The present invention relates to a kind of front and back wing layout vertically taking off and landing flyer based on novel high lift device.
Background technology
Conventional fixed wing aircraft to the having relatively high expectations of runway, is difficult to realize vertical takeoff and landing in the landing process; Helicopter can be realized vertical takeoff and landing, but helicopter has the rotor of High Rotation Speed, and blade is at wing tip place speed, to cause tip vortex, asymmetric the coming off of propeller blade tail turbulent eddy, produce periodic shock to airframe, and propulsion coefficient is lower, safety is poor, complex structure, maintenance difficulties is higher, and passenger's comfort level is also poor simultaneously, can produce strong aerodynamic noise in whole flight course, to reaching surrounding environment in machine, produce severe jamming.
Summary of the invention
Under the background of aviation fast development, require aircraft to there is better economy, traveling comfort and safety.The present invention is directed to the deficiencies in the prior art, a kind of front and back wing layout vertically taking off and landing flyer based on novel high lift device is provided, this aircraft can increase the synthetic thrust gain of former jet pipe 10%-50%, makes whole aircraft obtain more reasonably thrust and a lift distribution, and this aircraft will have vertical takeoff and landing, short take-off and landing (STOL), the low speed landing, the anti-stall of the large angle of attack of low speed, tight spiral, crosswind impact is little, the technical advantage such as fly safer.This technology can be widely used in dual-use aeronautical technology field, has wide market outlook.
For realizing above technical purpose, the present invention will take following technical scheme:
A kind of front and back wing layout vertically taking off and landing flyer based on novel high lift device, comprise fuselage, the front portion of fuselage, rear portion configure anterior high lift device, rear portion high lift device accordingly, described anterior high lift device, rear portion high lift device include jet pipe and the lift wing be used in conjunction with, described jet pipe is for set the pancake jet pipe of pancake accelerating sections at nozzle exit, and the suction surface of the outlet of jet pipe and the lift wing over against; The cross-sectional plane that the nozzle exit that described pancake accelerating sections is D by equivalent diameter is corresponding, centered by nozzle axis line, shrink and to transit to the accelerating sections outlet and form; In described pancake accelerating sections, from the part that nozzle exit extends out, length is the whole length 20%-60% of pancake accelerating sections, the rangeability of cross-sectional area is not more than ± and 3%, and the cross-sectional area of accelerating sections exit position is 90% ~ 100% of nozzle exit cross-sectional area; The span of spacing g between described nozzle exit and accelerating sections outlet is: 2D<=g<=5D; The span that accelerating sections goes out open height h is: 0.1D<=h<=0.95D.
As to further improvement of the present invention, the horizontal throw between the outlet of the accelerating sections of the lift wing trailing edge of described anterior high lift device and the pancake jet pipe of rear portion high lift device is L 1, its span is 0.5c<=L 1<=5c; The jet pipe of anterior high lift device and the jet pipe of rear portion high lift device distance in the vertical direction is H 1, its span is 0<=H 1<=5h; Wherein: c means the chord length of the lift wing, and h means that accelerating sections goes out open height.
As to further improvement of the present invention, described suction surface integral body is arc setting; The attached wall of exhaust jet stream of accelerating sections outlet output is in the surface of suction surface, exhaust jet stream is through the anterior acceleration fast of the suction surface between aerofoil profile leading edge and aerofoil profile maximum ga(u)ge, and slowly slow down in the suction surface rear portion of aerofoil profile maximum ga(u)ge and airfoil trailing edge until the suction surface surface pressure lower than ambient pressure, the air-flow flowed out from airfoil trailing edge subsequently penetrates along the direction drainage of angle b, the thrust that this drainage along angle b direction has forward and makes progress; Wherein: angle b means the angle of suction surface trailing edge place's tangential direction and horizontal direction.
As to further improvement of the present invention, the acting face integral body of the described lift wing is arc setting, and this arc-shaped acting face and lift nose of wing form can prevent that exhaust jet stream from clashing into after suction surface jet attached flow to the profile of acting face.
As to further improvement of the present invention, the span of the wing chord of the described lift wing and horizontal direction angle a is: 0 °<=90 ° of a ﹤; The span of the lift wing 5 leading edge angle e is: 10 °<=e<=80 °; The span of the chord length c of the lift wing is 1D<=c<=10D; The maximum ga(u)ge d of the lift wing with the span of the ratio of the chord length c of aerofoil profile is: 0.1<=d/c<=0.8, maximum ga(u)ge position
Figure DEST_PATH_IMAGE001
Span be: 0.1<= <=0.7, x wherein dMean the distance of aerofoil profile maximum ga(u)ge to leading edge; The maximum camber f of this aerofoil profile with the span of the ratio of the chord length c of aerofoil profile is: 0.1<=f/c<=0.8, the maximum camber position is
Figure 201310313422X100002DEST_PATH_IMAGE002
Span be: 0.1<=
Figure 533119DEST_PATH_IMAGE002
<=0.7, x wherein fMean the distance of aerofoil profile maximum camber to leading edge; The scope of the angle b of suction surface trailing edge place's tangential direction and horizontal direction is: 20 °<=b<=120 °; The span of the angle k of acting face leading edge and horizontal direction is 0 °<=k<=80 °; The span of the angle j of acting face trailing edge and horizontal direction is 5 °<=k ﹤ b.
As to further improvement of the present invention, the vertical distance H of described lift nose of wing and accelerating sections center line of discharge 2Span be: 0<=H 2<=30h, and the lift nose of wing is apart from the horizontal throw L of accelerating sections outlet 2Span be: h<=L 2<=10h.
According to above technical scheme, with respect to prior art, the present invention has advantages of following:
1, the present invention is improved existing nozzle structure, at the equipped pancake accelerating sections of nozzle exit, the pancake acceleration/accel is by special profile designing requirement, making the air-flow of nozzle exit further expand accelerates and penetrates at a high speed with pancake outlet, the exhaust jet stream of simultaneously being discharged by this pancake accelerating sections is over against the suction surface of the lift wing, cause air flow stream to cross the area of lift wing suction surface larger, with the acting face combined action under, obtain larger lift component;
2, the present invention has all carried out particular design to suction surface, the acting face of aerofoil profile, with the momentum to the outlet of pancake accelerating sections, redistributed, obtain the lift lift-rising by specific how much profiles, the angle b of reasonable arrangement suction surface trailing edge in addition, make the ratio of thrust and lift reach optimum, finally obtain the synthetic thrust gain of 10%-50%;
3, this device makes the lift wing just can obtain larger lift in quiescence, therefore can make aircraft realize short take-off and landing (STOL), even the function of vertical takeoff and landing, simultaneously, the efficiency of this device is higher than helicopter, and safety is higher, and the difficulty of complexity and maintenance all descends greatly.The distribution of this thrust and lift, make aircraft that good flight stability just be arranged when low speed, can realize the flying for long time in less spatial domain.
4, the lift wing can be rotated along lift nose of wing point, thereby changes lift on the lift wing and the distribution of thrust, makes aircraft based on this device can realize the conversion of high-speed flight and low-speed operations.
The accompanying drawing explanation
Fig. 1 is the three-dimensional structure schematic diagram of the front and back wing layout vertically taking off and landing flyer based on novel high lift device of the present invention;
Fig. 2 is the two-dimensional structure schematic diagram of the front and back wing layout vertically taking off and landing flyer based on novel high lift device of the present invention;
In Fig. 1,2: front pancake jet pipe 1; The front lift wing 2; Front lift wing suction surface 3; Front lift wing lower surface 4; Rear pancake jet pipe 5; The rear lift wing 6; Fuselage 7; Rear lift wing suction surface 8; Rear lift wing lower surface 9;
The open height that goes out of front pancake jet pipe, rear pancake jet pipe is h; Horizontal throw between the accelerating sections outlet of front lift wing trailing edge and rear pancake jet pipe is L1; Front pancake jet pipe and rear pancake jet pipe distance in the vertical direction is H1;
Fig. 3 is the structural representation of anterior high lift device of the present invention;
Fig. 4 a is the birds-eye view of pancake accelerating sections of the present invention; Fig. 4 b is the left view of pancake accelerating sections of the present invention; Fig. 4 c is the front view of pancake accelerating sections of the present invention; Fig. 4 d is the M-M cutaway view of pancake accelerating sections of the present invention; Fig. 4 e is the N-N cutaway view of pancake accelerating sections of the present invention; Fig. 4 f is the P-P cutaway view of pancake accelerating sections of the present invention; Fig. 4 g is the R-R cutaway view of pancake accelerating sections of the present invention;
In figure: front pancake jet pipe 1; Pancake accelerating sections 11; Nozzle exit 12; Accelerating sections outlet 13; The front lift wing 2; The suction surface 3 of the front lift wing; The acting face 4 of the front lift wing;
Nozzle exit equivalent diameter D; Accelerating sections goes out open height h;
Vertical distance H2 between lift nose of wing and accelerating sections center line of discharge; The lift nose of wing is apart from the horizontal throw L2 of accelerating sections outlet;
The angle a of the wing chord of the lift wing and horizontal direction; Lift nose of wing angle e; The maximum ga(u)ge d of the lift wing; The chord length c of the lift wing; The maximum camber f of the lift wing; The angle k of acting face leading edge and horizontal direction; The angle j of acting face trailing edge and horizontal direction; Suction surface is at the angle b of tangential direction and the horizontal direction at trailing edge place; The aerofoil profile maximum ga(u)ge to leading edge apart from x dThe aerofoil profile maximum camber to leading edge apart from x f.
The specific embodiment
Accompanying drawing discloses the structural representation of preferred embodiment involved in the present invention without limitation; Explain technical scheme of the present invention below with reference to accompanying drawing.
As depicted in figs. 1 and 2, front and back wing layout vertically taking off and landing flyer based on novel high lift device of the present invention, comprise fuselage, the front portion of fuselage, rear portion configure anterior high lift device, rear portion high lift device accordingly, described anterior high lift device, rear portion high lift device include jet pipe and the lift wing be used in conjunction with, described jet pipe is for set the pancake jet pipe of pancake accelerating sections at nozzle exit, and the suction surface of the outlet of jet pipe and the lift wing over against; Horizontal throw between the accelerating sections outlet of the lift wing trailing edge of described anterior high lift device and the pancake jet pipe of rear portion high lift device is L 1, its span is 0.5c<=L 1<=5c; The jet pipe of anterior high lift device and the jet pipe of rear portion high lift device distance in the vertical direction is H 1, its span is 0<=H 1<=5h; Wherein: anterior high lift device comprises front pancake jet pipe 1 and the front lift wing 2, and wherein, the front lift wing 2 comprises front lift wing suction surface 3, front lift wing lower surface 4; The rear portion high lift device comprises rear pancake jet pipe 5 and the rear lift wing 6, and the rear lift wing 6 comprises rear lift wing suction surface 8, rear lift wing lower surface 9.C means the chord length of the lift wing, and h means that accelerating sections goes out open height.In the aircraft flight process, the described front lift wing 2 and the rear lift wing 6, can rotate around the lift nose of wing, thereby change the shooting angle after the attached body suction surface of high velocity air, thereby be adjusted at lift and thrust profiles on high lift device, in real time the aircraft aeroperformance in the change of flight process.In addition, the front lift wing 2 and the rear lift wing 6 can be rotated along lift nose of wing point, thereby the lift on the change lift wing and the distribution of thrust realize the real-time adjusting of the aerodynamic force of aircraft in flight course.
Fig. 3 discloses the structural representation of anterior high lift device of the present invention, wherein: comprise front pancake jet pipe 1, pancake accelerating sections 11 and the front lift wing 2.As shown in Fig. 4 a-4g, schematic diagram for pancake accelerating sections 11, the nozzle exit section that described pancake accelerating sections 11 is is D by equivalent diameter is through length g, transit to is highly the profile transition phase in the pancake cross section of h, 20% ~ 60% the part that it is characterized in that described pancake accelerating sections streamwise front portion, each sectional area and jet area are consistent substantially, the area change amplitude is not more than ± and 3%, part after this, it is large that each sectional area progressively becomes, platypelloid type accelerating sections exit sectional area is than little 10% left and right of jet area.
The scope of the length g of pancake accelerating sections 11 is 2D<=g<=5D, and the scope that accelerating sections goes out open height h is 0.1D<=h<=0.95D.The wing chord of the described front lift wing 2 and horizontal direction angle a, span is 0 °<=90 ° of a ﹤.The leading edge of the described front lift wing 2 is apart from pancake accelerating sections 11 outlet horizontal throw L, and span is h<=L<=10h; Leading edge is apart from pancake accelerating sections 11 center line of discharge vertical distance H, and span is 0<=H<=30h, the front lift wing 2 leading edge angle e, and span is 10 °<=e<=80 °.The outlet exhaust jet stream of pancake accelerating sections 11 is over against the suction surface 3 on the front lift wing 2 tops.The maximum ga(u)ge of the front lift wing 2 is d/c with the ratio of the chord length of aerofoil profile, and span is 0.1<=d/c<=0.8, the maximum ga(u)ge position
Figure 312856DEST_PATH_IMAGE001
Span be 0.1<=
Figure 708065DEST_PATH_IMAGE001
<=0.7.The maximum camber of this aerofoil profile is f/c with the ratio of the chord length of aerofoil profile, and span is 0.1<=f/c<=0.8, and the maximum camber position is
Figure 210853DEST_PATH_IMAGE002
, span is 0.1<=
Figure 33316DEST_PATH_IMAGE002
<=0.7; The span of the chord length c of the front lift wing 2 is 1D<=c<=10D; The scope of the angle b of suction surface 3 trailing edge place tangential directions and horizontal direction is 20 °<=b<=120 °.One of the whole formation of suction surface 3 is arc, make the attached wall of high velocity air of pancake accelerating sections 11 outlets in the surface of suction surface 3, forwardly first accelerate fast slowly to slow down at rear portion, impel the suction surface surface pressure lower than ambient pressure, subsequently remaining air-flow is penetrated along the direction drainage of angle b, thereby forward and the power made progress.
The angle k of acting face 4 leading edges and horizontal direction, span is 0 °<=k<=80 °.The angle j of acting face 4 trailing edges and horizontal direction, span is 5 °<=k ﹤ b.Therefore, the whole formation of acting face 4 is arc, with the front lift wing 2 leading edges, matches, and prevents that the high velocity air of pancake accelerating sections 11 outlets from, after clashing into suction surface 3, having a little air-flow along wall, and jet attached flow, to acting face 4, makes acting face 4 pressure drops.
Pancake accelerating sections 11 of the present invention is accelerated to pancake outlet by the high velocity air of front pancake jet pipe 1 outlet, makes the area of the suction surface 3 that air flow stream crosses larger, from the common effect of acting face 4 obtain larger lift component.The front lift wing 2 is redistributed the momentum of pancake accelerating sections 11 outlets, obtain the lift lift-rising by specific how much profiles, the angle b of reasonable arrangement suction surface 3 trailing edges, make the ratio of thrust and lift reach optimum in addition, finally obtains the synthetic thrust gain of 10%-50%.This device makes the lift wing just can obtain larger lift in quiescence, therefore can make aircraft realize short take-off and landing (STOL), even the function of vertical takeoff and landing, simultaneously, the efficiency of this device is higher than helicopter, and safety is higher, and the difficulty of complexity and maintenance all descends greatly.The distribution of this thrust and lift, make aircraft that good flight stability just be arranged when low speed, can realize the flying for long time in less spatial domain.The front lift wing 2 can be rotated along lift nose of wing point, thereby the lift on the lift wing 2 and the distribution of thrust before changing makes aircraft based on this device can realize the conversion of high-speed flight and low-speed operations.
Described front pancake jet pipe 1 outlet can be circle, ellipse, square equal cross-section.
The above-mentioned concrete structure that discloses particularly anterior high lift device, rear portion high lift device and anterior high lift device structure are identical, at this, will tire out and state no longer one by one.
Pancake jet pipe of the present invention impacts lift wing upper surface suction surface by high velocity air, produce the gain of the 10%-50% of synthetic thrust, thereby can further save energy consumption, and this synthetic thrust is useful and aircraft is realized vertical takeoff and landing or short take-off and landing (STOL).
The layout of the front and back wing can comparatively be easy to realize the balance control of lift and aircraft weight, facilitates the manipulation of aircraft.
Therefore this aircraft just can obtain larger lift in quiescence, can make aircraft realize vertical takeoff and landing, the function of vertical takeoff and landing even, and simultaneously, the efficiency of this device is higher than helicopter, and safety is higher, and the difficulty of complexity and maintenance all descends greatly.The distribution of this thrust and lift, make aircraft that good flight stability just be arranged when low speed, can realize the flying for long time in less spatial domain.

Claims (6)

1.一种基于新型增升装置的前后翼布局垂直起降飞行器，包括机身，机身的前部、后部对应地配置前部增升装置、后部增升装置，所述前部增升装置、后部增升装置均包括配合使用的喷管和升力翼，其特征在于：所述喷管为在喷管出口配设扁平形加速段的扁平形喷管，且喷管的出口与升力翼的吸力面正对；所述扁平形加速段通过当量直径为D的喷管出口对应的横截面、以喷管轴线为中心线、收缩过渡至加速段出口而形成；所述的扁平形加速段中，从喷管出口延伸出来、长度为扁平形加速段整个长度20%-60%的部分，横截面面积的变化幅度不大于±3%，而处于加速段出口位置的横截面面积为喷管出口横截面面积的90%~100%；所述喷管出口与加速段出口之间的间距g的取值范围为：2D≦g≦5D；加速段出口高度h的取值范围为：0.1D≦h≦0.95D。 1. A vertical take-off and landing aircraft with front and rear wing layout based on a new type of increasing lift device, comprising a fuselage, the front portion and the rear portion of the fuselage are correspondingly equipped with a front portion increasing lift device and a rear portion increasing lift device, the front portion increasing lift device The lifting device and the rear lifting device all include a nozzle pipe and a lift wing used in conjunction, and it is characterized in that: the nozzle pipe is a flat nozzle equipped with a flat acceleration section at the outlet of the nozzle, and the outlet of the nozzle is connected to the The suction surface of the lift wing is facing; the flat acceleration section is formed by the corresponding cross-section of the nozzle outlet with an equivalent diameter of D, taking the axis of the nozzle as the center line, and shrinking and transitioning to the outlet of the acceleration section; the flat acceleration section In the acceleration section, for the part extending from the outlet of the nozzle and having a length of 20%-60% of the entire length of the flat acceleration section, the variation range of the cross-sectional area is not more than ±3%, while the cross-sectional area at the exit of the acceleration section is 90%~100% of the cross-sectional area of the outlet of the nozzle; the range of the distance g between the outlet of the nozzle and the outlet of the acceleration section is: 2D≦g≦5D; the range of the height h of the outlet of the acceleration section is: 0.1D≦h≦0.95D. 2.根据权利要求1所述基于新型增升装置的前后翼布局垂直起降飞行器，其特征在于：所述前部增升装置的升力翼尾缘与后部增升装置的扁平形喷管的加速段出口之间的水平距离为L1，其取值范围为0.5c≦L1≦5c；前部增升装置的喷管和后部增升装置的喷管在垂直方向的距离为H1，其取值范围为0≦H1≦5h；其中：c表示升力翼的弦长，而h表示加速段出口高度。 2. according to claim 1, the front and rear wing layout vertical take-off and landing aircraft based on the novel increasing lift device is characterized in that: the lift wing trailing edge of the front increasing lift device and the flat nozzle of the rear increasing lift device The horizontal distance between the outlets of the acceleration section is L 1 , and its value range is 0.5c≦L 1 ≦5c; the vertical distance between the nozzles of the front high-lift device and the rear high-lift device is H 1 , whose value range is 0≦H 1 ≦5h; where: c represents the chord length of the lift wing, and h represents the exit height of the acceleration section. 3.根据权利要求1或2所述基于新型增升装置的前后翼布局垂直起降飞行器，其特征在于：所述吸力面整体呈弓形设置；加速段出口输出的排气射流附壁于吸力面的表面，排气射流经处于翼型前缘与翼型最大厚度之间的吸力面前部快速加速，而翼型最大厚度与翼型后缘的吸力面后部缓慢减速直至吸力面表面压力低于环境压力，随后从翼型后缘流出的气流沿夹角b的方向引流射出，该沿夹角b方向的引流具有向前和向上的推力；其中：夹角b表示吸力面尾缘处切线方向与水平方向的夹角。 3. According to claim 1 or 2, the vertical take-off and landing aircraft with front and rear wing layout based on the novel high-lift device is characterized in that: the suction surface is arranged in a bow shape as a whole; the exhaust jet output from the outlet of the acceleration section is attached to the suction surface The surface of the airfoil, the exhaust jet quickly accelerates through the front of the suction surface between the leading edge of the airfoil and the maximum thickness of the airfoil, while the rear of the suction surface between the maximum thickness of the airfoil and the trailing edge of the airfoil slowly decelerates until the surface pressure of the suction surface is lower than Ambient pressure, then the airflow flowing out from the trailing edge of the airfoil is ejected along the direction of the angle b, and the drainage along the direction of the angle b has forward and upward thrust; where: the angle b represents the tangent direction at the trailing edge of the suction surface The angle with the horizontal direction. 4.根据权利要求3所述基于新型增升装置的前后翼布局垂直起降飞行器，其特征在于：所述升力翼的压力面整体呈弓形设置，该弓形状压力面与升力翼前缘构成能够防止排气射流撞击吸力面后附壁流动至压力面的型面。 4. according to claim 3, the vertical take-off and landing aircraft based on the new type of lift device, characterized in that: the pressure surface of the lift wing is arc-shaped as a whole, and the bow-shaped pressure surface and the leading edge of the lift wing can form a vertical take-off and landing aircraft. A profile that prevents the exhaust jet from flowing to the pressure surface after the exhaust jet hits the suction surface. 5.根据权利要求4所述基于新型增升装置的前后翼布局垂直起降飞行器，其特征在于：所述升力翼的翼弦与水平方向夹角a的取值范围为：0°≦a﹤90°；升力翼5前缘夹角e的取值范围为：10°≦e≦80°；升力翼的弦长c的取值范围为1D≦c≦10D；升力翼的最大厚度d与翼型的弦长c之比的取值范围为：0.1≦d/c≦0.8，最大厚度位置                                               
Figure 193264DEST_PATH_IMAGE002
的取值范围为：0.1≦
Figure 110405DEST_PATH_IMAGE002
≦0.7，其中xd表示翼型最大厚度到前缘的距离；该翼型的最大弯度f与翼型的弦长c之比的取值范围为：0.1≦f/c≦0.8，最大弯度位置为的取值范围为：0.1≦
Figure 160717DEST_PATH_IMAGE004
≦0.7，其中xf表示翼型最大弯度到前缘的距离；吸力面尾缘处切线方向与水平方向的夹角b的范围为：20°≦b≦120°；压力面前缘与水平方向的夹角k的取值范围为0°≦k≦80°；压力面后缘与水平方向的夹角j的取值范围为5°≦k﹤b。 5. According to claim 4, the vertical take-off and landing aircraft with front and rear wing layout based on the novel high-lift device is characterized in that: the value range of the included angle a between the chord of the lift wing and the horizontal direction is: 0°≦a﹤ 90°; the value range of the leading edge angle e of the lift wing 5 is: 10°≦e≦80°; the value range of the chord length c of the lift wing is 1D≦c≦10D; the maximum thickness d of the lift wing and the wing The value range of the chord length c ratio of the type is: 0.1≦d/c≦0.8, the maximum thickness position
Figure 193264DEST_PATH_IMAGE002
The value range is: 0.1≦
Figure 110405DEST_PATH_IMAGE002
≦0.7, where x d represents the distance from the maximum thickness of the airfoil to the leading edge; the value range of the ratio of the maximum camber f of the airfoil to the chord length c of the airfoil is: 0.1≦f/c≦0.8, the maximum camber position for The value range is: 0.1≦
Figure 160717DEST_PATH_IMAGE004
≦0.7, where x f represents the distance from the maximum camber of the airfoil to the leading edge; the range of the angle b between the tangent direction and the horizontal direction at the trailing edge of the suction surface is: 20°≦b≦120°; The value range of the included angle k is 0°≦k≦80°; the value range of the included angle j between the trailing edge of the pressure surface and the horizontal direction is 5°≦k<b. 6.根据权利要求1所述基于新型增升装置的前后翼布局垂直起降飞行器，其特征在于：所述升力翼前缘与加速段出口中心线的垂直距离H2的取值范围为：0≦H2≦30h，而升力翼前缘距离加速段出口的水平距离L2的取值范围为：h≦L2≦10h。 6. according to claim 1, the vertical take-off and landing aircraft with front and rear wing layout based on the novel increasing lift device is characterized in that: the value range of the vertical distance H2 between the leading edge of the lift wing and the outlet centerline of the acceleration section is: 0 ≦H 2 ≦30h, and the value range of the horizontal distance L 2 from the leading edge of the lift wing to the exit of the acceleration section is: h≦L 2 ≦10h.
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CN113071667A (en) * 2021-03-12 2021-07-06 南京航空航天大学 Method for improving wave resistance of amphibious aircraft based on active flow control technology

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Inventor after: Xu Jinglei

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