CN110435873B - Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family - Google Patents

Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family Download PDF

Info

Publication number
CN110435873B
CN110435873B CN201910752594.4A CN201910752594A CN110435873B CN 110435873 B CN110435873 B CN 110435873B CN 201910752594 A CN201910752594 A CN 201910752594A CN 110435873 B CN110435873 B CN 110435873B
Authority
CN
China
Prior art keywords
airfoil
wing
chord
unmanned aerial
aerial vehicle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201910752594.4A
Other languages
Chinese (zh)
Other versions
CN110435873A (en
Inventor
昌敏
陈娇娇
孙杨
汪辉
屈峰
白俊强
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northwestern Polytechnical University
Original Assignee
Northwestern Polytechnical University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northwestern Polytechnical University filed Critical Northwestern Polytechnical University
Priority to CN201910752594.4A priority Critical patent/CN110435873B/en
Publication of CN110435873A publication Critical patent/CN110435873A/en
Application granted granted Critical
Publication of CN110435873B publication Critical patent/CN110435873B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Toys (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention provides a cruising self-balancing half-wing body integrated tailless unmanned aerial vehicle wing type family, which comprises a first wing type, a second wing type and a third wing type; the spread positions of the first airfoil, the second airfoil and the third airfoil on the wing are respectively as follows: the first airfoil is positioned at the root of the wing, the second airfoil is positioned at 28.1 percent of the span direction of the wing, and the third airfoil is positioned at the tip of the wing; the maximum relative thicknesses of the first airfoil, the second airfoil and the third airfoil are 14.00%, 11.00% and 11.90% respectively; the relative positions of the maximum thicknesses are 30.60%, 33.90%, respectively. Has the following advantages: the airfoil family provided by the invention is designed aiming at the cruise state of the tailless layout unmanned aerial vehicle, the unmanned aerial vehicle realizes cruise self-balancing under low Mach number and low Reynolds number, and has the characteristics of high lift, low resistance, high lift-drag ratio and moderate stall characteristic.

Description

Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family
Technical Field
The invention belongs to the technical field of aerodynamic shape/airfoil design, and particularly relates to a cruise self-balancing half-airfoil integrated tailless unmanned aerial vehicle airfoil family.
Background
The unmanned aerial vehicle technology is developed vigorously in the world, and unmanned aerial vehicles with various performances, advanced technology and wide application are continuously emerged. Unmanned aerial vehicle has advantages such as mobility is strong, cost-effectiveness ratio is high, the use is nimble, along with the continuous development of modern technology, unmanned aerial vehicle has all obtained extensive application in civilian and military field. In order to improve the cruising performance of the unmanned aerial vehicle, the cruising self-leveling capability is particularly important in the use of the unmanned aerial vehicle.
Half wing body fusion unmanned aerial vehicle is with traditional fuselage and the smooth transition of wing, compares with traditional column fuselage and wing overall arrangement aircraft, has advantages such as integrated shaping, aerodynamic efficiency height, all has good prospect in military and civilian field.
The wing profile is the basis of the design of the airplane wing, and whether the wing profile is successfully designed or not fundamentally determines the success or failure of the airplane design. And China has not systematically studied the high-cruise-performance wing profile of the tailless unmanned aerial vehicle fused with the semi-wing body so far. In order to further improve the combat performance and the application universality of the half-wing-body integrated tailless unmanned aerial vehicle, at present, it is very important to improve the aerodynamic performance of the half-wing-body integrated tailless unmanned aerial vehicle in a cruising state.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a cruise self-balancing half-wing body fusion tailless unmanned aerial vehicle wing type family, which can effectively solve the problems.
The technical scheme adopted by the invention is as follows:
the invention provides a cruising self-balancing half-wing body integrated tailless unmanned aerial vehicle wing type family, which comprises a first wing type, a second wing type and a third wing type;
the spanwise positions of the first airfoil, the second airfoil and the third airfoil on the wing are respectively as follows: the first airfoil is positioned at the root of the wing, the second airfoil is positioned at 28.1 percent of the span direction of the wing, and the third airfoil is positioned at the tip of the wing;
the maximum relative thicknesses of the first, second and third airfoils are 14.00%, 11.00%, 11.90%, respectively; the relative positions of the maximum thicknesses are 30.60%, 30.60% and 33.90%, respectively; the maximum relative thickness is the ratio of the maximum distance between the upper surface and the lower surface of each airfoil to the length of a chord line, and the chord length is the length of the chord line from the leading edge to the trailing edge of each airfoil;
the maximum relative camber of the first airfoil, the second airfoil and the third airfoil is respectively 2.168%, 2.167% and 1.598%, and the relative positions of the maximum camber are respectively 18.00%, 17.90% and 36.80%;
leading edge radii of the first, second and third airfoils are 1.234%, 0.736%, 0.972%, respectively;
the first airfoil, the second airfoil and the third airfoil are blunt trailing edges, and the thickness of the trailing edges is 0.626%, 0.492% and 0.0% respectively;
the twist angles of the first airfoil profile, the second airfoil profile and the third airfoil profile are respectively 1 degree, 1 degree and-7 degrees.
Preferably, the dimensionless geometrical coordinates of the first airfoil are:
Figure BDA0002167699100000021
Figure BDA0002167699100000031
where x/c represents the position of a point on the airfoil curve in the chord direction relative to the leading edge, and y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord.
Preferably, the dimensionless geometrical coordinates of the second airfoil are:
Figure BDA0002167699100000032
Figure BDA0002167699100000041
Figure BDA0002167699100000051
where x/c represents the position of a point on the airfoil curve in the chord direction relative to the leading edge, and y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord.
Preferably, the dimensionless geometrical coordinate of the third airfoil is:
Figure BDA0002167699100000052
Figure BDA0002167699100000061
where x/c represents the position of a point on the airfoil curve in the chord direction relative to the leading edge, and y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord.
The cruising self-balancing half-wing body integrated tailless unmanned aerial vehicle wing type family provided by the invention has the following advantages:
the invention provides an airfoil family with the maximum relative thickness of 11.00-14.00% and emphasis on cruise characteristics. The airfoil family has the capability of cruise self-balancing, the pitching moment is only 0.0003275 when the cruise point fixes the lift coefficient to be 0.35, and the moment inflection point is more than 12 degrees.
The airfoil family provided by the invention is designed aiming at the cruise state of the tailless layout unmanned aerial vehicle, the unmanned aerial vehicle realizes cruise self-balancing under low Mach number and low Reynolds number, and has the characteristics of high lift, low resistance, high lift-drag ratio and moderate stall characteristic.
Drawings
Fig. 1 is a model line drawing of a tailless swept wing layout semi-wing body fusion tailless unmanned aerial vehicle provided by the invention at an angle; in the figure, thick lines are schematic views of spanwise use positions of all the wing profiles of the unmanned aerial vehicle respectively;
fig. 2 is a model line drawing of the tailless swept wing layout semi-fuselage integrated tailless drone at another angle provided by the present invention; in the figure, thick lines are schematic views of spanwise use positions of all the wing profiles of the unmanned aerial vehicle respectively;
FIG. 3 is a model entity diagram of a tailless swept wing layout semi-fuselage integrated tailless unmanned aerial vehicle provided by the invention;
FIG. 4 is a combination diagram of a semi-fuselage blended tailless unmanned aerial vehicle dedicated airfoil family for tailless swept-back wing layout of the present invention;
FIG. 5 is a comparison of the profile of the first airfoil profile and the initial airfoil profile in the semi-fuselage fusion tailless unmanned aerial vehicle specific airfoil profile family of the tailless swept-back wing layout of the present invention;
FIG. 6 is a comparison of profiles of a second airfoil profile and an initial airfoil profile in the semi-fuselage fusion tailless unmanned aerial vehicle dedicated airfoil family of the tailless swept-back wing layout of the present invention;
FIG. 7 is a comparison of the profile of the third airfoil profile and the initial airfoil profile in the semi-fuselage fusion tailless unmanned aerial vehicle specific airfoil profile family of the tailless swept-back wing layout of the present invention;
FIG. 8 is a lift coefficient C of a first airfoil in a half-body fusion tailless unmanned aerial vehicle dedicated airfoil family and a first airfoil in an original configuration airfoil family of the tailless swept-back wing layout of the present inventionLA curve graph varying with angle of attack;
FIG. 9 is a drag coefficient C of the first airfoil profile in the wing profile family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and the first airfoil profile in the original configuration wing profile family of the present inventionDA curve graph varying with angle of attack;
FIG. 10 is a pitching moment coefficient C of the first airfoil in the wing family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and the first airfoil in the wing family with the original configurationmA curve graph varying with angle of attack;
fig. 11 is a graph showing a lift-drag ratio K of a first airfoil in the half-wing body fusion type unmanned aerial vehicle dedicated airfoil family and a first airfoil in the original configuration airfoil family with the tailless swept-back wing layout according to the change of an attack angle;
FIG. 12 is a lift coefficient C of the second airfoil profile in the wing profile family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and the second airfoil profile in the wing profile family with the original configurationLA curve graph varying with angle of attack;
FIG. 13 is a drag coefficient C of the second airfoil profile in the wing profile family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and the second airfoil profile in the wing profile family with the original configurationDA curve graph varying with angle of attack;
FIG. 14 is a pitch moment coefficient C of the second airfoil profile in the wing profile family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and the second airfoil profile in the wing profile family with the original configurationmA curve graph varying with angle of attack;
fig. 15 is a graph showing the variation of lift-drag ratio K with the angle of attack of the second airfoil in the semi-airfoil fusion type unmanned aerial vehicle special airfoil family of the tailless swept-back wing layout of the present invention and the second airfoil in the original configuration airfoil family;
FIG. 16 is a lift coefficient C of a third airfoil in the wing family special for the half-wing body fusion type unmanned aerial vehicle with the tailless swept-back wing layout and a third airfoil in the wing family with the original configurationLA curve graph varying with angle of attack;
FIG. 17 is a drag coefficient C of the third airfoil profile in the half-wing body fusion type unmanned aerial vehicle special airfoil profile family and the third airfoil profile in the original configuration airfoil profile family with tailless swept-back wing layout of the present inventionDA curve graph varying with angle of attack;
FIG. 18 is a pitching moment coefficient C of the third airfoil in the semi-wing body fusion type unmanned aerial vehicle special airfoil family and the third airfoil in the original configuration airfoil family with tailless swept-back wing layout of the inventionmA curve graph varying with angle of attack;
fig. 19 is a graph showing a lift-drag ratio K of a third airfoil in the half-wing body fusion type unmanned aerial vehicle dedicated airfoil family and a third airfoil in the original configuration airfoil family with the tailless swept-back wing layout according to the change of an attack angle;
FIG. 20 is a graph of lift coefficient C for a full-airfoil configuration and an initial full-airfoil configuration formed from a family of airfoils of the present inventionLA comparison plot of variation with angle of attack;
FIG. 21 is a drag coefficient C for a full-airfoil configuration and an initial full-airfoil configuration formed from a family of airfoils of the present inventionDA comparison plot of variation with angle of attack;
FIG. 22 is a pitch moment coefficient C for a full-profile and an initial full-profile formed from a family of airfoils of the present inventionmA comparison plot of variation with angle of attack;
FIG. 23 is a comparison of lift-to-drag ratio K versus angle of attack curves for a full-profile configuration constructed from a family of airfoils of the present invention and an initial full-profile configuration;
FIG. 24 is a comparison of full-profile, initial full-profile, and elliptical ring mass distributions for a full-profile, initial full-profile, airfoil family of the present invention, with the abscissa of the graph showing relative position along the span of the airfoil and the ordinate of the true ring mass.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The half-wing body integrated tailless unmanned aerial vehicle adopts tailless sweepback wing layout, so that the resistance can be reduced, the lift-drag ratio is improved, and the pneumatic performance is improved. Meanwhile, the half-wing body integrated unmanned aerial vehicle with the layout of the tailless swept-back wing faces the challenge in the design process: the aircraft needs to maintain good stability and maneuverability during flight, while tailless layout does not provide trim capability due to the lack of a horizontal tail, resulting in the inability of the aircraft to cruise self-trim during flight. The invention mainly aims at improving the self-balancing aspect of the cruising state of the aircraft. The invention provides a half-wing body integrated tailless unmanned aerial vehicle wing type family capable of cruising and self-balancing, which emphasizes the cruising characteristic and has higher lift coefficient and lift-drag ratio performance at the cruising point on the premise of meeting the cruising and self-balancing.
Specifically, by using an advanced airfoil design technology, the invention enables an airfoil family to have a higher lift-drag ratio under a lower design lift coefficient, a lower flight Mach number and a lower flight Reynolds number on the premise of meeting the cruise self-trim, thereby improving the cruise efficiency, and developing the airfoil family design aiming at the cruise state, wherein the index requirements are as follows:
1. pitching moment C in cruising statem≈0±0.015；
2. The working state of the half-wing body fusion type unmanned aerial vehicle with the layout of the tailless sweepback wing is as follows:
the cruising state is as follows: ma ═ 0.1, Re ═ 2.33E6, CL＝0.35；
According to the design indexes, the invention adopts a computer fluid mechanics method, designs a heavy cruise point in a state, and provides a wing type group which is suitable for a half-wing body fusion type unmanned aerial vehicle with tailless sweepback wing layout, emphasizes on cruise characteristics, can cruise self-trim, has high lift force, low resistance and high lift-drag ratio.
The geometrical parameters of each airfoil in the airfoil family and the initial airfoil family of the present invention are shown in tables 1 and 2:
table 1: improving the geometrical parameters of each airfoil in a family of airfoils
Figure BDA0002167699100000091
The torsion angles of the first airfoil profile, the second airfoil profile and the third airfoil profile provided by the invention are respectively 1 degree, 1 degree and-7 degrees.
Table 2: geometric parameters of each airfoil in the initial family of airfoils
Figure BDA0002167699100000092
In the specification of the invention and the attached drawings, the improved wing profiles are a first wing profile, a second wing profile and a third wing profile designed by the invention. Whereas the original airfoil is a prior art airfoil.
The dimensionless data of the profiles of the first airfoil profile, the second airfoil profile and the third airfoil profile provided by the invention are shown in the following table:
the dimensionless geometrical coordinates of the first airfoil profile of the invention are:
Figure BDA0002167699100000101
Figure BDA0002167699100000111
the dimensionless geometrical coordinates of the second airfoil of the invention are:
Figure BDA0002167699100000112
Figure BDA0002167699100000121
the dimensionless geometrical coordinate of the third airfoil of the invention is as follows:
Figure BDA0002167699100000122
Figure BDA0002167699100000131
Figure BDA0002167699100000141
wherein the x/c value represents the position of a point on the airfoil curve in the chord direction relative to the leading edge; the y/c value represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord. The dimensionless coordinate order in the table starts from the trailing edge (x/c 1) of the airfoil, proceeds along the pressure surface to the leading edge (x/c 0), and returns from the leading edge along the suction surface to the trailing edge (x/c 1).
Referring to fig. 1 to fig. 3, schematic views of wing span positions of half-wing fusion type unmanned aerial vehicle with each wing profile in a tailless swept wing layout are shown, and the span positions of the first wing profile, the second wing profile, and the third wing profile on the wing are respectively: the first airfoil is located at the root of the wing, the second airfoil is located at 28.1% of the span direction of the wing, and the third airfoil is located at the tip of the wing. Fig. 3 shows a semi-wing body fusion type unmanned aerial vehicle model entity diagram of a tailless swept-back wing layout, which is easier to see that the wings and the fuselage are semi-fused.
Referring to fig. 4, fig. 4 shows a combination diagram of each airfoil in the airfoil family of the present invention, and the present invention obtains profile comparison diagrams of the airfoils at different spanwise positions and the initial airfoil, as shown in fig. 5 to 7.
Fig. 8-11 show aerodynamic comparison curves for the first airfoil of the present invention with the initial airfoil. 12-15, aerodynamic profile comparison curves for the second airfoil of the present invention with the initial airfoil are shown. FIGS. 16-19 illustrate aerodynamic property pairs of a third airfoil of the present invention with an initial airfoilAnd (4) a ratio curve. For each set of aerodynamic characteristic comparison curves, the method sequentially comprises the following steps: coefficient of lift CLA curve varying with angle of attack; coefficient of resistance CDA curve varying with angle of attack; coefficient of pitching moment CmA curve varying with angle of attack; the lift-drag ratio K varies with the angle of attack.
FIGS. 20-23 are aerodynamic characteristic comparison plots of a full profile formed by a family of airfoils of the present invention versus an initial full profile (in order: lift coefficient C)LA curve varying with angle of attack; coefficient of resistance CDA curve varying with angle of attack; coefficient of pitching moment CmA curve varying with angle of attack; lift-drag ratio K versus angle of attack). As can be seen from the figure: compared with the initial full-mechanical configuration, the full-mechanical configuration has the advantages that the resistance coefficient is reduced after the attack angle is 0 degree; at cruise point CLAt 0.35, the drag coefficient does not change much, but the pitch moment coefficient is changed from-0.02654 to 0.0003275, so that the unmanned aerial vehicle can achieve cruise self-balancing and reduce balancing resistance.
FIG. 24 shows the initial full-aircraft configuration and the full-aircraft configuration consisting of the airfoil family of the invention in cruise conditions, i.e. at constant lift CLAs can be seen from fig. 24, the full-span configuration formed by the airfoil family of the present invention results in a ring volume distribution that is closer to the elliptical ring volume distribution, where the ring volume distribution within 0.6 of the relative position along the span of the airfoil substantially coincides with the elliptical ring volume distribution, thus greatly reducing induced drag.
Therefore, the half-wing body integrated tailless unmanned aerial vehicle wing type family capable of cruising and self-balancing provided by the invention is designed aiming at the cruising state of a tailless layout unmanned aerial vehicle, the unmanned aerial vehicle realizes cruising and self-balancing under the conditions of low Mach number and low Reynolds number, and has the characteristics of high lift force, low resistance, high lift-drag ratio and moderate stalling characteristic.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements should also be considered within the scope of the present invention.

Claims (1)

1. A cruising self-balancing half-wing body fusion tailless unmanned aerial vehicle wing type family is characterized by comprising a first wing type, a second wing type and a third wing type;
the spanwise positions of the first airfoil, the second airfoil and the third airfoil on the wing are respectively as follows: the first airfoil is positioned at the root of the wing, the second airfoil is positioned at 28.1 percent of the span direction of the wing, and the third airfoil is positioned at the tip of the wing;
the maximum relative thicknesses of the first, second and third airfoils are 14.00%, 11.00%, 11.90%, respectively; the relative positions of the maximum thicknesses are 30.60%, 30.60% and 33.90%, respectively; the maximum relative thickness is the ratio of the maximum distance between the upper surface and the lower surface of each airfoil to the length of a chord line, and the chord length is the length of the chord line from the leading edge to the trailing edge of each airfoil;
the maximum relative camber of the first airfoil, the second airfoil and the third airfoil is respectively 2.168%, 2.167% and 1.598%, and the relative positions of the maximum camber are respectively 18.00%, 17.90% and 36.80%;
leading edge radii of the first, second and third airfoils are 1.234%, 0.736%, 0.972%, respectively;
the first airfoil, the second airfoil and the third airfoil are blunt trailing edges, and the thickness of the trailing edges is 0.626%, 0.492% and 0.0% respectively;
the torsion angles of the first airfoil profile, the second airfoil profile and the third airfoil profile are respectively 1 degree, 1 degree and-7 degrees;
wherein the dimensionless geometric coordinates of the first airfoil are:
Figure FDA0002955843550000011
Figure FDA0002955843550000021
wherein x/c represents the position of a point on the airfoil curve relative to the leading edge in the chord direction, y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord;
wherein the dimensionless geometric coordinates of the second airfoil are:
Figure FDA0002955843550000022
Figure FDA0002955843550000031
wherein x/c represents the position of a point on the airfoil curve relative to the leading edge in the chord direction, y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord;
wherein the dimensionless geometric coordinates of the third airfoil are:
Figure FDA0002955843550000032
Figure FDA0002955843550000041
where x/c represents the position of a point on the airfoil curve in the chord direction relative to the leading edge, and y/c represents the height from the chord to a point on the airfoil curve, positive above the chord and negative below the chord.
CN201910752594.4A 2019-08-15 2019-08-15 Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family Active CN110435873B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910752594.4A CN110435873B (en) 2019-08-15 2019-08-15 Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910752594.4A CN110435873B (en) 2019-08-15 2019-08-15 Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family

Publications (2)

Publication Number Publication Date
CN110435873A CN110435873A (en) 2019-11-12
CN110435873B true CN110435873B (en) 2021-04-23

Family

ID=68435586

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910752594.4A Active CN110435873B (en) 2019-08-15 2019-08-15 Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family

Country Status (1)

Country Link
CN (1) CN110435873B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111348175A (en) * 2020-01-13 2020-06-30 北京航空航天大学 Special airfoil profile matched with high-universality large-loading small-sized unmanned aerial vehicle
CN111498085A (en) * 2020-04-15 2020-08-07 成都飞机工业（集团）有限责任公司 High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout
CN112478127A (en) * 2020-12-04 2021-03-12 中国航空工业集团公司沈阳飞机设计研究所 Flying wing unmanned aerial vehicle with geometry twists reverse structure
CN112849387B (en) * 2021-01-22 2022-11-08 西北工业大学 Flying wing reverse-bending wing section considering power installation platform
CN114572340B (en) * 2022-04-18 2023-02-03 西北工业大学 Family of underwater high-lift low-cavitation airfoil

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101230836A (en) * 2007-01-09 2008-07-30 通用电气公司 Wind turbine airfoil family
CN203374428U (en) * 2013-06-14 2014-01-01 中国科学院工程热物理研究所 Family of wind-power airfoil profiles with large thickness and blunt trailing edges
CN103482054A (en) * 2013-08-14 2014-01-01 西北工业大学 Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle
CN203594560U (en) * 2013-09-13 2014-05-14 宜春学院 Wind turbine blade anti-fouling high-performance airfoil family
CN104819106A (en) * 2015-04-30 2015-08-05 南京北大工道创新有限公司 Wind turbine blade wing section group
CN105129071A (en) * 2015-06-26 2015-12-09 北京昶远科技有限公司 Solar-powered airplane airfoil profile design method and solar-powered airplane airfoil profile
CN106864726A (en) * 2016-12-27 2017-06-20 西北工业大学 A kind of laminar flow airfoil that cruising characteristics are laid particular stress on suitable for general purpose vehicle
CN108583847A (en) * 2018-04-26 2018-09-28 陈俊胤 A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6607164B2 (en) * 2001-10-22 2003-08-19 Toyota Motor Sales, U.S.A., Inc. Wing airfoil

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101230836A (en) * 2007-01-09 2008-07-30 通用电气公司 Wind turbine airfoil family
CN203374428U (en) * 2013-06-14 2014-01-01 中国科学院工程热物理研究所 Family of wind-power airfoil profiles with large thickness and blunt trailing edges
CN103482054A (en) * 2013-08-14 2014-01-01 西北工业大学 Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle
CN203594560U (en) * 2013-09-13 2014-05-14 宜春学院 Wind turbine blade anti-fouling high-performance airfoil family
CN104819106A (en) * 2015-04-30 2015-08-05 南京北大工道创新有限公司 Wind turbine blade wing section group
CN105129071A (en) * 2015-06-26 2015-12-09 北京昶远科技有限公司 Solar-powered airplane airfoil profile design method and solar-powered airplane airfoil profile
CN106864726A (en) * 2016-12-27 2017-06-20 西北工业大学 A kind of laminar flow airfoil that cruising characteristics are laid particular stress on suitable for general purpose vehicle
CN108583847A (en) * 2018-04-26 2018-09-28 陈俊胤 A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft

Also Published As

Publication number Publication date
CN110435873A (en) 2019-11-12

Similar Documents

Publication Publication Date Title
CN110435873B (en) Cruise self-balancing semi-wing body fusion tailless unmanned aerial vehicle wing type family
CN103552682B (en) A kind of all-wing aircraft and buzzard-type wing connection wing airplane
CN110498037B (en) High lift-drag ratio laminar flow wing section suitable for low-altitude low-speed unmanned aerial vehicle
CN107757871B (en) Airfoil profile for light and small fixed wing unmanned aerial vehicle
CN104118556B (en) Special spoon-shaped wing section with ultra-low Reynolds number, high lift-drag ratio and low speed
CN108974326B (en) Bionic wave front edge wingtip winglet device
CN103482054B (en) Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle
CN110979682A (en) Variable-area duck-type forward-swept wing variant aircraft
CN109229364B (en) Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region
CN102826216A (en) Aerodynamic configuration of aircraft
CN115571323A (en) Flat fusion body overall arrangement aircraft of subsonic speed
CN203740120U (en) Aerodynamic structure of morphing aircraft with wide flight envelope
CN114684348A (en) High-resistance divergent Mach number laminar flow airfoil suitable for light and medium-sized high-speed business machine
CN110386243B (en) High lift-drag ratio low-speed unmanned wing type
CN202953169U (en) Novel spoon-shaped blended winglet for civil airplane
CN106828872A (en) The HAE tandem rotor aircraft aerodynamic arrangement of empennage is supported using rear wing high
CN115924059A (en) Single sweepback flying wing horizontal tail fusion pneumatic layout aircraft
CN214660605U (en) High-lift wind turbine wing section
CN210681131U (en) Wing structure
CN205366050U (en) Fixed -wing unmanned aerial vehicle
CN207482179U (en) A kind of small-sized fixed-wing unmanned plane aerofoil profile
CN204937472U (en) A kind of aerofoil profile being directed to dopey
CN210416955U (en) Low-speed unmanned aerial vehicle wing section with high lift-drag ratio
CN211001782U (en) Aircraft aerodynamic layout capable of flying in high altitude and ground effect area
CN105775108A (en) Upper air propeller in externally-loaded layout

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant