CN103332288A - Edge strip at trailing edge of airplane and design method thereof - Google Patents
Edge strip at trailing edge of airplane and design method thereof Download PDFInfo
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- CN103332288A CN103332288A CN2013102345736A CN201310234573A CN103332288A CN 103332288 A CN103332288 A CN 103332288A CN 2013102345736 A CN2013102345736 A CN 2013102345736A CN 201310234573 A CN201310234573 A CN 201310234573A CN 103332288 A CN103332288 A CN 103332288A
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Abstract
The invention provides an edge strip at a trailing edge of an airplane and a design method of the edge strip. The side surface at the front edge of the edge strip is glued with the side surface of the back edge of the airplane, the upper surface of the edge strip is in smooth transition with the upper surface of a main wing of the airplane, and the lower surface of the edge strip is in smooth transition with the lower surface of the main wing of the airplane, so that airflow can smoothly flow through the edge strip. When an inner flap is packed up, the lower surface of the edge strip is glued with the upper surface of the inner flap. According to the edge strip provided by the invention, the edge strip is installed on the main wing of the airplane and corresponds to the inner flag, so that the gap way width Gf and the gap way overlap quantity Of of the trailing edge flap can be adjusted, the flow separation of the trailing edge flap can be controlled under the status that the trailing edge flap is large in skewness, and the aerodynamic performance of the airplane under the taking-off/landing status of the airplane can be improved.
Description
Technical field
The present invention relates to the Flight Vehicle Design field, specifically is a kind of edge strip and method of designing thereof that is installed in aircraft main wing trailing edge place.
Background technology
Large aircraft carries greatly owing to the wing, take off/flying speed is low when landing, and needs very high disposable lift.Present generation aircraft mainly obtains high disposable lift by the following method: increase wing camber, increase wing area, the control etc. of flowing.Increasing wing camber is the most frequently used method, and it is mainly realized by trailing edge flap deflection.The trailing edge flap deflection angle is more big, and wing camber changes just more many, and the aircraft disposable lift is generally also just more high.But, trailing edge flap can with deflection angle be limited.When trailing edge flap is in big degree of bias state, the pressure coefficient peak value of trailing edge flap head is very high, brings out flow separation at the trailing edge flap upper surface easily, causes loss of lift, reduce taking off/landing data of aircraft, even the situation of taking off/land requirement may occur to satisfy.
In order to control the flow separation that the big degree of bias state of trailing edge flap occurs, improve taking off/landing data of aircraft, carried out the research of a large amount of active flow control techniques both at home and abroad.As vortex generator being installed at the trailing edge flap upper surface, blowing at trailing edge flap upper surface fluting/air-breathing, installing the plasma excitation device additional, being laid MEMS actuator etc., all can obtain certain effect.But these technology ubiquity usage condition harshnesses, destroy the wing flap original structure, need shortcomings such as additional energy input, auxiliary mechanism's complexity, working service cost height, limited the engineering practical application.
Summary of the invention
For overcoming the usage condition harshness that exists in the prior art, destroy the wing flap original structure, needing additional energy input, auxiliary mechanism's complexity, the high deficiency of working service cost, the present invention proposes a kind of aircraft main wing trailing edge edge strip and method of designing thereof.
The edge strip at the aircraft main wing trailing edge place that the present invention proposes, described edge strip are installed on the aircraft main wing and are corresponding with interior wing flap, to adjust the seam road width G of trailing edge flap
fWith seam trace overlap amount O
f, under the big degree of bias state of trailing edge flap, control trailing edge flap flow separation improves and takes off/aeroperformance of landing state.
The trailing edge of described edge strip is arc; The exhibition of this edge strip exhibition of wing flap in length l and the aircraft is identical to length L, and the width at edge strip two ends is 25% of edge strip maximum width D; The edge strip exhibition is the wideest to the width at length direction plane of symmetry place, and the maximum width D of described edge strip is that the edge strip exhibition is to 0.5% of length l; Be connected with spline method is smooth between the two ends of edge strip arc trailing edge and described edge strip the widest part.The thickness of described edge strip and aircraft main wing trailing edge cooperation place is identical with the thickness of this aircraft main wing trailing edge, and the profile of the upper surface of described edge strip and lower surface all the profile with the aircraft main wing that cooperates is identical.
The side surface of the side surface of described edge strip leading edge and aircraft main wing trailing edge is bonding, and the upper surface smooth transition of the upper surface of described edge strip and aircraft main wing, the lower surface smooth transition of the lower surface of described edge strip and aircraft main wing is so that air-flow can flow through edge strip smooth-goingly.When interior wing flap was packed up, the lower surface of edge strip and the upper surface of interior wing flap were fitted.
The invention allows for the method for designing of a kind of described aircraft main wing trailing edge place edge strip, its detailed process is:
Cl=(F
y*cosa-F
x*sina)/(0.5*ρ*V
2*S)； （1）
Wherein: F
yBe that the total aerodynamic force of full machine is at the component of y direction; F
xBe that the total aerodynamic force of full machine is at the component of x direction; A is the incoming flow angle of attack; ρ is density of air; V is the flying speed of aircraft; S is the reference area of aircraft.
Cp=（Pressure-Preference)/(0.5*ρ*V
2)； （2）
Wherein: Pressure is the pressure of exhibition on interior each coordinate points of wing flap profile at section place; Preference is reference pressure, gets standard atmosphere.
As edge strip maximum width D=D
Max, and a=0 °～20 ° of the incoming flow angles of attack, if airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip maximum width D meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, then edge strip maximum width D does not satisfy pneumatic requirement, need reduce the maximum width D of edge strip, proceeds edge strip design, enters step 7.
Formula (3) is:
△D
i+1=△D
i/(1-k*△Cp
i/D
max)； （3）
Wherein: △ D
iIt is the adjustment amount of the i time edge strip maximum width; △ D
I+1It is the adjustment amount of the i+1 time edge strip maximum width; △ Cp
iBe goal pressure coefficient Cp
Min2The interior wing flap profile pressure coefficient minimum value Cp corresponding with the i time edge strip maximum width adjustment amount
Min_ △ DiDifference; D
MaxThe upper limit for the maximum width of the edge strip determined by structural constraint; K is relaxation factor, is used for control adjustment amount △ D
I+1Size.Described i is the adjustment number of times of edge strip maximum width.
After the i+1 time adjustment, following relational expression is arranged:
△Cp
i+1=Cp
min2-Cp
min_△Di+1； （4）
In the formula (4): Cp
Min_ △ Di+1It is the interior wing flap profile pressure coefficient minimum value of adjustment amount correspondence of the i+1 time edge strip maximum width; △ Cp
I+1Difference for the goal pressure coefficient interior wing flap profile pressure coefficient minimum value corresponding with the adjustment amount of the i+1 time edge strip maximum width.
When | △ Cp
I+1/ Cp
Min2|≤0.05 o'clock, finish to adjust, enter step 10.
If airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip maximum width D meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, goal pressure coefficient Cp is described
Min2 
Unreasonable, increment △ value is bigger than normal, and increment △ is adjusted to 90% of former increment, reenters step 7 then, proceeds the design of edge strip.Described increment △ is the pressure coefficient of interior wing flap profile
Minimum value Cp
Min1Increment.
Among the present invention, install edge strip additional by the main wing trailing edge place at certain aircraft, obvious change has taken place in the seam road parameter of trailing edge flap.The trailing edge flap seam trace overlap amount O2 that uses behind the edge strip will be used trailing edge flap seam trace overlap amount O1 before the edge strip to repair to be; And O1 is negative value, O2 be on the occasion of.Along with use trailing edge flap seam trace overlap amount O2 behind the edge strip repair on the occasion of, become the trailing edge flap seam road width G 1 used before the edge strip and stitch road width G 2 for using the trailing edge flap behind the edge strip, and G2＜G1.The effect that this variation of seam road parameter produces is: the aircraft main wing is strengthened the inhibit function that the trailing edge flap upper surface flows, the pressure coefficient peak value of trailing edge flap descends, adverse pressure gradient reduces, thereby the flow separation that originally was present in the trailing edge flap upper surface is effectively controlled, the wing flap quality improving that flows, lift increases, take off/aeroperformance of landing state promotes.
Compared with prior art, the obtained effect of the present invention shows in the following areas:
1. edge strip can effectively improve and takes off/aeroperformance of landing state.Only install an edge strip additional at the main wing trailing edge place of certain aircraft, flow separation in can effectively controlling on the wing flap, lift under each angle of attack is all obviously promoted, especially angle of attack=8 °～12 ° takes off/lands the most frequently used state, it is about 4% that lift increases, and effectively improved taking off/landing data of aircraft.
2. edge strip is installed on the main wing trailing edge place of aircraft by bonding way, has avoided destroying the problem of aircraft original structure, is specially adapted to the improvement design of existing aircraft, and convenient for installation and maintenance, and engineering practicability is strong.
3. edge strip has effectively relaxed the contradiction of maximum lift with the most frequently used state disposable lift that takes off/land.Because the degree of bias of trailing edge flap designs for main purpose to guarantee maximum lift, that causes angle of attack=8 °～12 ° easily takes off/lands the most frequently used state, and flow separation appears in trailing edge flap.Use edge strip under the prerequisite that guarantees maximum lift, to cure the trailing edge flap flow separation of taking off/landing under the most frequently used angle of attack, avoid reducing the trailing edge flap degree of bias in order to prevent trailing edge flap from separating, cause the problem of maximum lift loss.
4. the main wing trailing edge of large aircraft generally is designed to the spoiler form, and therefore, edge strip is installed on main wing trailing edge place, on the one hand, can be used for controlling the trailing edge flap flow separation, improves to take off/aeroperformance of landing state; On the other hand, can increase the area of spoiler again, improve the efficient of spoiler.
Description of drawings
Accompanying drawing 1 is the application scheme drawing of edge strip on certain aircraft main wing;
Accompanying drawing 2 is the aircraft wing partial enlarged drawings that installed edge strip additional;
Accompanying drawing 3 is that the position of edge strip and aircraft main wing and trailing edge flap concerns scheme drawing;
Accompanying drawing 4 is that edge strip is adjusted trailing edge flap seam road parameter scheme drawing;
Accompanying drawing 5 is lift-rising effect scheme drawings of edge strip;
Accompanying drawing 6 is edge strip design flow diagram of the present invention;
Accompanying drawing 7 is full machine aerodynamic force decomposing schematic representations; Wherein: F
xBe that the total aerodynamic force of full machine is at the component of x direction, F
yBe that the total aerodynamic force of full machine is at the component of y direction, F
LiftBe full machine lift, F
DragIt is full machine resistance.
Accompanying drawing 8 is to install the preceding interior wing flap flow characteristic of edge strip additional;
Accompanying drawing 9 is that interior wing flap profile pressure coefficient minimum value is adjusted scheme drawing;
Accompanying drawing 10 is the interior wing flap flow characteristiies that install additional behind the edge strip;
Accompanying drawing 11 is to install the front/rear interior wing flap profile pressure coefficient distribution contrast of edge strip additional.Wherein:
1. leading edge slat; 2. aircraft main wing; 3. trailing edge flap; 4. edge strip; 5. interior wing flap; 6. outer wing flap; 7. interior flap surface limiting streamline; 8. interior wing flap defiber; 9. installing the preceding pressure coefficient of edge strip additional distributes; 10. the pressure coefficient that installs additional behind the edge strip distributes.
The specific embodiment
As accompanying drawing 1, shown in the accompanying drawing 2.Present embodiment is a kind of edge strip that is installed in aircraft main wing trailing edge place, and described edge strip 4 is positioned at this aircraft main wing 2 and wing flap 5 corresponding positions.Install edge strip 4 additional by the trailing edge at aircraft main wing 2, to adjust the seam road width G of trailing edge flap
fWith seam trace overlap amount O
f, under the big degree of bias state of trailing edge flap, control trailing edge flap flow separation improves and takes off/aeroperformance of landing state.
As shown in Figure 3.The described stripe board of edge strip 4 for making with aluminum alloy for certain aircraft, an and side surface of described edge strip 4 is arc, and be the trailing edge of described edge strip 4 with this curved side surface.The exhibition of edge strip 4 exhibition of wing flap 5 in length l and the aircraft is identical to length L, and the width at edge strip 4 two ends is 25% of edge strip 4 maximum width D; The exhibition of edge strip 4 is the wideest to the width at length direction plane of symmetry place, and the maximum width D of described edge strip 4 is that edge strip 4 exhibitions are to 0.5% of length l; Be connected with spline method is smooth between the two ends on edge strip 4 curved side surfaces and described edge strip 4 the widest part.The thickness of described edge strip 4 and aircraft main wing 2 trailing edge cooperation places is identical with the thickness of these aircraft main wing 2 trailing edges, and the profile of the upper surface of described edge strip 4 and lower surface all the profile with the aircraft main wing 2 that cooperates is identical.
Described edge strip 4 is installed in aircraft main wing 2 trailing edge places, and makes the position of edge strip 4 corresponding with the position of interior wing flap 5.The side surface of described edge strip 4 leading edges is connected by bonding mode with the side surface of aircraft main wing 2 trailing edges, and the upper surface smooth transition of the upper surface of described edge strip 4 and aircraft main wing 2, the lower surface smooth transition of the lower surface of described edge strip 4 and aircraft main wing 2 is so that air-flow can flow through edge strip 4 smooth-goingly.When interior wing flap 5 was packed up, the upper surface of the lower surface of edge strip 4 and interior wing flap 5 was fitted.
The edge strip that accompanying drawing 4 has provided present embodiment is used for adjusting the principle that trailing edge flap stitches the road parameter.Can see from accompanying drawing 4, install edge strip additional by the main wing trailing edge at certain aircraft, obvious change has taken place in the seam road parameter of trailing edge flap, will use trailing edge flap seam trace overlap amount O1 before the edge strip to repair to be the trailing edge flap seam trace overlap amount O2 that uses behind the edge strip; Describedly use the trailing edge flap seam trace overlap amount O1 before the edge strip to be negative value, use trailing edge flap seam trace overlap amount O2 behind the edge strip be on the occasion of.Along with use trailing edge flap seam trace overlap amount O2 behind the edge strip repair on the occasion of, become the trailing edge flap seam road width G 1 used before the edge strip and stitch road width G 2 for using the trailing edge flap behind the edge strip, and G2＜G1.
From the edge strip lift-rising effect scheme drawing of accompanying drawing 5 as can be seen, after the main wing trailing edge of certain aircraft installed edge strip additional, the lift under each angle of attack all was significantly increased.Particularly take off/the most frequently used angle of attack of landing state=8 °～12 °, it is about 4% that lift increases, and will effectively improve taking off/landing data of aircraft.
The main wing trailing edge edge strip that accompanying drawing 8, accompanying drawing 10 and accompanying drawing 11 have disclosed present embodiment improves to be taken off/physical mechanism of landing state aeroperformance.
The pressure coefficient that provides from accompanying drawing 11 distributes and can see, at Mach number Ma=0.20, during angle of attack=8 °, certain aircraft is before using edge strip, and the peak value of the pressure coefficient Cp of interior wing flap profile has reached-3.4.Interior wing flap pressure coefficient peak value height can form strong adverse pressure gradient near the pressure coefficient peak value, the danger that the wing flap generation separates in increasing, and this also can be confirmed from the interior wing flap flow characteristic of accompanying drawing 8.
The pressure coefficient peak value height of trailing edge flap, the main wing of the aircraft that has its source in and the seam road parameter between the trailing edge flap are unreasonable, and a little less than the inhibition ability that the main wing of aircraft flows to the trailing edge flap upper surface, it is too strong to wash effect on the trailing edge flap head air-flow.And after the main wing trailing edge of aircraft has installed edge strip additional, trailing edge flap seam trace overlap amount O
fIncrease trailing edge flap seam road width G
fReduce, the aircraft main wing is obviously strengthened the inhibit function of trailing edge flap.
The pressure coefficient of accompanying drawing 11 distributes and then shows, after the main wing trailing edge of aircraft installs edge strip additional, the pressure coefficient peak value of interior wing flap profile obviously descends, be reduced to-2.5 from original-3.4, effectively weakened adverse pressure gradient, therefore the flow characteristic of interior wing flap also is improved, and the separation of interior flap upper surface disappears, regained the desirable flow characteristic that adheres to, as shown in Figure 10.
Interior wing flap flow characteristic improves, the air-flow velocity of the feasible machine wing that is diversion is accelerated, be exactly that the main wing of aircraft and the pressure coefficient peak value of leading edge slat improve on the pressure coefficient that is reflected to accompanying drawing 11 distributes, circular rector increases, thereby effectively remedied the loss of lift of interior wing flap, increased resultant lift, improved and taken off/aeroperformance of landing state.
Present embodiment has also proposed a kind of method of designing of described edge strip, and detailed process is:
Cl=(F
y*cosa-F
x*sina)/(0.5*ρ*V
2*S)； （1）
Wherein: F
yBe that the total aerodynamic force of full machine is at the component of y direction; F
xBe that the total aerodynamic force of full machine is at the component of x direction; A is the incoming flow angle of attack; ρ is density of air; V is the flying speed of aircraft; S is the reference area of aircraft.Full machine aerodynamic force decomposes referring to accompanying drawing 7.
Step 2 determines that the scope of separation takes place trailing edge flap and the pressure coefficient of trailing edge flap distributes.Owing to take off/the most frequently used incoming flow angle of attack of landing state is about a=8 °.Therefore, determine a=8 ° of the incoming flow angle of attack, utilize the Tecplot PaintShop, import the flow field result who is calculated by step 1, the surperficial limiting streamline 7 that draws on the surface of interior wing flap 5, as shown in Figure 8.The defiber 8 of wing flap 5 in the meld line of surface limiting streamline 7 is.Behind the wing flap defiber 8, in the distance the shortest position of defiber 8 to interior wing flap 5 leading edges, the exhibition of wing flap 5 is to section in doing in obtaining, and the intersection of section and interior wing flap 5 is this exhibition to the interior wing flap profile of position.(x y), obtains the graph of a relation of pressure coefficient Cp and profile abscissa x, as shown in Figure 9 to take out pressure coefficient Cp on this profile and the geometric coordinate of profile.In the present embodiment, interior wing flap defiber 8 is opened up to length direction plane of symmetry place at interior wing flap 5 to the shortest position of distance of interior wing flap 5 leading edges.Pressure coefficient Cp is defined as:
Cp=（Pressure-Preference)/(0.5*ρ*V
2)； （2）
Wherein: Pressure is the pressure of exhibition on interior each coordinate points of wing flap profile at section place; Preference is reference pressure, gets standard atmosphere.
As edge strip maximum width D=D
Max, and a=0 °～20 ° of the incoming flow angles of attack, if airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip maximum width D meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, then edge strip maximum width D does not satisfy pneumatic requirement, need reduce the maximum width D of edge strip, proceeds edge strip design, enters step 7.
Formula (3) is:
△D
i+1=△D
i/(1-k*△Cp
i/D
max)； （3）
Wherein: △ D
iIt is the adjustment amount of the i time edge strip maximum width; △ D
I+1It is the adjustment amount of the i+1 time edge strip maximum width; △ Cp
iBe goal pressure coefficient Cp
Min2The interior wing flap profile pressure coefficient minimum value Cp corresponding with the i time edge strip maximum width adjustment amount
Min_ △ DiDifference; D
MaxThe upper limit for the maximum width of the edge strip determined by structural constraint; K is relaxation factor, is used for control adjustment amount △ D
I+1Size, present embodiment is got k=0.005.Described i is the adjustment number of times of edge strip maximum width.
After the i+1 time adjustment, following relational expression is arranged:
△Cp
i+1=Cp
min2-Cp
min_△Di+1； （4）
In the formula (4): Cp
Min_ △ Di+1It is the interior wing flap profile pressure coefficient minimum value of adjustment amount correspondence of the i+1 time edge strip maximum width; △ Cp
I+1Difference for the goal pressure coefficient interior wing flap profile pressure coefficient minimum value corresponding with the adjustment amount of the i+1 time edge strip maximum width.
When | △ Cp
I+1/ Cp
Min2|≤0.05 o'clock, finish to adjust, enter step 10.
If airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, goal pressure coefficient Cp is described
Min2Unreasonable, increment △ value is bigger than normal, and increment △ is adjusted to 90% of former increment, reenters step 7 then, proceeds the design of edge strip.The pressure coefficient minimum value Cp that described increment △ is interior wing flap profile
Min1Increment.
Claims (4)
1. an aircraft main wing trailing edge edge strip is characterized in that, described edge strip is installed on the aircraft main wing and is corresponding with interior wing flap, to adjust the seam road width G of trailing edge flap
fWith seam trace overlap amount O
f, under the big degree of bias state of trailing edge flap, control trailing edge flap flow separation improves and takes off/aeroperformance of landing state.
2. a kind of aircraft main wing trailing edge edge strip according to claim 1 is characterized in that the trailing edge of described edge strip is arc; The exhibition of this edge strip exhibition of wing flap in length l and the aircraft is identical to length L, and the width at described edge strip two ends is 20～30% of edge strip maximum width D; The edge strip exhibition is the wideest to the width at length direction plane of symmetry place, for edge strip is opened up to 0.5% of length l; Be connected with spline method is smooth between the two ends of edge strip arc trailing edge and described edge strip the widest part; The thickness of described edge strip and aircraft main wing trailing edge cooperation place is identical with the thickness of this aircraft main wing trailing edge, and the profile of the upper surface of described edge strip and lower surface all the profile with the aircraft main wing that cooperates is identical.
3. a kind of aircraft main wing trailing edge edge strip according to claim 1, it is characterized in that, the side surface of the side surface of described edge strip leading edge and aircraft main wing trailing edge is bonding, and the upper surface smooth transition of the upper surface of edge strip and aircraft main wing, the lower surface smooth transition of the lower surface of described edge strip and aircraft main wing is so that air-flow can flow through edge strip smooth-goingly; When interior wing flap was packed up, the lower surface of edge strip and the upper surface of interior wing flap were fitted.
4. method of designing of aircraft main wing trailing edge edge strip according to claim 1 is characterized in that detailed process is:
Step 1 is determined the lift of aircraft; The method for numerical simulation of average Navier-Stokes equation is found the solution in utilization, calculates flying speed V=68m/s, the aircraft flow field in a=0 °～20 ° scopes of the incoming flow angle of attack; Utilize formula (1) to obtain airplane ascensional force coefficient Cl under each angle of attack;
Cl=(F
y*cosa-F
x*sina)/(0.5*ρ*V
2*S)； （1）
Wherein: F
yBe that the total aerodynamic force of full machine is at the component of y direction; F
xBe that the total aerodynamic force of full machine is at the component of x direction; A is the incoming flow angle of attack; ρ is density of air; V is the flying speed of aircraft; S is the reference area of aircraft;
Step 2 determines that the scope of separation takes place trailing edge flap and the pressure coefficient of trailing edge flap distributes; Determine a=8 ° of the incoming flow angle of attack, at the interior flap surface surperficial limiting streamline that draws; The defiber of wing flap in the meld line of surface limiting streamline is; In the distance the shortest position of defiber to interior wing flap leading edge, the exhibition of wing flap is to section in doing, and the intersection of section and interior wing flap is this exhibition to the interior wing flap profile of position; (x y), obtains the graph of a relation of pressure coefficient Cp and profile abscissa x to take out pressure coefficient Cp on this profile and the geometric coordinate of profile; Pressure coefficient Cp is defined as:
Cp=（Pressure-Preference)/(0.5*ρ*V
2)； （2）
Wherein: Pressure is the pressure of exhibition on each coordinate points of wing flap profile at section place; Preference is reference pressure, gets standard atmosphere;
Step 3 determines that the exhibition of edge strip is to length; Wing flap defiber in obtaining according to step 2, described in the wing flap defiber along exhibition to the start-stop scope in, according to edge strip along exhibition to the start-stop position and interior wing flap defiber along open up to the principle of start-stop position consistency, determine that the exhibition of edge strip is to length;
Step 4 is determined the span of edge strip maximum width; The exhibition of the weakness of interior wing flap defiber and interior wing flap leading edge distance is defined as the position of edge strip maximum width D to the position;
Step 5 is determined the width at edge strip two ends; The width at described edge strip two ends is 20～30% of edge strip maximum width D; Step 6 is checked edge strip to the influence of airplane ascensional force; The maximum width D=D of described edge strip
MaxThe maximum width D of the edge strip of determining according to step 4 and step 54 and the width at edge strip 4 two ends construct edge strip by spline method, and edge strip are attached to the main wing trailing edge place of aircraft; The method for numerical simulation of average Navier-Stokes equation is found the solution in utilization, calculates flying speed V=68m/s, and the aircraft flow field in a=0 °～20 ° scopes of the incoming flow angle of attack utilizes formula (1) to obtain lift coefficient Cl under each angle of attack;
As edge strip maximum width D=D
Max, and a=0 °～20 ° of the incoming flow angles of attack, if airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip maximum width D meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, then edge strip maximum width D does not satisfy pneumatic requirement, need reduce the maximum width D of edge strip, proceeds edge strip design, enters step 7;
Step 7 is determined the goal pressure coefficient; Pressure coefficient in the interior wing flap profile that is obtained by step 2
Minimum value Cp
Min1Add an increment △, obtain new pressure coefficient minimum value Cp
Min2Cp
Min2Be the goal pressure coefficient;
Step 8, the maximum width of adjustment edge strip; The adjustment amount of edge strip maximum width D is designated as △ D; The span of △ D is [0, D
Max]; The width at edge strip two ends still is taken as 20～30% of edge strip maximum width D; Through the edge strip maximum width D=D after adjusting
Max-△ D; Utilize spline method to obtain to have adjusted the edge strip behind the maximum width, and it is attached to the main wing trailing edge of aircraft; The method for numerical simulation of average Navier-Stokes equation is found the solution in utilization, calculates flying speed V=68m/s, the aircraft flow field that the incoming flow angle of attack is a=8 °; Utilize the method identical with step 2, obtain the exhibition of edge strip maximum width D place to the pressure coefficient minimum value Cp of the interior wing flap profile of position
Min_ △ DThe difference △ Cp=Cp of itself and goal pressure coefficient
Min2-Cp
Min_ △ D
Step 9 is determined the edge strip maximum width of goal pressure coefficient correspondence; According to the size of the △ Cp that is obtained by step 8, utilize formula (3) to determine the new value of the adjustment amount △ D of edge strip maximum width D; Then, △ Cp process is found the solution and is obtained in the structure edge strip of repeating step 8, flow field, until | △ Cp
I+1/ Cp
Min2|≤0.05;
Formula (3) is:
△D
i+1=△D
i/(1-k*△Cp
i/D
max)； （3）
Wherein: △ D
iIt is the adjustment amount of the i time edge strip maximum width; △ D
I+1It is the adjustment amount of the i+1 time edge strip maximum width; △ Cp
iBe goal pressure coefficient Cp
Min2The interior wing flap profile pressure coefficient minimum value Cp corresponding with the i time edge strip maximum width adjustment amount
Min_ △ DiDifference; D
MaxThe upper limit for the maximum width of the edge strip determined by structural constraint; K is relaxation factor, is used for control adjustment amount △ D
I+1Size; Described i is the adjustment number of times of edge strip maximum width; After the i+1 time adjustment, following relational expression is arranged:
△Cp
i+1=Cp
min2-Cp
min_△Di+1； （4）
In the formula (4): Cp
Min_ △ Di+1It is the interior wing flap profile pressure coefficient minimum value of adjustment amount correspondence of the i+1 time edge strip maximum width; △ Cp
I+1Difference for the goal pressure coefficient interior wing flap profile pressure coefficient minimum value corresponding with the adjustment amount of the i+1 time edge strip maximum width;
When | △ Cp
I+1/ Cp
Min2|≤0.05 o'clock, finish to adjust, enter step 10;
Step 10 is checked edge strip to the influence of airplane ascensional force; The method for numerical simulation of average Navier-Stokes equation is found the solution in utilization, calculates flying speed V=68m/s, the aircraft flow field in a=0 °～20 ° scopes of the incoming flow angle of attack; Utilize formula (1), obtain each angle of attack lift coefficient Cl that gets off the plane; If airplane ascensional force coefficient maxim Cl
Max〉=install edge strip additional before, then edge strip maximum width D meets design requirement, and finishes the edge strip design; If airplane ascensional force coefficient maxim Cl
Max＜install edge strip additional before, goal pressure Cp is described
Min2Unreasonable, increment △ value is bigger than normal, and increment △ is adjusted to 90% of former increment, reenters step 7 then, proceeds the design of edge strip; The pressure coefficient minimum value Cp that described increment △ is interior wing flap profile
Min1Increment.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310234573.6A CN103332288B (en) | 2013-06-13 | 2013-06-13 | Edge strip at trailing edge of airplane and design method thereof |
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|---|---|---|---|
| CN201310234573.6A CN103332288B (en) | 2013-06-13 | 2013-06-13 | Edge strip at trailing edge of airplane and design method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN103332288A true CN103332288A (en) | 2013-10-02 |
| CN103332288B CN103332288B (en) | 2015-05-27 |
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| CN105109669A (en) * | 2014-12-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Aircraft recovery spin improving device |
| CN109328163A (en) * | 2016-06-29 | 2019-02-12 | 庞巴迪公司 | For the method and system of adjacent trailing edge flap to be unfolded |
| CN110239733A (en) * | 2019-05-29 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | A kind of aircraft yaw, when breakking away wing flap adjustment amount calculation method |
| CN110239737A (en) * | 2019-05-29 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | The calculation method of wing flap adjustment amount when multiple whirlpool paddle aircraft yaw, sideslip |
| CN112093029A (en) * | 2019-06-18 | 2020-12-18 | 成都飞机工业（集团）有限责任公司 | Aircraft airfoil trailing edge |
| CN113420379A (en) * | 2021-06-29 | 2021-09-21 | 西北工业大学 | Method for extracting surface-average pressure distribution from CFL3D calculation result |
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| CN110239733A (en) * | 2019-05-29 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | A kind of aircraft yaw, when breakking away wing flap adjustment amount calculation method |
| CN110239737A (en) * | 2019-05-29 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | The calculation method of wing flap adjustment amount when multiple whirlpool paddle aircraft yaw, sideslip |
| CN110239737B (en) * | 2019-05-29 | 2022-08-23 | 陕西飞机工业（集团）有限公司 | Method for calculating flap adjustment amount of multi-engine turboprop aircraft during yawing and sideslip |
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| CN113420379A (en) * | 2021-06-29 | 2021-09-21 | 西北工业大学 | Method for extracting surface-average pressure distribution from CFL3D calculation result |
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