CN112623254B - Hybrid laminar flow wing air suction energy loss engineering calculation method - Google Patents

Hybrid laminar flow wing air suction energy loss engineering calculation method Download PDF

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CN112623254B
CN112623254B CN202011556262.8A CN202011556262A CN112623254B CN 112623254 B CN112623254 B CN 112623254B CN 202011556262 A CN202011556262 A CN 202011556262A CN 112623254 B CN112623254 B CN 112623254B
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张声伟
张健
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AVIC First Aircraft Institute
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
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Abstract

The invention discloses a hybrid laminar flow wing inspiration energy loss engineering calculation method, which respectively fits a Rake fender number REN and a lift coefficient C according to CFD calculation data, wind tunnel test data and flight test data analysisLThe energy loss factor calculation function of the wing air suction device with the wing leading edge sweepback angle lambdaw and cruise Mach number as independent variables; using the position of upper and lower wing layer circulation crime obtained by X21 flight test as reference, and considering the air suction eNThe method for calculating the transition position of the laminar flow of the wing boundary layer calculates the energy loss factor generated by the airfoil quality, and finally obtains the energy loss factor of the wing air suction device of the whole aircraft by summing the area integrals of the energy loss factors of the wing sections in the spanwise direction. The method is suitable for power requirement demonstration of a mixed laminar flow wing leading edge air suction device with a complex configuration and air suction system pipeline design based on power distribution optimization, and provides technical support for thrust-weight ratio design and wing configuration optimization design of an airplane with a mixed laminar flow control technology.

Description

Hybrid laminar flow wing air suction energy loss engineering calculation method
Technical Field
The invention belongs to the technical field of aviation aircraft design, relates to a method for calculating wing air suction energy loss of a transport plane, and particularly relates to a method for calculating mixed laminar flow wing air suction energy loss engineering.
Background
The natural laminar flow technology has strict requirements on flight environment and wing configuration, and is only suitable for small airplanes with the speed not higher than 0.7 Ma; the air suction device of the full laminar flow control technology is complex and has large energy loss; the mixed layer flow control technology has small air suction energy consumption and obvious resistance reduction effect, and is one of the resistance reduction technologies with the best application prospect. The energy loss of the wing air suction device is sensitive to the influence of the performance of the airplane, so that the accurate calculation of the energy loss is a key technology for evaluating the performance of the mixed layer flow control wing. At present, most of energy loss data of mixed laminar flow wing airplanes come from flight test data, and due to the lack of an air suction energy loss calculation method, performance index design, thrust-weight ratio design and wing airfoil and plane parameter optimization design of the airplane adopting a mixed laminar flow control technology cannot be developed.
Disclosure of Invention
In order to solve the problems, the invention provides a mixed laminar flow wing air suction energy loss engineering calculation method, which is used for calculating the energy loss of an air suction device at the front edge of a wing of an airplane adopting a mixed layer flow control technology and providing technical support for the thrust-weight ratio design, the wing configuration optimization design and the air suction device design of the airplane adopting the mixed layer flow control technology.
The technical scheme of the invention is as follows:
a hybrid laminar flow wing inspiration energy loss engineering calculation method is characterized in that a radar curve number REN and a lift coefficient C are respectively fitted according to CFD calculation data, wind tunnel test data and flight test data analysisLThe energy loss factor calculation function of the wing air suction device with the wing leading edge sweepback angle lambdaw and cruise Mach number as independent variables; using the position of upper and lower wing layer circulation crime obtained by X21 flight test as reference, and considering the air suction eNThe method for calculating the transition position of the laminar flow of the wing boundary layer calculates the energy loss factor generated by the mass of the wing profile, and finally obtains the energy loss factor of the wing air suction device of the whole airplane by summing the area integrals of the energy loss factors of the wing sections in the span direction.
Further, the method specifically comprises the steps of wing spanwise wing section division, reynolds number energy loss factor Kr calculation, design lift coefficient energy loss factor Kw calculation, sweepback angle energy loss factor Kj calculation, speed energy loss factor Kv calculation, airfoil energy loss factor Ka calculation and whole-engine air suction device energy loss factor Kz calculation.
Further, the wing span-wise wing segment is divided into: dividing the extension direction of the wing into n sections according to the difference of the influence sensitive parameters of the layer flow crime, and giving the wing area S of each section of the wingiMean aerodynamic chord length CiWing leading edge sweep angle ΛiSum wing equivalent design lift coefficient CLi。
Further, the method for calculating the wing Reynolds number energy loss factor Kr specifically comprises the following steps:
the method comprises the following steps of (1) calculating a wing Reynolds number energy loss factor:
Figure BDA0002856903250000021
Kr＝0，reni＜1
wherein S isWIs the total area of the wing;
firstly, calculating Reynolds numbers ren of all the wings according to the cruise performance data of the airplane and the data input of all the span-direction wing sections of the wingsiHas a unit of 107And then calculating the wing Reynolds number energy loss factor Kr of the whole computer according to the calculation model.
Further, the method for calculating the energy loss factor Kw of the wing design lift coefficient specifically comprises the following steps:
designing a model for calculating an energy loss factor of a lift coefficient of a wing:
Figure BDA0002856903250000022
Kw＝0，CLi＜0.28
designing lift coefficient C according to airfoil profile of each section of wingLiThe equivalent wing profile design lift coefficient is calculated through the torsion angle and the installation angle, and then the design lift coefficient energy loss factor Kw of the wing is calculated according to the calculation model.
Further, the method for calculating the wing sweepback angle energy loss factor Kj specifically comprises the following steps:
Figure BDA0002856903250000023
Kj＝0，Λi＜10°
and calculating the energy loss factor Kj of the leading edge sweepback angle of the wing according to the leading edge sweepback angle of each section of the wing and the calculation model.
Further, the method for calculating the wing airfoil energy loss factor Ka specifically comprises the following steps:
the wing airfoil energy loss factor calculation model is obtained by fitting based on X21 flight test data, and firstly, the e considering inspiration is adoptedNCalculating the transition position of the wing boundary layer laminar flow crime on each section of wing
Figure BDA0002856903250000031
The position of the boundary layer of the lower airfoil surface is crime
Figure BDA0002856903250000032
Calculating an energy loss factor generated by the airfoil mass of the whole machine according to a calculation model; the airfoil energy loss factor Ka is calculated as:
Figure BDA0002856903250000033
further, the method for calculating the energy loss factor Kv of the cruising speed specifically comprises the following steps:
because the speeds of all the sections of the wing are consistent, the Gu Jiyi cruise speed energy loss factor calculation model is as follows:
Figure BDA0002856903250000034
when the cruise Mach number Ma is less than 0.65, the wing speed energy loss factor is zero, and the speed is greater than 0.73Ma, the speed energy loss factor is increased rapidly.
Further, the method for calculating the energy loss factor Kz of the whole air suction device specifically comprises the following steps:
the energy loss factor calculation model of the whole machine air suction device is as follows:
Kz＝Kr+Kw+Kj+Ka+Kv。
the invention has the advantages that:
the calculation model provided by the invention is fine and comprehensive, and the influence of the sensitive factors of the main mixed layer circulation crime is considered. The wing air suction energy loss factor is calculated and decomposed into five components of a Reynolds number energy loss factor Kr, a design lift coefficient energy loss factor Kw, a wing sweep angle energy loss factor Kj, a speed energy loss factor Kv and a wing energy loss factor Ka, and a corresponding engineering calculation model is established by adopting a fitting technology according to CFD calculation data, wind tunnel test data and flight test data. In order to meet the calculation accuracy of the inspiratory energy loss factor of the wing with the complex configuration, a numerical algorithm that the wing span direction is segmented and the energy loss factor component is integrated section by section is adopted.
The calculation method provided by the invention is suitable for power requirement demonstration of a mixed laminar flow wing leading edge air suction device with a complex configuration and air suction system pipeline design based on power distribution optimization. The method provides technical support for the thrust-weight ratio design and wing configuration optimization design of the airplane adopting the mixed layer flow control technology.
Drawings
FIG. 1 is a flow chart of a method for calculating the inspiratory energy loss of a hybrid laminar flow airfoil in accordance with the present invention;
FIG. 2 is an exploded view of a hybrid laminar flow machine spanwise panel according to an embodiment of the present invention;
FIG. 3 is a schematic view of the main configuration parameters of each section of the wing according to the embodiment of the invention;
FIG. 4 is a graph of 4 energy loss factor calculations for each section of an airfoil in accordance with an embodiment of the present invention.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A hybrid laminar flow wing air suction energy loss engineering calculation method comprises the steps of respectively fitting an energy loss factor engineering calculation function of a wing air suction device with a radar number REN, a lift coefficient CL, a wing leading edge sweepback angle lambaw and a cruise Mach number as independent variables according to CFD calculation data, wind tunnel test data and flight test data analysis; calculating energy loss factors generated by the quality of wing profiles by taking the positions of upper and lower wing layer flows crime obtained by an X21 flight test as reference and using an enwing boundary layer flow transition position calculation method considering air suction, and finally obtaining the energy loss factors of the wing suction device of the whole aircraft by summing the area integrals of the energy loss factors of wing spanwise wing sections; the method specifically comprises the steps of wing span division, reynolds number energy loss factor Kr calculation, design lift coefficient energy loss factor Kw calculation, sweepback angle energy loss factor Kj calculation, speed energy loss factor Kv calculation, wing energy loss factor Ka calculation and whole-aircraft air suction device energy loss factor Kz calculation.
1. The wing span-wise wing panel is divided into the following specific steps: for complex configurationsThe corresponding energy loss factor of the wing can not be accurately calculated by only using a single Reynolds number, the wing profile, the design lift coefficient and the sweepback angle of the wing leading edge. Therefore, before calculating each energy loss factor, the wing extension direction is divided into n sections according to the difference of influence sensitive parameters of layer flow crime, and the wing area S of each section of wing is giveniMean aerodynamic chord length CiWing leading edge sweep angle ΛiSum wing equivalent design lift coefficient CLi。
The method for calculating the wing Reynolds number energy loss factor Kr specifically comprises the following steps:
2. the method comprises the following steps of (1) calculating a wing Reynolds number energy loss factor:
Figure BDA0002856903250000041
Kr＝0，reni＜1
wherein S isWIs the total area of the wing;
firstly, calculating Reynolds numbers ren of all the wings according to the cruise performance data of the airplane and the data input of all the span-direction wing sections of the wingsiHas a unit of 107And then calculating the wing Reynolds number energy loss factor Kr of the whole computer according to the calculation model.
3. The method for calculating the energy loss factor Kw of the wing design lift coefficient specifically comprises the following steps:
designing a model for calculating an energy loss factor of a lift coefficient of a wing:
Figure BDA0002856903250000051
Kw＝0，CLi＜0.28
the wing attack angle or wing profile design lift coefficient has obvious influence on the layer-by-layer rotation crime position of the wing boundary, and in order to improve the pitching moment characteristic of the airplane and avoid the wing tip stall of the wing, a pneumatic torsion angle or a geometric torsion technology is adopted, so that the difference of the used attack angles of all sections of the wing is large, and the difference is determined according to all the sections of the wingWing profile design lift coefficient C of section wingLiCalculating equivalent wing profile design lift coefficient by the torsion angle and the installation angle, and calculating the design lift coefficient energy loss factor Kw of the wing according to the calculation model.
4. The method for calculating the sweep angle energy loss factor Kj of the wing specifically comprises the following steps:
Figure BDA0002856903250000052
Kj＝0，Λi＜10°
the influence of the wing leading edge sweepback angle on the wing energy loss is obvious, and the leading edge sweepback angle energy loss factor Kj of the wing is calculated according to the leading edge sweepback angle of each section of the wing and a calculation model.
5. The method for calculating the wing airfoil energy loss factor Ka specifically comprises the following steps:
the wing airfoil energy loss factor calculation model is obtained by fitting based on X21 flight test data, and firstly, the e considering inspiration is adoptedNCalculating the transition position of the wing boundary layer laminar flow crime on each section of wing
Figure BDA0002856903250000053
The position of the boundary layer of the lower airfoil surface is crime
Figure BDA0002856903250000054
Calculating an energy loss factor generated by the airfoil mass of the whole machine according to a calculation model; the airfoil energy loss factor Ka is calculated as:
Figure BDA0002856903250000055
6. the method for calculating the energy loss factor Kv of the cruising speed comprises the following specific steps:
because the speeds of all the sections of the wing are consistent, the Gu Jiyi cruise speed energy loss factor calculation model is as follows:
Figure BDA0002856903250000061
the calculation model shows that: when the cruise Mach number Ma is less than 0.65, the wing speed energy loss factor is zero, and the speed is greater than 0.73Ma, the speed energy loss factor is increased rapidly.
7. Calculating the energy loss factor Kz of whole-machine air suction device
The energy loss factor calculation model of the whole air suction device is as follows:
Kz＝Kr+Kw+Kj+Ka+Kv
and (3) inputting 5 wing energy loss factor components obtained by calculation in the first 6 steps according to the whole-aircraft air suction device energy loss factor calculation model, and calculating the whole-aircraft air suction device energy loss factor Kz.
Another embodiment of the present invention is described below with reference to the drawings.
The method flow of the invention is shown in figure 1, and the method respectively fits the Radar fender number REN and the lift coefficient C according to CFD calculation data, wind tunnel test data and flight test data analysisLWing leading edge sweep angle ΛWAn energy loss factor engineering calculation function of the wing air suction device taking the cruise Mach number as an independent variable; using the position of upper and lower wing layer circulation crime obtained by X21 flight test as reference, and considering the air suction eNThe method for calculating the transition position of the laminar flow of the wing boundary layer calculates the energy loss factor generated by the mass of the wing profile, and finally obtains the energy loss factor of the wing air suction device of the whole airplane by summing the area integrals of the energy loss factors of the wing sections in the span direction. The design method of the mixed laminar flow wing air suction energy loss engineering provided by the invention has a fine energy loss factor calculation model, and is suitable for calculating the energy loss of conventional and complex-configuration wings. The calculation method provided by the invention is suitable for power requirement demonstration of a mixed laminar flow wing leading edge air suction device with a complex configuration and air suction system pipeline design based on power distribution optimization.
Taking an airplane as an example, the airplane is a large-scale transport airplane with a wing body combination configuration by adopting a mixed laminar flow control technology, the wing control section is a supercritical mixed laminar flow airfoil profile, and the main performance indexes of the transport airplane are as follows: cruising speed: 0.78Ma, cruise altitude 12000m.
Step 1, the section of the wing is shown in the attached figure 2, and the main configuration parameters of each section of the wing are shown in the figure 3.
Step 2, calculating an energy loss factor Kxz of the wing:
calculating 4 energy loss factor calculation data of each section of the wing except the wing speed energy loss factor according to the calculation method flow and the calculation model shown in figure 4;
from the calculated data in fig. 4, kxz =0.1172 of the full wing is known.
And 3, calculating a wing speed energy loss factor Kv:
cruise speed 0.78Ma, wing speed energy loss factor calculation is 0.0319.
Kv＝0.5{(0.78-0.65)/0.6}1.8＝0.0319
Step 4, calculating the air suction energy loss factor of the whole aircraft wing
KZ＝KXZ+KV＝0.149
The calculation data shows that: as the cruising speed of the airplane is high, the sweepback angle of the front edges of the wings W1 and W2 at the inner side 2 sections is large, the air suction energy loss of the whole airplane wing is large, and the thrust-weight ratio of the airplane needs to be increased by 14.9 percent.

Claims (1)

1. The hybrid laminar flow wing air suction energy loss engineering calculation method is characterized in that Reynolds number REN and lift coefficient C are respectively fitted according to CFD calculation data, wind tunnel test data and flight test data analysisLThe energy loss factor calculation function of the wing air suction device takes an inverted V-w value of the front edge sweepback angle of the wing and the cruise Mach number as independent variables; taking the transition position of the laminar flows of the upper wing and the lower wing obtained by the X21 flight test as reference, using the e considering the air suctionNThe method for calculating the transition position of the laminar flow of the wing boundary layer calculates energy loss factors generated by the mass of wing profiles, and finally obtains the energy loss factors of the wing air suction device of the whole airplane by summing the area integrals of the energy loss factors of the wing sections in the span direction;
the method specifically comprises the steps of wing spanwise wing section division, reynolds number energy loss factor Kr calculation, design lift coefficient energy loss factor Kw calculation, sweepback angle energy loss factor Kj calculation, speed energy loss factor Kv calculation, wing energy loss factor Ka calculation and whole-aircraft air suction device energy loss factor Kz calculation;
the wing span-wise wing panel is divided into the following specific steps: according to the difference of sensitive parameters influenced by layer flow transition, the wing extension direction is divided into n sections, and the wing area S of each section of wing is giveniMean aerodynamic chord length CiSweepback angle of wing leading edgeiSum wing equivalent design lift coefficient CLi；
The method for calculating the wing Reynolds number energy loss factor Kr specifically comprises the following steps:
the method comprises the following steps of (1) calculating a wing Reynolds number energy loss factor:
Figure FDA0003808014370000011
Kr＝0，reni＜1
wherein S iswIs the total area of the wing;
firstly, calculating Reynolds numbers ren of all the wings according to the cruise performance data of the airplane and the data input of all the span-direction wing sections of the wingsiHas a unit of 107Then, calculating the wing Reynolds number energy loss factor Kr of the whole computer according to the calculation model;
the method for calculating the energy loss factor Kw of the wing design lift coefficient specifically comprises the following steps:
designing a model for calculating an energy loss factor of a lift coefficient of a wing:
Figure FDA0003808014370000012
Kw＝0，CLi＜0.28
designing lift coefficient C according to airfoil profile of each section of wingLiCalculating equivalent airfoil profile design lift coefficient according to the torsion angle and the installation angle, and calculating according to a calculation modelCalculating the design lift coefficient energy loss factor Kw of the wing;
the method for calculating the sweep angle energy loss factor Kj of the wing specifically comprises the following steps:
Figure FDA0003808014370000013
Kj＝0,Λi＜10°
calculating the energy loss factor Kj of the leading edge sweepback angle of each section of wing according to the leading edge sweepback angle and the calculation model;
the method for calculating the wing airfoil energy loss factor Ka specifically comprises the following steps:
the wing airfoil energy loss factor calculation model is obtained by fitting based on X21 flight test data, and firstly, the e considering inspiration is adoptedNCalculating the transition position of an upper airfoil surface boundary layer and the transition position of a lower airfoil surface boundary layer of each section of the wing by using a wing boundary layer transition position calculation method, and calculating an energy loss factor generated by the wing profile quality of the whole computer according to a calculation model; the airfoil energy loss factor Ka is calculated as:
Figure FDA0003808014370000021
the method for calculating the energy loss factor Kv of the cruising speed comprises the following specific steps:
because the speeds of all the sections of the wing are consistent, the calculation model of the energy loss factor of the cruising speed of the wing is as follows:
Figure FDA0003808014370000022
when the cruise Mach number Ma is less than 0.65, the wing speed energy loss factor is zero, the speed is greater than 0.73Ma, and the speed energy loss factor is rapidly increased;
the method for calculating the energy loss factor Kz of the whole air suction device comprises the following steps:
the energy loss factor calculation model of the whole air suction device is as follows:
Kz＝Kr+Kw+Kj+Ka+Kv。
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