CN202609085U - Aircraft aerodynamic configuration with blended wing body - Google Patents
Aircraft aerodynamic configuration with blended wing body Download PDFInfo
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- CN202609085U CN202609085U CN201220207832.7U CN201220207832U CN202609085U CN 202609085 U CN202609085 U CN 202609085U CN 201220207832 U CN201220207832 U CN 201220207832U CN 202609085 U CN202609085 U CN 202609085U
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Abstract
The utility model discloses an aircraft aerodynamic configuration with a blended wing body. The aerodynamic configuration of one side of the aircraft with the blended wing body serves as an example, a central aircraft body, a transition section and an outer wing section are arranged respectively spanwise, the transition section is located between the central aircraft body and the outer wing section, and the area ration of the central aircraft body, the transition section and the outer wing section is 1:0.350:0.554. The technical scheme includes that the drag divergence mach number Madd satisfies the condition that Madd=0.83, the maximum lift-drag ratio Kmax satisfies the condition that Kmax=25, and the maximum lift-drag ratio is 8.7% higher than that the wing body fusion layout. Compared with the wing body fusion layout, the aircraft aerodynamic configuration has high aerodynamic efficiency and good lift-drag performance, longitudinal moment static stability margin is 3%, the self-balancing design requirement in cruising flight is met basically, and the aircraft aerodynamic configuration has large loading space at the same time.
Description
Technical field
The present invention relates to the Flight Vehicle Design field, specifically is a kind of aircraft aerodynamic configuration that mixes wing body that adopts.
Background technology
Along with the eighties in 20th century wing body merge the initial test flight of the huge strategic bomber B2 of all-wing aircraft layout, people have produced great interest and discussion to the possibility that this type of profile is applied to civil aviaton's passenger plane or transport plane.Boeing is from early 1990s begin one's study the technical of blended wing-body profile and coml feasibility and Conceptual Design Study, and Europe, Russia and Japan etc. also carry out similar research in succession subsequently.With respect to normal arrangement, the advantage that wing body merges layout mainly show following some, adopt wing body to merge tailless configuration, reduced to soak area greatly, possessed higher pneumatic efficiency; Because the raising of pneumatic efficiency has reduced fuel oil consumption, and has reduced the discharging of oxides of nitrogen, has higher environmental advantage; Roomy central body has possessed the big and high advantage of structure efficiency of loading space; Driving engine is placed roomy body upper surface, effectively shielded engine noise and avoided noise simultaneously, help reducing noise level by the reflection of wing lower surface.But wing body merges layout also has associated disadvantages, merges layout like the described wing body of patent US-20090152392A1, and thicker central body and transition phase are prone to produce shock wave when transonic speed flying; The outer panel sweepback angle is bigger, and pneumatic efficiency is lower and be unfavorable for balance in pitch control, and the limited wings body merges the further raising of layout aeroperformance, and central body is shorter, can't arrange more escape hatch door, is difficult to satisfy airworthiness requirement.
Summary of the invention
Merge the pneumatic efficiency and the deficiency of fore-and-aft control ability that exists in the topology for overcoming existing wing body, the present invention proposes a kind of aircraft aerodynamic configuration that adopts mixing wing body.
With said mixing wing body aircraft one side aerodynamic configuration is example; Open up to being respectively central body, transition phase and outer panel along body; And described transition phase is between central body and outer panel, and the area of central body, transition phase and outer panel ratio is 1: 0.350: 0.554;
A. before adopting, central body loads back unloading aerofoil profile; Central authorities' body comprises central body root control surface, central body middle part control surface, central body taper control surface; The aspect of central authorities' body is trapezoidal; The area of conter of central authorities' body is 52.5% of a full machine half module area of conter; The body leading edge sweep α of central authorities is 65 °; The body root control surface chord length L of central authorities
4=38m; Central authorities' body taper control surface is apart from the span distance S of central body root control surface
6-4=6.8342m, the coordinate on central body taper control surface leading edge summit be (15.0740m, 6.8341m, 0.7000m), central body taper control surface chord length L
6=20.7739m; Central authorities' body middle part control surface is apart from the span distance S5-4=3.4171m of central body root control surface; The chord length of central authorities' body middle part control surface is 29.3869m, the coordinate on control surface leading edge summit, central body middle part be (7.5370m, 3.4171m, 0.3500m);
The leading edge summit of the aerofoil profile of central authorities' body root control surface overlaps with central body root control surface leading edge summit; And the abscissa x and the ordinate y of the aerofoil profile of said central body root control surface all amplified 38 times, obtain the cross sectional shape of central body root control surface;
The leading edge summit of the aerofoil profile of central authorities' body middle part control surface overlaps with control surface leading edge summit, central body middle part; And the abscissa x of the aerofoil profile of said central body middle part control surface amplified 29.3869 times; Ordinate y amplifies 31.0119 times, obtains the cross sectional shape of central body middle part control surface;
The leading edge summit of the aerofoil profile of central authorities' body taper control surface overlaps with central body taper control surface leading edge summit; And the abscissa x of the aerofoil profile of said central body taper control surface amplified 20.7739 times; Ordinate y amplifies 22.9655 times, obtains the cross sectional shape of central body taper control surface;
B. transition phase comprises central body taper control surface, transition phase middle part control surface, transition phase taper control surface; The aspect of transition phase is trapezoidal, and central body taper control surface is the root of transition phase; The area of conter of transition phase is 18.4% of a full machine half module area of conter; Transition phase leading edge sweep β is 50 °; Transition phase taper control surface is apart from the span distance S of central body taper control surface
8-6=4.8464m, the coordinate on transition phase taper control surface leading edge summit be (20.6963m, 11.6804m, 1.4000m), transition phase taper control surface chord length L
8=8.3942m;
Transition phase middle part control surface is apart from the span distance S of central body taper control surface
7-6=2.4232m; The chord length of confirming transition phase middle part control surface through above geometric relationship is 14.5841m, the coordinate on control surface leading edge summit, transition phase middle part be (17.8851m, 9.2572m, 1.0500m);
Before adopting, the aerofoil profile of transition phase middle part control surface loads back unloading aerofoil profile; The leading edge summit of the aerofoil profile of transition phase middle part control surface overlaps with control surface leading edge summit, transition phase middle part, and the abscissa x of aerofoil profile is amplified 14.5841 times, and ordinate y amplifies 14.6570 times, obtains the cross sectional shape of transition phase middle part control surface;
The aerofoil profile of transition phase taper control surface adopts supercritical airfoil; The leading edge summit of the aerofoil profile of transition phase taper control surface overlaps with transition phase taper control surface leading edge summit, and the abscissa x and the ordinate y of aerofoil profile amplified 8.3942 times respectively, obtains the cross sectional shape of transition phase taper control surface;
C. outer panel comprises transition phase taper control surface, outer panel middle part control surface, outer panel taper control surface; And, adopt approach based on linear interpolation to obtain the 3-d modelling of outer panel through described transition phase taper control surface, outer panel middle part control surface and outer panel taper control surface;
The transition phase taper control surface of outer panel is the root of outer panel; The area of conter of outer panel is 29.1% of a full machine half module area of conter; Outer panel leading edge sweep γ is 26 °; Outer panel taper control surface is apart from the span distance S of transition phase taper control surface
10-8=19.8794m, the coordinate on outer panel taper control surface leading edge summit be (30.3429m, 31.5600m, 1.400m), outer panel taper control surface chord length L
10=2.8132m;
Outer panel middle part control surface is apart from the span distance S of transition phase taper control surface
9-8=9.9397m; The chord length of outer panel middle part control surface is 5.6037m, the coordinate on control surface leading edge summit, outer panel middle part be (25.5196m, 21.6202m, 1.4000m);
The aerofoil profile of outer panel middle part control surface adopts supercritical airfoil; The leading edge summit of the aerofoil profile of outer panel middle part control surface overlaps with control surface leading edge summit, outer panel middle part, and aerofoil profile is spent according to right-hand rule rotation 1.7 around described leading edge summit, forms negative geometric twist; The abscissa x and the ordinate y of aerofoil profile are amplified 5.6037 times respectively, obtain the cross sectional shape of outer panel middle part control surface;
The aerofoil profile that constitutes outer wing taper control surface adopts the wingtip aerofoil profile; The leading edge summit of the aerofoil profile that constitutes outer wing taper control surface is overlapped with outer panel taper control surface leading edge summit, the abscissa x and the ordinate y of aerofoil profile amplified 2.8132 times respectively, obtain the cross sectional shape of outer panel taper control surface.
The aerofoil profile data that load unloading aerofoil profile in back before said are shown in table one, and wherein the aerofoil profile leading edge point is (0,0);
Load the aerofoil profile data of back unloading aerofoil profile before the table one
The aerofoil profile data of said supercritical airfoil are shown in table two, and wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table two supercritical airfoil
The aerofoil profile data of said wingtip aerofoil profile are shown in table three, and wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table three wingtip aerofoil profile
The present invention can be widely used in military-civil transportation type layout of future generation, and its concrete advantage is:
Central authorities' body is providing lift; Leading edge sweep that central authorities' body is bigger and bigger local chord length, the drag due to shock wave when effectively having avoided transonic flight; Merge the empennage that layout has been cancelled normal arrangement owing to mix wing body, outer wing has produced stronger nose-down pitching moment, is unfavorable for balance.Therefore, the back unloading aerofoil profile that central body adopts provides nose-up pitching moment balance outer wing nose-down pitching moment through the negative lift that airfoil trailing edge produced, and helps full machine and realizes the trim designing requirement under the cruising condition, reduces the trim resistance.
Merge layout larger area transitional region with respect to wing body, the less transition phase of the present invention has been realized the quick transition of central body and outer panel, has reduced the adverse effect of the transition phase of low pneumatic efficiency to full machine aeroperformance.
Merge the bigger outer wing leading edge sweep of layout with respect to wing body, outer panel of the present invention adopts the high aspect ratio supercritical wing of less leading edge sweep and thickness, when having guaranteed transonic flight than high lift-drag ratio and better drag divergence characteristic.Less outer wing leading edge sweep has reduced the moment of flexure of wing root, has reduced structural weight simultaneously.
Roomy central body provides bigger loading space, can satisfy overall cargo-carring demand.Merge the less leading edge sweep of layout central authorities' body with respect to wing body, the present invention central authorities body sweepback angle is bigger, length increases, and helps arranging more escape hatch door, and airworthiness requirement is content with very little.Can driving engine be placed central body upper surface afterbody, effectively reduce noise level.
Through the CFD Numerical Simulation Analysis, mix blended wing-body layout maximum lift-drag ratio K
Max=25, obtain mixing pneumatic efficiency that wing body the merges layout body of flying wing to wing and merge layout and improved 8.7%; Vertically adopting the static-stability design, is 3% with respect to the static stability marging of the average aerodynamic force chord length of full area of conter, when having reached cruising flight basically from the trim designing requirement; Unshock state when having realized cruising flight, drag divergence Mach number Ma
Dd=0.83.
Description of drawings
Accompanying drawing 1 is to mix wing body to merge the layout birds-eye view;
Accompanying drawing 2 is to mix the central body that wing body merges layout;
Accompanying drawing 3 is to mix the transition phase that wing body merges layout;
Accompanying drawing 4 is to mix the outer wing that wing body merges layout;
Accompanying drawing 5 is to mix wing body to merge the layout lateral plan;
Accompanying drawing 6 is to mix wing body to merge the layout front elevation;
Accompanying drawing 7 is to mix the A-A cutaway view that wing body merges layout;
Accompanying drawing 8 is to mix the B-B cutaway view that wing body merges layout;
Accompanying drawing 9 is to mix the C-C cutaway view that wing body merges layout;
Accompanying drawing 10 is to mix the D-D cutaway view that wing body merges layout;
Accompanying drawing 11 is to mix the E-E cutaway view that wing body merges layout;
Accompanying drawing 12 is to mix the F-F cutaway view that wing body merges layout;
Accompanying drawing 13 is to mix the G-G cutaway view that wing body merges layout.Wherein:
1. central body 2. transition phases 3. outer panels 4. central body root control surface
5. central body middle part control surface 6. central body taper control surface 7. transition phases middle part control surface
8. transition phase taper control surface 9. outer panels middle parts control surface 10. outer panel taper control surface
11. control surface leading edge summit, 12. central body middle part, central body root control surface leading edge summit
13. control surface leading edge summit, central body taper control surface leading edge summit 14. transition phases middle part
15. control surface leading edge summit, transition phase taper control surface leading edge summit 16. outer panels middle part
17. load unloading aerofoil profile in back before the outer panel taper control surface leading edge summit 18.
19. supercritical airfoil 20. wingtip aerofoil profile α. central body leading edge sweep β. the transition phase leading edge sweep
γ. outer panel leading edge sweep L
4. central body root control surface chord length L
6. central body taper control surface chord length
L
8. transition phase taper control surface chord length L
10. outer panel taper control surface chord length
S
5-4. central body middle part control surface is apart from the span distance of central body root control surface
S
6-4. central body taper control surface is apart from the span distance of central body root control surface
S
7-6. transition phase middle part control surface is apart from the span distance of central body taper control surface
S
8-6. transition phase taper control surface is apart from the span distance of central body taper control surface
S
9-8. outer panel middle part control surface is apart from the span distance of transition phase taper control surface
S
10-8. outer panel taper control surface is apart from the span distance of transition phase taper control surface
The specific embodiment
Present embodiment is a kind of aerodynamic configuration that adopts the aircraft that mixes wing body; As shown in Figure 2; Present embodiment is an example with a side of body; To being respectively central body 1, transition phase 2 and outer panel 3, and described transition phase 2 is between central body 1 and outer panel 3 along body exhibition, and the area ratio of central body 1, transition phase 2 and outer panel 3 is 1: 0.350: 0.554.
In the present embodiment; Central authorities' body 1 comprises central body root control surface 4, central body middle part control surface 5, central body taper control surface 6; And, obtain the 3-d modelling of central body 1 through approach based on linear interpolation with described central body root control surface 4, central body middle part control surface 5 and central body taper control surface 6.
Central authorities' body
As shown in Figure 2, the aspect of central body 1 is trapezoidal.The area of conter of central authorities' body 1 is 52.5% of a full machine half module area of conter; The body leading edge sweep α of central authorities is 65 °; The body root control surface chord length L of central authorities
4=38m; Central authorities' body taper control surface 6 is apart from the span distance S of central body root control surface 4
6-4=6.8342m, the coordinate on central body taper control surface leading edge summit 13 be (15.0740m, 6.8341m, 0.7000m), central body taper control surface chord length L
6=20.7739m.
Central authorities' body middle part control surface 5 is apart from the span distance S5-4=3.4171m of central body root control surface 4.The chord length of confirming central body middle part control surface 5 through above geometric relationship is 29.3869m, the coordinate on control surface leading edge summit, central body middle part 12 be (7.5370m, 3.4171m, 0.3500m).Described central body middle part control surface 5 is between centre body root control surface 4 and central body taper control surface 6.
Before all adopting, the aerofoil profile of described central body root control surface 4, central body middle part control surface 5 and central body taper control surface 6 loads back unloading aerofoil profile 18.
The leading edge summit of the aerofoil profile of central authorities' body root control surface 4 overlaps with central body root control surface leading edge summit 11; And the abscissa x and the ordinate y of the aerofoil profile of said central body root control surface all amplified 38 times; Obtain the cross sectional shape of central body root control surface 4, shown in figure 11.
The leading edge summit of the aerofoil profile of central authorities' body middle part control surface 5 overlaps with control surface leading edge summit, central body middle part 12; And the abscissa x of the aerofoil profile of said central body middle part control surface 5 amplified 29.3869 times; Ordinate y amplifies 31.0119 times; Obtain the cross sectional shape of central body middle part control surface 5, shown in figure 12.
The leading edge summit of the aerofoil profile of central authorities' body taper control surface 6 overlaps with central body taper control surface leading edge summit 13; And the abscissa x of the aerofoil profile of said central body taper control surface 6 amplified 20.7739 times; Ordinate y amplifies 22.9655 times; Obtain the cross sectional shape of central body taper control surface 6, shown in figure 13.
Transition phase
In the present embodiment; Transition phase 2 comprises central body taper control surface 6, transition phase middle part control surface 7, transition phase taper control surface 8; And, adopt approach based on linear interpolation to obtain the 3-d modelling of transition phase 2 through described central body taper control surface 6, transition phase middle part control surface 7 and transition phase taper control surface 8.
As shown in Figure 2, the aspect of transition phase 2 is trapezoidal, and central body taper control surface 6 is the root of transition phase 2.The area of conter of transition phase 2 is 18.4% of a full machine half module area of conter; Transition phase leading edge sweep β is 50 °; Transition phase taper control surface 8 is apart from the span distance S of central body taper control surface 6
8-6=4.8464m, the coordinate on transition phase taper control surface leading edge summit 15 be (20.6963m, 11.6804m, 1.4000m), transition phase taper control surface chord length L
8=8.3942m.
Transition phase middle part control surface 7 is apart from the span distance S of central body taper control surface 6
7-6=2.4232m.The chord length of confirming transition phase middle part control surface 7 through above geometric relationship is 14.5841m, the coordinate on control surface leading edge summit, transition phase middle part 14 be (17.8851m, 9.2572m, 1.0500m).
Before adopting, the aerofoil profile of transition phase middle part control surface 7 loads back unloading aerofoil profile 18.The leading edge summit of the aerofoil profile of transition phase middle part control surface 7 overlaps with control surface leading edge summit, transition phase middle part 14; And the abscissa x of aerofoil profile amplified 14.5841 times; Ordinate y amplifies 14.6570 times, obtains the cross sectional shape of transition phase middle part control surface 7, and is shown in figure 14.
The aerofoil profile of transition phase taper control surface 8 adopts supercritical airfoil 19.The leading edge summit of the aerofoil profile of transition phase taper control surface 8 overlaps with transition phase taper control surface leading edge summit 15, and the abscissa x and the ordinate y of aerofoil profile amplified 8.3942 times respectively, obtains the cross sectional shape of transition phase taper control surface 8, and is shown in figure 15.
In the present embodiment; Outer panel 3 comprises transition phase taper control surface 8, outer panel middle part control surface 9, outer panel taper control surface 10; And, adopt approach based on linear interpolation to obtain the 3-d modelling of outer panel 3 through described transition phase taper control surface 8, outer panel middle part control surface 9 and outer panel taper control surface 10.
Outer panel
Like Fig. 2, shown in 3 and 4, outer panel 3 is a high mounted wing, and the aspect of outer panel 3 is trapezoidal, and transition phase taper control surface 8 is the root of outer panel 3.The area of conter of outer panel 3 is about 29.1% of full machine half module area of conter; Outer panel leading edge sweep γ is 26 °; Outer panel taper control surface 10 is apart from the span distance S of transition phase taper control surface 8
10-8=19.8794m, the coordinate on outer panel taper control surface leading edge summit 17 be (30.3429m, 31.5600m, 1.400m), outer panel taper control surface chord length L
10=2.8132m.
Outer panel middle part control surface 9 is apart from the span distance S of transition phase taper control surface 8
9-8=9.9397m.The chord length of confirming outer panel middle part control surface 9 through above geometric relationship is 5.6037m, the coordinate on control surface leading edge summit, outer panel middle part 16 be (25.5196m, 21.6202m, 1.4000m).
The aerofoil profile of outer panel middle part control surface 9 adopts supercritical airfoil 19.The leading edge summit of the aerofoil profile of outer panel middle part control surface 9 overlaps with control surface leading edge summit, outer panel middle part 16, and aerofoil profile is spent according to right-hand rule rotation 1.7 around described leading edge summit, forms negative geometric twist.The abscissa x and the ordinate y of aerofoil profile are amplified 5.6037 times respectively, obtain the cross sectional shape of outer panel middle part control surface 9, shown in figure 16.
The aerofoil profile that constitutes outer wing taper control surface 10 adopts wingtip aerofoil profile 20.The leading edge summit of the aerofoil profile that constitutes outer wing taper control surface 10 is overlapped with outer panel taper control surface leading edge summit 17, the abscissa x and the ordinate y of aerofoil profile amplified 2.8132 times respectively, obtain the cross sectional shape of outer panel taper control surface 10, shown in figure 17.
, verified that present embodiment has possessed the body of flying wing to wing and merged the higher pneumatic efficiency of layout, and had bigger loading space the present embodiment analysis through the CFD numerical value emulation method.
The aerofoil profile data that load unloading aerofoil profile in back before said are shown in table one, and wherein the aerofoil profile leading edge point is (0,0);
Load the aerofoil profile data of back unloading aerofoil profile before the table one
The aerofoil profile data of said supercritical airfoil are shown in table two, and wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table two supercritical airfoil
The aerofoil profile data of said wingtip aerofoil profile are shown in table three, and wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table three wingtip aerofoil profile
The maximum lift-drag ratio K of present embodiment
Max=25, the body of flying wing to wing merges layout and improves 8.7%, has the resistive ability of good liter.The longitudinal moment static stability marging is 3%, when having reached cruising flight basically from the trim designing requirement.Unshock state when having realized cruising flight, drag divergence Mach number Ma
Dd=0.83.
Claims (4)
1. one kind is adopted the aircraft aerodynamic configuration that mixes wing body; It is characterized in that to being respectively central body, transition phase and outer panel, and described transition phase is between central body and outer panel along body exhibition, and the area of central body, transition phase and outer panel ratio is 1: 0.350: 0.554;
A. before adopting, central body loads back unloading aerofoil profile; Central authorities' body comprises central body root control surface, central body middle part control surface, central body taper control surface; The aspect of central authorities' body is trapezoidal; The area of conter of central authorities' body is 52.5% of a full machine half module area of conter; The body leading edge sweep α of central authorities is 65 °; The body root control surface chord length L of central authorities
4=38m; Central authorities' body taper control surface is apart from the span distance S of central body root control surface
6-4=6.8342m, the coordinate on central body taper control surface leading edge summit be (15.0740m, 6.8341m, 0.7000m), central body taper control surface chord length L
6=20.7739m; Central authorities' body middle part control surface is apart from the span distance S5-4=3.4171m of central body root control surface; The chord length of central authorities' body middle part control surface is 29.3869m, the coordinate on control surface leading edge summit, central body middle part be (7.5370m, 3.4171m, 0.3500m);
The leading edge summit of the aerofoil profile of central authorities' body root control surface overlaps with central body root control surface leading edge summit; And the abscissa x and the ordinate y of the aerofoil profile of said central body root control surface all amplified 38 times, obtain the cross sectional shape of central body root control surface;
The leading edge summit of the aerofoil profile of central authorities' body middle part control surface overlaps with control surface leading edge summit, central body middle part; And the abscissa x of the aerofoil profile of said central body middle part control surface amplified 29.3869 times; Ordinate y amplifies 31.0119 times, obtains the cross sectional shape of central body middle part control surface;
The leading edge summit of the aerofoil profile of central authorities' body taper control surface overlaps with central body taper control surface leading edge summit; And the abscissa x of the aerofoil profile of said central body taper control surface amplified 20.7739 times; Ordinate y amplifies 22.9655 times, obtains the cross sectional shape of central body taper control surface;
B. transition phase comprises central body taper control surface, transition phase middle part control surface, transition phase taper control surface; The aspect of transition phase is trapezoidal, and central body taper control surface is the root of transition phase; The area of conter of transition phase is 18.4% of a full machine half module area of conter; Transition phase leading edge sweep β is 50 °; Transition phase taper control surface is apart from the span distance S of central body taper control surface
8-6=4.8464m, the coordinate on transition phase taper control surface leading edge summit be (20.6963m, 11.6804m, 1.4000m), transition phase taper control surface chord length L
8=8.3942m; Transition phase middle part control surface is apart from the span distance S of central body taper control surface
7-6=2.4232m; The chord length of confirming transition phase middle part control surface through above geometric relationship is 14.5841m, the coordinate on control surface leading edge summit, transition phase middle part be (17.8851m, 9.2572m, 1.0500m);
Before adopting, the aerofoil profile of transition phase middle part control surface loads back unloading aerofoil profile; The leading edge summit of the aerofoil profile of transition phase middle part control surface overlaps with control surface leading edge summit, transition phase middle part, and the abscissa x of aerofoil profile is amplified 14.5841 times, and ordinate y amplifies 14.6570 times, obtains the cross sectional shape of transition phase middle part control surface;
The aerofoil profile of transition phase taper control surface adopts supercritical airfoil; The leading edge summit of the aerofoil profile of transition phase taper control surface overlaps with transition phase taper control surface leading edge summit, and the abscissa x and the ordinate y of aerofoil profile amplified 8.3942 times respectively, obtains the cross sectional shape of transition phase taper control surface;
C. outer panel comprises transition phase taper control surface, outer panel middle part control surface, outer panel taper control surface; And, adopt approach based on linear interpolation to obtain the 3-d modelling of outer panel through described transition phase taper control surface, outer panel middle part control surface and outer panel taper control surface;
The transition phase taper control surface of outer panel is the root of outer panel; The area of conter of outer panel is 29.1% of a full machine half module area of conter; Outer panel leading edge sweep γ is 26 °; Outer panel taper control surface is apart from the span distance S of transition phase taper control surface
10-8=19.8794m, the coordinate on outer panel taper control surface leading edge summit be (30.3429m, 31.5600m, 1.400m), outer panel taper control surface chord length L
10=2.8132m;
Outer panel middle part control surface is apart from the span distance S of transition phase taper control surface
9-8=9.9397m; The chord length of outer panel middle part control surface is 5.6037m, the coordinate on control surface leading edge summit, outer panel middle part be (25.5196m, 21.6202m, 1.4000m);
The aerofoil profile of outer panel middle part control surface adopts supercritical airfoil; The leading edge summit of the aerofoil profile of outer panel middle part control surface overlaps with control surface leading edge summit, outer panel middle part, and aerofoil profile is spent according to right-hand rule rotation 1.7 around described leading edge summit, forms negative geometric twist; The abscissa x and the ordinate y of aerofoil profile are amplified 5.6037 times respectively, obtain the cross sectional shape of outer panel middle part control surface;
The aerofoil profile that constitutes outer wing taper control surface adopts the wingtip aerofoil profile; The leading edge summit of the aerofoil profile that constitutes outer wing taper control surface is overlapped with outer panel taper control surface leading edge summit, the abscissa x and the ordinate y of aerofoil profile amplified 2.8132 times respectively, obtain the cross sectional shape of outer panel taper control surface.
2. a kind of according to claim 1 aircraft aerodynamic configuration that mixes wing body that adopts; It is characterized in that the said preceding aerofoil profile data that load back unloading aerofoil profile are shown in table one, wherein the aerofoil profile leading edge point is (0,0);
Load the aerofoil profile data of back unloading aerofoil profile before the table one
3. a kind of according to claim 1 aircraft aerodynamic configuration that mixes wing body that adopts; It is characterized in that the aerofoil profile data of said supercritical airfoil are shown in table two, wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table two supercritical airfoil
4. a kind of according to claim 1 aircraft aerodynamic configuration that mixes wing body that adopts; It is characterized in that the aerofoil profile data of said wingtip aerofoil profile are shown in table three, wherein the aerofoil profile leading edge point is (0,0);
The aerofoil profile data of table three wingtip aerofoil profile
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730181A (en) * | 2012-05-11 | 2012-10-17 | 西北工业大学 | Aerobat aerodynamic configuration adopting mixing wing body |
| CN105173112A (en) * | 2015-08-14 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Method for adjusting wing class model and system for adjusting wing class model |
| CN105181293A (en) * | 2015-06-04 | 2015-12-23 | 中国航天空气动力技术研究院 | Wing-body combination aircraft wind tunnel test model designing and processing method |
| CN106741919A (en) * | 2016-12-21 | 2017-05-31 | 顺丰科技有限公司 | A kind of fixed-wing unmanned plane of VTOL |
| WO2018129768A1 (en) * | 2017-01-16 | 2018-07-19 | 顺丰科技有限公司 | Fused wing and body aircraft |
| CN108367808A (en) * | 2015-12-09 | 2018-08-03 | 庞巴迪公司 | Blended wing-body aircraft |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
-
2012
- 2012-05-11 CN CN201220207832.7U patent/CN202609085U/en not_active Withdrawn - After Issue
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730181A (en) * | 2012-05-11 | 2012-10-17 | 西北工业大学 | Aerobat aerodynamic configuration adopting mixing wing body |
| CN102730181B (en) * | 2012-05-11 | 2014-03-12 | 西北工业大学 | Aerobat aerodynamic configuration adopting mixing wing body |
| CN105181293A (en) * | 2015-06-04 | 2015-12-23 | 中国航天空气动力技术研究院 | Wing-body combination aircraft wind tunnel test model designing and processing method |
| CN105173112A (en) * | 2015-08-14 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Method for adjusting wing class model and system for adjusting wing class model |
| CN108367808A (en) * | 2015-12-09 | 2018-08-03 | 庞巴迪公司 | Blended wing-body aircraft |
| CN108367808B (en) * | 2015-12-09 | 2022-05-31 | 庞巴迪公司 | Wing-body integrated airplane |
| CN106741919A (en) * | 2016-12-21 | 2017-05-31 | 顺丰科技有限公司 | A kind of fixed-wing unmanned plane of VTOL |
| WO2018129768A1 (en) * | 2017-01-16 | 2018-07-19 | 顺丰科技有限公司 | Fused wing and body aircraft |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
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