CN108583847A - A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft - Google Patents

A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft Download PDF

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CN108583847A
CN108583847A CN201810382463.7A CN201810382463A CN108583847A CN 108583847 A CN108583847 A CN 108583847A CN 201810382463 A CN201810382463 A CN 201810382463A CN 108583847 A CN108583847 A CN 108583847A
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aerofoil profile
reynolds number
power factor
airfoil
chord length
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CN108583847B (en
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陈俊胤
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings

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Abstract

The present invention provides a kind of suitable for long endurance unmanned aircraft low reynolds number high power factor aerofoil profile, disclose maximum camber and its position of the aerofoil profile, maximum gauge and its position, the equation and aerofoil profile coordinate that upper and lower surface meets respectively, f is maximum camber, Xf is the abscissa value at aerofoil profile maximum camber, t is maximum gauge, and Xt is the abscissa value at aerofoil profile maximum gauge, and C is chord length.The origin of coordinate system is airfoil mean line leading edge point where defining aerofoil profile, and X-axis is overlapped with string, and airfoil trailing edge is directed toward in direction by aerofoil profile leading edge, and Y-axis is directed toward the direction of airfoil mean line bending perpendicular to X-axis.By carrying out rational modification to the upper and lower surface gradient distribution of aerofoil profile, delay turning point Forward bubble separation, it may be implemented under the operating Reynolds number of setting, the aerofoil profile has more preferably performance, i.e. larger range of lift resistance ratio, higher power factor coordinates Aircraft Conceptual Design, improves the cruise duration of unmanned plane.

Description

A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft
Technical field
The invention belongs to Unmanned Aerial Vehicle Airfoil design fields, and in particular to a kind of low reynolds number high power factor aerofoil profile.
Background technology
Long endurance unmanned aircraft, such as small-sized solar unmanned plane and Altitude Long Endurance Unmanned Air Vehicle, flying speed is small, flight thunder Promise number is low, and cruise Reynolds number is about in 20-40 ten thousand or so, and mostly referred to as low reynolds number (claims in the industry 100,000-100 ten thousand Reynolds number For low reynolds number), under the reynolds number range, relate generally to low reynolds number, the Laminar Flow of low speed, laminar flow bubble, laminar flow point From and turn twist etc. flowing physical phenomenons, with powered by conventional energy middle and high Reynolds number flying condition under of the laminar flow to turbulent flow have very It is different.Thus determine that such long endurance unmanned aircraft Aerodynamic Design method has obviously with thinking with middle and high Reynolds number aircraft Difference.And solar energy unmanned plane also needs to consider the compound of photovoltaic module, therefore airfoil profile also suffers restraints.
Although there is part to can be used for low Reynolds number airfoil under low reynolds number state of flight in existing aerofoil profile library, for example originally set The SD7032 of aerofoil profile as a comparison in meter, under the Reynolds number of 200,000 magnitudes, top airfoil turning point with the increase of the angle of attack and Rapid forward edge movement, detaches, causing property loss of energy so as to cause air-flow.
Invention content
In view of the deficiencies of the prior art, performance bad situation when being matched with practical work for existing low Reynolds number airfoil, The present invention provides a kind of low reynolds number high power factor aerofoil profile, can be well matched with the low flight Reynolds number of long endurance unmanned aircraft Actual condition, meanwhile, upper surface bending degree is small, is suitable for the matching of the photovoltaic module of solar energy unmanned plane.
In order to realize that the above technical purpose, the present invention use following technical scheme：
Specific flying condition is analyzed, such as assumes that flight Reynolds number is 200,000.So under this condition, it first tentatively picks out often The low Reynolds number airfoil seen, under specified operating mode, with the aerodynamic analysis technology of aircraft industry, analysis different airfoil profiles are being set Performance under operating mode.
Since the main performance of aerofoil profile is heavily dependent on its shape upper and lower surfaces of, by further grinding Study carefully performance capabilities preferably several groups of aerofoil profiles in back, by pointedly changing leading-edge radius, upper and lower surface gradient is distributed, most The parameters such as heavy camber position then find out the best aerofoil profile of performance capabilities, as designing airfoil, and pass through experimental verification and making Practical unmanned plane Flight.
Above-mentioned aerodynamic analysis is primarily referred to as calculating under setting operating mode, using the lift resistance ratio of the aircraft complete machine of specific aerofoil profile, The common performance parameter such as power factor.
According to above-mentioned design principle, the present invention specifically provides low reynolds number high power factor aerofoil profile, and is named For DMXfoil-1, for being described as follows for aerofoil profile：
The ratio between the maximum camber f and chord length C of aerofoil profile f/C=3.88%,
The maximum camber position Xf/C=48.09 of aerofoil profile,
The ratio between the maximum gauge t and chord length C of aerofoil profile t/C=10.50%,
The maximum gauge position of aerofoil profile is Xt/C=28.99%；
When definition chord length is 1, the equation of aerofoil profile upper surface is：
Y=-2.687263401080x6+9.080382811085x5-12.119920168585x4+8.215218339892x3- 3.252320013999x2+0.754048283792x+0.008814393076
When definition chord length is 1, the equation of aerofoil profile lower surface is：
Y=3.108344757931x6-10.324958446486x5+13.345995816048x4-8.586501844602x3+ 2.878571621603x2-0.414971953131x-0.005291297688
Wherein, Xf is the abscissa value at aerofoil profile maximum camber, and Xt is the abscissa value at aerofoil profile maximum gauge.Define aerofoil profile institute It is airfoil mean line leading edge point in the origin of coordinate system, X-axis is overlapped with string, and airfoil trailing edge, Y-axis are directed toward in direction by aerofoil profile leading edge The direction of airfoil mean line bending is directed toward perpendicular to X-axis.
When the chord length of the aerofoil profile is 1, then the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows：
Upper table areal coordinate：
Following table areal coordinate：
Description of the drawings
Fig. 1 is the composition figure of designing airfoil, and in figure, 1 is aerofoil profile leading edge, and 2 be aerofoil profile upper surface, and 3 be aerofoil profile lower surface, 4 It is airfoil trailing edge for aerofoil profile string, 5, f is aerofoil profile maximum camber, and Xf is the abscissa value at aerofoil profile maximum camber, and C is chord length, t For aerofoil profile maximum gauge, Xt is the abscissa value at aerofoil profile maximum gauge.
Fig. 2 is the geometry external form comparison diagram of designing airfoil DMXfoil-1 and comparison aerofoil profile SD7032.
Fig. 3 be designing airfoil DMXfoil-1 under design point pressure distribution curve figure (Re=20 ten thousand, angle of attack= 5.6 °, low speed).
Fig. 4 be compare aerofoil profile SD7032 under design point pressure distribution curve figure (Re=20 ten thousand, angle of attack=5.6 °, Low speed).
Fig. 5 is the lift resistance ratio characteristic curve comparison diagram (Re=20 of designing airfoil DMXfoil-1 and comparison aerofoil profile SD7032 Ten thousand, low speed), in figure, 6 be the aerodynamic characteristic curve graph under design point of designing airfoil DMXfoil-1, and 7 be comparison aerofoil profile The aerodynamic characteristic curve graph under design point of SD7032.
Fig. 6 is that designing airfoil DMXfoil-1 and comparison aerofoil profile SD7032 is respectively adopted with comparison aerofoil profile in design point Under power factor Character Comparison figure, in figure, 6 be the aerodynamic characteristic curve under design point of designing airfoil DMXfoil-1 Figure, 7 be the aerodynamic characteristic curve graph under design point for comparing aerofoil profile SD7032.(Re=20 ten thousand, low speed)
Specific implementation mode
Below in conjunction with attached drawing, the present invention is described in detail：
A kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft of the present invention, design principle are： Specific flying condition is analyzed, such as in the present embodiment, at the beginning of analysis, that is, assumes that flight Reynolds number is 20W.In the condition Under, common low Reynolds number airfoil is tentatively first picked out, under specified operating mode, with the aerodynamic analysis technology of aircraft industry, Analyze performance of the different airfoil profiles in the case where setting operating mode.
Since the main performance of aerofoil profile is heavily dependent on its shape upper and lower surfaces of, by further grinding Study carefully performance capabilities preferably several groups of aerofoil profiles in back, by pointedly changing leading-edge radius, upper and lower surface gradient is distributed, most The parameters such as heavy camber position then find out the best aerofoil profile of performance capabilities, as designing airfoil.
Above-mentioned aerodynamic analysis is primarily referred to as calculating under setting operating mode, using the lift resistance ratio of the aircraft complete machine of specific aerofoil profile, The common performance parameter such as power factor.
In the following, being given by the rule characteristic for the low reynolds number high power factor aerofoil profile that the optimization method obtains, give The designing airfoil regularity of distribution upper and lower surfaces of, the equation and shape of satisfaction, can refer to Fig. 1.
According to above-mentioned design principle, the present invention specifically provides low reynolds number high power factor aerofoil profile, and is named For DMXfoil-1, for being described as follows for aerofoil profile：
The ratio between maximum camber f and chord length C of aerofoil profile
F/C=3.88%,
The maximum camber position of aerofoil profile
Xf/C=48.09,
The ratio between maximum gauge t and chord length C of aerofoil profile
T/C=10.50%
The maximum gauge position of aerofoil profile is
Xt/C=28.99%；
When definition chord length is 1, the equation of aerofoil profile upper surface is：
Y=-2.687263401080x6+9.080382811085x5-12.119920168585x4+8.215218339892x3- 3.252320013999x2+0.754048283792x+0.008814393076
When definition chord length is 1, the equation of aerofoil profile lower surface is：
Y=3.108344757931x6-10.324958446486x5+13.345995816048x4-8.586501844602x3+ 2.878571621603x2-0.414971953131x-0.005291297688
Wherein, Xf is the abscissa value at aerofoil profile maximum camber, and Xt is the abscissa value at aerofoil profile maximum gauge.Define aerofoil profile institute It is airfoil mean line leading edge point in the origin of coordinate system, X-axis is overlapped with string, and airfoil trailing edge, Y-axis are directed toward in direction by aerofoil profile leading edge The direction of airfoil mean line bending is directed toward perpendicular to X-axis.
When the chord length of the aerofoil profile is 1, then the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows：
Upper table areal coordinate：
Following table areal coordinate：
It is special to have carried out a series of Pneumatic Calculations and reality with comparison aerofoil profile SD7032 in order to illustrate the progressive of the design aerofoil profile Verification, it is as follows to obtain result：
Reynolds number is set as 200,000, when the aerofoil profile angle of attack is 5.6 °, the lift resistance ratio of designing airfoil DMXfoil-1 reaches maximum, meter It is 83.8 to calculate result, and about at 52% chord length, and under same Reynolds number, the lift resistance ratio of SD7032 is only top airfoil turning point 62.3, this is because for SD7032 aerofoil profiles, under this angle of attack, turning point is very close to leading edge locus, since energy subtracts It is few, it is not enough to be attached to upper surface, airflow diversion has occurred, resistance is made to increase severely, die-off so as to cause lift resistance ratio.
Under above-mentioned condition, the pressure distribution curve figure of DMXfoil-1 and SD7032 are attached to Fig. 3 and Fig. 4 respectively.
And in the angle-of-attack range of bigger (Fig. 5), it is not difficult to find out, the angle of attack is designing airfoil within the scope of -5 ° -3 ° The lift resistance ratio characteristic of DMXfoil-1 and comparison aerofoil profile SD7032 are close, and when the angle of attack is within the scope of 3 ° -20 °, designing airfoil The lift resistance ratio of DMXfoil-1 is better than comparison aerofoil profile SD7032.
Further, (major parameter is wing chord length 400mm, the span for our designs to same solar energy unmanned plane 5.4m, RECTANGULAR WINGS add wingtip), designing airfoil DMXfoil-1 and comparison aerofoil profile SD7032 is respectively adopted, compares setting flight reappearance Under the conditions of power factor, the results are shown in Figure 6, also can be seen that, except when the wing angle of attack be 1 ° when power factor having the same Outside, under remaining angle of attack, the power factor of designing airfoil DMXfoil-1 is above comparison aerofoil profile SD7032.Pay special attention to cruise shape State, that is, range of angles of attack, between 4 ° -6 °, the difference of power factor is more apparent, the cruising power breath of this value and aircraft Manner of breathing closes, and directly affects the cruise duration of aircraft.In the case where flight reappearance is certain, high power factor advantageously reduces Cruising power, and then improve cruise duration.For long endurance unmanned aircraft, there is obvious significance.

Claims (2)

1. a kind of low reynolds number low-power factor aerofoil profile, this aerofoil profile are named as DMXfoil-1, it is characterised in that：Aerofoil profile is most The ratio between heavy camber f and chord length C f/C=3.88%, maximum camber position Xf/C=48.09%, the maximum gauge t and chord length C of aerofoil profile The ratio between t/C=10.50%, maximum gauge position be Xt/C=28.99%；
When definition chord length is 1, the equation of aerofoil profile upper surface is：
y = -2.687263401080 x6 + 9.080382811085 x5 - 12.119920168585 x4 + 8.215218339892 x3 - 3.252320013999 x2 + 0.754048283792 x + 0.008814393076
When definition chord length is 1, the equation of aerofoil profile lower surface is：
y = 3.108344757931 x6 - 10.324958446486 x5 + 13.345995816048 x4 - 8.586501844602 x3 + 2.878571621603 x2 - 0.414971953131 x - 0.005291297688
Wherein, Xf is the abscissa value at aerofoil profile maximum camber, and Xt is the abscissa value at aerofoil profile maximum gauge,
The origin of coordinate system is airfoil mean line leading edge point where defining aerofoil profile, and X-axis is overlapped with string, and direction is referred to by aerofoil profile leading edge To airfoil trailing edge, Y-axis is directed toward the direction of airfoil mean line bending perpendicular to X-axis.
2. a kind of low reynolds number high power factor aerofoil profile suitable for long endurance unmanned aircraft according to claim 1, special Sign is：When the chord length of the aerofoil profile is 1, then the coordinate corresponding to the upper and lower surface of aerofoil profile is as follows：
Upper table areal coordinate：
X Y 1.00000 0.00000 0.99639 0.00083 0.99025 0.00230 0.98324 0.00402 0.97547 0.00593 0.96715 0.00796 0.95845 0.01003 0.94948 0.01212 0.94041 0.0142 0.93123 0.01628 0.92197 0.01835 0.91267 0.02043 0.90337 0.02250 0.8941 0.02454 0.88483 0.02657 0.87559 0.02858 0.86635 0.03057 0.85713 0.03254 0.84797 0.03447 0.83882 0.03637 0.82973 0.03823 0.82064 0.04006 0.8116 0.04185 0.80258 0.0436 0.79356 0.04531 0.78453 0.04699 0.77551 0.04863 0.76646 0.05023 0.75736 0.05181 0.74826 0.05335 0.73912 0.05486 0.72996 0.05636 0.72078 0.05782 0.71159 0.05925 0.70237 0.06066 0.69313 0.06205 0.68389 0.0634 0.67463 0.06473 0.66539 0.06603 0.65617 0.0673 0.64693 0.06854 0.6377 0.06974 0.62845 0.07092 0.61924 0.07206 0.61002 0.07317 0.6008 0.07424 0.59159 0.07528 0.58237 0.07628 0.57318 0.07725 0.56398 0.07817 0.55479 0.07906 0.54561 0.07991 0.53641 0.08072 0.52723 0.08149 0.51806 0.08222 0.50889 0.08291 0.49974 0.08355 0.49056 0.08415 0.48138 0.08471 0.47219 0.08523 0.46299 0.08571 0.45376 0.08614 0.44454 0.08655 0.43529 0.08691 0.42606 0.08723 0.41678 0.0875 0.4075 0.08775 0.39827 0.08795 0.38902 0.08811 0.37982 0.08823 0.37064 0.08831 0.36154 0.08833 0.35248 0.0883 0.34343 0.08822 0.33445 0.08808 0.3255 0.08788 0.31658 0.08762 0.30772 0.0873 0.29888 0.08691 0.29003 0.08645 0.28119 0.08592 0.27235 0.08532 0.2635 0.08465 0.25464 0.08391 0.24575 0.08309 0.23684 0.08222 0.22796 0.08127 0.21905 0.08024 0.21014 0.07915 0.20125 0.07799 0.19241 0.07676 0.18363 0.07547 0.17494 0.0741 0.16633 0.07267 0.15778 0.07114 0.14931 0.06953 0.14087 0.06781 0.13247 0.066 0.12411 0.06408 0.11577 0.06206 0.10749 0.05993 0.0993 0.05772 0.09129 0.05542 0.08348 0.05304 0.07588 0.05056 0.06848 0.04799 0.0613 0.04531 0.05438 0.04255 0.04781 0.03976 0.04167 0.03697 0.03609 0.03427 0.03111 0.0317 0.02675 0.02929 0.02296 0.02708 0.01969 0.02502 0.01686 0.02311 0.01438 0.0213 0.01223 0.0196 0.01034 0.01798 0.00868 0.01644 0.00721 0.01498 0.00593 0.01359 0.0048 0.01225 0.0038 0.01096 0.00293 0.0097 0.00216 0.00846 0.0015 0.00727 0.00094 0.00609 0.00049 0.00496 0.00015 0.00385 0.00278 0.00000 0.00176 0.00000 0.00075 0.00000
Following table areal coordinate：
X Y 0.00005 -0.00027 0.00038 -0.00130 0.00085 -0.00233 0.00147 -0.00336 0.00223 -0.00438 0.00312 -0.00539 0.00411 -0.00637 0.00522 -0.00734 0.00645 -0.00828 0.00781 -0.00921 0.00931 -0.01012 0.01095 -0.01102 0.01276 -0.01192 0.01476 -0.01282 0.01696 -0.01373 0.01942 -0.01462 0.02217 -0.01551 0.02528 -0.01640 0.02882 -0.01730 0.03284 -0.01820 0.0374 -0.01910 0.04255 -0.01999 0.04828 -0.02085 0.05456 -0.02166 0.06126 -0.02239 0.06832 -0.02301 0.07569 -0.02349 0.08341 -0.02382 0.09156 -0.02405 0.10014 -0.02419 0.1091 -0.0243 0.11828 -0.02438 0.12755 -0.02442 0.13689 -0.02442 0.14624 -0.02437 0.15555 -0.02426 0.16485 -0.02410 0.17418 -0.02389 0.18354 -0.02363 0.19293 -0.02332 0.20235 -0.02297 0.21181 -0.0226 0.2213 -0.02218 0.23084 -0.02174 0.24039 -0.02127 0.24999 -0.02078 0.25958 -0.02026 0.26918 -0.01973 0.27875 -0.01919 0.28831 -0.01864 0.29787 -0.01809 0.30742 -0.01753 0.31697 -0.01697 0.32652 -0.0164 0.33607 -0.01584 0.34564 -0.01527 0.35519 -0.01470 0.36474 -0.01413 0.37431 -0.01356 0.38386 -0.01299 0.39342 -0.01242 0.40299 -0.01184 0.41254 -0.01126 0.42208 -0.01069 0.43157 -0.01011 0.44109 -0.00955 0.45059 -0.00897 0.4601 -0.00841 0.46962 -0.00784 0.47909 -0.00728 0.48859 -0.00673 0.49809 -0.00617 0.50756 -0.00562 0.51702 -0.00508 0.52649 -0.00454 0.53595 -0.00399 0.54537 -0.00345 0.5548 -0.00291 0.56425 -0.00238 0.57366 -0.00184 0.58306 -0.00131 0.59245 -0.00079 0.60183 -0.00027 0.6112 0.00024 0.62055 0.00075 0.62989 0.00123 0.6392 0.00171 0.64849 0.00216 0.65779 0.00259 0.66706 0.003 0.6763 0.00339 0.68555 0.00375 0.69478 0.00407 0.70401 0.00438 0.71325 0.00464 0.72255 0.00489 0.73184 0.00511 0.74118 0.00530 0.75056 0.00546 0.76001 0.00561 0.76947 0.00574 0.77896 0.00585 0.78849 0.00595 0.79805 0.00603 0.80759 0.00609 0.81711 0.00614 0.82661 0.00617 0.83606 0.00618 0.84546 0.00616 0.85486 0.00611 0.8642 0.00603 0.87349 0.00591 0.88277 0.00576 0.892 0.00556 0.90121 0.00532 0.91048 0.00502 0.91976 0.00468 0.92908 0.00429 0.93845 0.00386 0.94779 0.00341 0.95701 0.00292 0.96601 0.00242 0.97464 0.00190 0.98268 0.00137 0.98994 0.00085 0.99629 0.00033 1 0
。
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CN109969381A (en) * 2019-04-12 2019-07-05 中国空气动力研究与发展中心计算空气动力研究所 A kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber
CN110386243A (en) * 2019-07-22 2019-10-29 北京耐威科技股份有限公司 A kind of low-speed unmanned aerial vehicle aerofoil profile of high lift-drag ratio
CN110435873A (en) * 2019-08-15 2019-11-12 西北工业大学 A kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race cruised from trim
CN111498084A (en) * 2020-04-15 2020-08-07 成都飞机工业（集团）有限责任公司 Low-resistance laminar flow airfoil applied to high-altitude high-speed long-endurance unmanned aerial vehicle
CN112977815A (en) * 2021-05-10 2021-06-18 北京三快在线科技有限公司 Rotor craft, blade of rotor craft and wing section of blade
CN114194373A (en) * 2021-12-03 2022-03-18 中电科芜湖通用航空产业技术研究院有限公司 Aircraft wing and aircraft
CN114718903A (en) * 2022-04-19 2022-07-08 成都航空职业技术学院 High-performance wing section for heat dissipation axial flow fan

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