CN118067351B - Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine - Google Patents
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Abstract
The invention discloses a wind tunnel test method for resistance characteristics of a nacelle of a civil aircraft engine, which relates to the field of wind tunnel tests and comprises the following steps: s1, simulating the air inlet state of a nacelle by directly ventilating the nacelle based on incoming flow simulation conditions provided by a wind tunnel; s2, regulating the inlet air flow of the nacelle so as to obtain the total static pressure I of the local section through a pressure measuring rake I arranged at the outlet of the nacelle, and obtaining the total static pressure II of the local section through a pressure measuring rake II arranged in the middle of the equal straight section; s3, obtaining the internal resistance D in and the aerodynamic resistance D MF of the nacelle through a momentum integration mode; s4, correcting the D in、DMF, and calculating to obtain the corresponding nacelle cover resistance D cowl. The wind tunnel test method for the resistance characteristics of the nacelle of the civil aircraft engine can conveniently and accurately measure the resistance characteristics of the aircraft engine under different flow conditions, and the balance force measurement interference problem caused by contact or blowby of the straight sections such as the isolation and the like at the outlet is also eliminated by adopting the method.
Description
Technical Field
The invention relates to the field of wind tunnel tests. More particularly, the invention relates to a wind tunnel test method for resistance characteristics of a nacelle of a civil aircraft engine.
Background
The nacelle has the function of providing the engine with air flow matched with the working state of the engine, and is required to ensure that the engine cannot suck lip separation air flow and simultaneously reduce plane flying resistance as much as possible. The design level has important influence on the flight safety and economy. The resistance of the nacelle affects the propulsion efficiency, fuel consumption, economy and other factors of the engine. In recent years, researches on drag reduction aerodynamic layout, drag reduction method and the like have been paid attention to improvement of aerodynamics and economy of an airplane. As one of the key components of the engine, the nacelle affects not only the aerodynamic layout of the whole machine, but also has an important impact on the drag characteristics of the whole machine. Therefore, in order to ensure the safety of the flight, it is necessary to develop an engine resistance test study.
With the rapid development of aeronautical technology, the need to evaluate the performances of the aircraft and the engines more precisely, and in particular the problem of matching between nacelle and engine, is a critical technology related to the aerodynamic and dynamic performances of the aircraft. As a main drag component of an aircraft, it is extremely necessary to conduct accurate simulation studies of aerodynamic drag thereon. In practice, it has been found that when the working state of the engine is changed, i.e. the intake flow is changed by adjusting the shutter, the aerodynamic resistance of the nacelle is significantly changed, especially in the transsupersonic phase.
In aircraft aerodynamics, aircraft engines are typically reduced to ventilated cabins, with resistance predictions made by wall area. The flow of the air inlet channel and the flow of the spray pipe of the real aircraft engine are adjustable, and the resistance value of the real aircraft engine is obviously different from the total resistance value of the aircraft cabin with ventilation. When the aircraft is in normal cruising flight, the flow coefficient of the aircraft varies approximately from 0.6 to 2.0 along with the difference of Mach numbers. Within this range, the flow coefficient change has less impact on aircraft/engine drag. However, when the flow coefficient of the aircraft is far from the cruising point and the flow coefficient is sharply reduced, the resistance of the air inlet channel is sharply increased, so that the total resistance of the aircraft is sharply increased, and particularly, when the engine is in a windmill state, the overflow resistance of the windmill is sharply increased. This phenomenon is particularly pronounced for transonic large aircraft with large bypass ratio engines. In the prior art, a balance is often adopted to obtain the nacelle resistance, but the method has the problems of measurement errors and unavoidable interference, so that the resistance characteristics of the aviation turbofan nacelle under the condition of different flow coefficients can not be accurately measured in a wind tunnel test.
Disclosure of Invention
It is an object of the present invention to address at least the above problems and/or disadvantages and to provide at least the advantages described below.
To achieve these objects and other advantages and in accordance with the purpose of the invention, a method for wind tunnel test of resistance characteristics of a nacelle of a civil aircraft engine is provided, comprising:
s1, simulating the air inlet state of a nacelle by directly ventilating the nacelle based on incoming flow simulation conditions provided by a wind tunnel;
S2, regulating the inlet air flow of the nacelle so as to obtain the total static pressure I of the local section through a pressure measuring rake I arranged at the outlet of the nacelle, and obtaining the total static pressure II of the local section through a pressure measuring rake II arranged in the middle of the equal straight section;
S3, acquiring internal resistance D in and aerodynamic resistance D MF of the nacelle through a momentum integration mode based on the total section static pressure I and the total section static pressure II obtained in the step S2;
S4, correcting the D in、DMF obtained in the step S3, and calculating to obtain the corresponding outer cover resistance D cowl.
Preferably, in S2, the adjustment manner of the air intake flow of the nacelle is:
the forward and backward movement position of the flow control cone on the nacelle resistance characteristic test device is adjusted, so that the air inlet flow of the nacelle is changed.
Preferably, the nacelle resistance characteristic test apparatus includes:
The front end of the support rod is provided with a rectifying cone;
the nacelle is arranged at the front section of the support rod through the support piece;
The isolation equal straight sections are arranged on the supporting rods through a plurality of brackets and are adjacently arranged with the rear end of the nacelle;
The pressure measuring harrow I is arranged at the front end of the straight section of the isolation and the like to measure the internal resistance of the nacelle;
The pressure measuring harrow II is arranged on the outer ring of the middle part of the straight section of the isolation and the like so as to measure the external resistance of the nacelle;
the inner side wall of the rear end of the isolation equal-straight section is provided with a conical surface, the supporting rod is provided with a cone matched with the conical surface, and the cone is arranged on the supporting rod through a driving mechanism;
the nacelle is in radial sealing connection with the isolated straight section through the sealing ring 1, and the nacelle is not in contact with the axial end face of the isolated straight section.
Preferably, a nacelle lining extending from the maximum through-flow section to the tail end face of the nacelle is arranged in the nacelle;
and the end face of the tail step of the nacelle lining is respectively provided with an outer pressure measuring point and an inner pressure measuring point.
Preferably, in S3, the internal resistance D in is obtained by:
S310, dividing an outlet section into a plurality of areas based on a total pressure detection tube distribution mode in the pressure measuring rake I, wherein each area corresponds to an area where an outlet area A e is located and comprises 11 total pressure measuring points P 0e and 1 static pressure measuring point P e;
S311, calculating a corresponding outlet Mach number M e based on P 0e、Pe;
S312, calculating the corresponding flow tube flow M e based on M e obtained in S311:
in the above formula, (M e) represents a flow function, and T 0 is the total temperature;
S313, based on m e obtained in the step S312, calculating a corresponding internal resistance D in according to the following formula:
In the above-mentioned method, the step of, The incoming flow rate is indicated by the velocity of the incoming flow,Representing the nacelle angle of attack, V e represents the nacelle exit velocity,Representing the incoming static pressure.
Preferably, in S311, when P e/P0e is ≡1, M e =0;
When 0.528< p e/P0e <1, ；
When P e/P0e <0.528, M e is solved by:
。
Preferably, in S3, the nacelle aerodynamic drag D MF is obtained by:
S320, dividing the outlet section into a plurality of areas based on a total pressure detection tube distribution mode in the pressure measuring rake II, wherein each area corresponds to an area where the outlet area A j is located and comprises 18 total pressure measuring points P 0j and 2 static pressure measuring points P j;
S321, integrating the wake harrow pressure data of different bus sections on the outer surface of the nacelle to obtain aerodynamic drag D MF of the nacelle:
In the above equation, father D MF represents the resistance correction term, D(s) represents the area integration region along the peripheral rake sector, and D MFj represents the wake resistance factor.
Preferably, in S4, the nacelle cover resistance D cowl is obtained by: the nacelle aerodynamic drag D MF and the nacelle internal resistance D in are obtained through momentum integration, and are corrected, and the nacelle aerodynamic drag D MF is the sum of the nacelle internal resistance D in and the nacelle cover resistance D cowl, so that the nacelle cover resistance D cowl is calculated.
The invention at least comprises the following beneficial effects: according to the invention, aerodynamic force measurement is not required in the whole test process, the internal resistance and the external resistance of the nacelle are measured by the pressure measuring harrow to measure the local total pressure and the static pressure, and the local total pressure and the static pressure are obtained by momentum integration, so that the resistance characteristics of the aeroengine under different flow conditions can be conveniently and accurately measured.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a schematic diagram of a nacelle drag characteristic test apparatus of the present invention;
FIG. 2 is a schematic diagram of the structure of the internal resistance measurement in the nacelle resistance characteristic test apparatus of the present invention;
FIG. 3 is an enlarged schematic view of the structure shown at I in FIG. 2;
FIG. 4 is a schematic view of the flow control structure in the nacelle resistance characteristic test apparatus of the present invention;
FIG. 5 is a schematic diagram of an internal flow pressure rake I of the present invention;
Fig. 6 is a schematic diagram of an outflow pressure measuring rake ii according to the present invention.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description.
The invention provides a wind tunnel test device for resistance characteristics of a civil aircraft engine nacelle, which can accurately measure the resistance characteristics of the aircraft turbofan engine nacelle under different flow coefficient conditions in a wind tunnel test, provides a reference for the overall design of an aircraft, and provides a certain technical support for the research of the nacelle-engine matching problem of a large aircraft.
The structure of the nacelle resistance characteristic test device provided by the invention is shown in figure 1, and the nacelle resistance characteristic test device comprises: the device comprises a nacelle 1, a nacelle support frame 2, an inner flow pressure measuring harrow I3, a straight section 4 for isolation and the like, an outer flow pressure measuring harrow II 5, a middle support 6, a flow control cone 7 and a support rod 8; the nacelle 1 is fixedly connected to the nacelle support frame 2; the nacelle supporting frame 2 is fixed at the front section of the supporting rod 8; the isolated straight section 4 is fixed on the supporting rod 8 through the middle support 6; the inner flow pressure measuring harrow I3 is positioned at the front end of the isolated equal straight section 4; the outflow pressure measuring harrow II 5 is fixedly connected to the outer ring of the isolation equal straight section 4 and is positioned at the middle section of the isolation equal straight section 4; the flow control cone 7 is arranged at the rear section of the supporting rod 8; the flow control cone 7 can be moved back and forth by electric control to change the intake flow of the nacelle 1.
As shown in fig. 2 to 3, the nacelle resistance characteristic test apparatus of the present invention mainly includes: nacelle 1, nacelle support 2, inner flow pressure measuring rake I3, straight sections 4 such as isolation, middle support 6, support rod 8, rectifying cone 9, tension bolt 10, gasket 11, copper bush 12, bolt and locating pin 13, nacelle lining 14, wiring hole 15, pressure measuring tube 16, outer bottom resistance (also called end face outer side pressure measuring point) 17, sealing ring 18, inner bottom resistance (also called end face inner side pressure measuring point) 19; the nacelle 1 is fixed on the nacelle supporting frame 2 through bolts and positioning pins; the nacelle supporting frame 2 is connected to the front end of the supporting rod 8 through the tension bolt 10, the gasket 11 and the copper sleeve 12 with a taper of 1:5; the rectifying cone 9 is arranged at the forefront end of the supporting rod 8 and fixedly connected with the nacelle supporting frame 2; the nacelle liner 14 extends to the end face of the tail of the nacelle 1 in an equal straight way with the largest through-flow section inside the nacelle 1; the inner flow pressure measuring harrow I3 is positioned in the isolated straight section 4 and fixedly arranged on the supporting rod 8; the pressure measuring tube 16 extends into the tail end of the nacelle 1 to measure the total and static pressure of multiple points at the outlet section of the nacelle 1; the nacelle 1 is in radial sealing connection with the isolated equal-straight section 4 through the sealing ring 18, and the axial end face is not contacted; the end face of the tail step of the nacelle lining 14 is provided with the end face outer side pressure measuring point 17 and the end face inner side pressure measuring point 19 to serve as resistance correction references; the pressure measuring tube 16 is gathered into the wiring holes 15 in the support rod 8 together through the wiring grooves on the support.
As shown in fig. 4, the nacelle resistance characteristic test apparatus of the present invention is applied to a structure mainly including: isolation equal straight section 4, flow control cone 7, support rod 8, blocking cone full closing position 20, through flow section 21, blocking cone full opening position 22 and driving unit 23; the flow control cone 7 is sleeved at the tail section of the supporting rod 8; the tail sections of the isolated equal-straight sections 4 and the flow control cone 7 form a variable through-flow section 21, and the opening position of the blocking cone can be remotely controlled through the driving unit 23, so that the air inlet flow is changed; when the flow control cone 7 moves to the position of the full closing position 20 of the blocking cone, the through flow section 21 is equivalent to zero, and no air inflow exists in the nacelle 1; when the flow control cone 7 moves to the position of the full opening 22 of the blocking cone, the through-flow section 21 is equivalent to the maximum section area of the outlet of the tail section of the nacelle 1, and the air inlet flow in the nacelle 1 is maximum.
The invention provides an incoming flow simulation condition by a wind tunnel, an engine nacelle directly ventilates and simulates the air intake of the nacelle, the air intake flow of the nacelle is changed by isolating a flow control cone arranged on a support rod at the tail part of an equal straight section, the total static pressure of a local section is measured by an internal resistance measuring device arranged at the outlet of the nacelle, and the total static pressure of the local section is measured by an external resistance measuring device arranged at the middle part of the equal straight section and is used for calculating the resistance characteristic of the engine nacelle.
Different nacelle resistance definition methods are given below, and nacelle outer cover resistance D cowl, nacelle internal resistance D in and nacelle aerodynamic resistance D MF are defined; the nacelle cover resistance D cowl is the force directly applied to the nacelle outer surface, the internal resistance D in is the resultant force of the internal flow applied to the interior of the engine, and the demarcation point of the nacelle inner and outer surfaces is the stagnation point of the engine inlet and outlet free flow pipes.
Nacelle cover drag D cowl is closely related to nacelle aerodynamic profile and flow coefficient phi, while internal drag D in is determined by engine operating conditions. When the flow coefficient Φ is less than 1, the airflow through the nacelle exterior accelerates to decompress, and the nacelle exterior pressure is less than ambient pressure, so the nacelle cover resistance D cowl is less than 0 (i.e., equivalent to suction).
Through numerical simulation, the nacelle internal resistance D in and the nacelle cover resistance D cowl can be found by wall integration, but since the standing point position varies with the flow rate, it is difficult to accurately measure both forces individually in the test.
The invention discloses a wind tunnel test method for resistance characteristics of a nacelle of a civil aircraft engine, which comprises the steps of obtaining pressure data of an inner flow pressure measuring rake I and an outer flow pressure measuring rake II through a test, calculating aerodynamic resistance D MF of the nacelle and internal resistance D in of the nacelle through momentum integration, correcting the aerodynamic resistance D MF, wherein the aerodynamic resistance D MF of the nacelle is the sum of the internal resistance D in of the nacelle and the external resistance D cowl of the nacelle, and calculating external resistance D cowl of the nacelle.
1. Calculation method for internal resistance D in of pressure measuring harrow I
As shown in FIG. 5, in the measurement process adopting the internal flow pressure measuring harrow I, the two-quadrant measuring points and the four-quadrant measuring points are bilaterally symmetrical to one quadrant and the three quadrant during data processing. According to the numerical calculation result, the outlet section is divided into a plurality of flow pipes corresponding to the outlet area of each flow pipe according to the distribution mode of the total pressure detection pipe of the pressure measuring rake, the whole internal flow channel is divided into 8 areas, each area comprises 11 total pressure measuring points P 0e and 1 static pressure measuring point P e, and 6, 18, 30, 42, 54 and 66 are static pressure points. The flow and internal resistance in each flow tube can be calculated as follows:
The exit Mach number M e may be calculated from the total and static pressure measurements of the pressure rake. If the total air flow and the static pressure of the model outlet are directly measured by adopting a leather-tupe pressure measuring device, the following shock wave condition at the front end of the pressure detecting tube is considered:
When P e/P0e is greater than or equal to 1, M e =0;
When 0.528< p e/P0e <1, ；
When P e/P0e <0.528, M e is solved by:
Wherein, M e is flow of a flow pipe, D in is internal resistance of the flow pipe, M in is ideal flow, T 0 is total temperature, A in is capture area of an air inlet channel, A e is outlet area of a nacelle, phi is flow coefficient, q (M e) is flow function, gamma is specific heat ratio, In order for the incoming flow rate to be high,Is the nacelle angle of attack, V e is the nacelle exit velocity,For incoming static pressure, P 0 is the total incoming pressure,Is a flow function; it should be noted that n flow tubes are divided as corresponding measuring points during experimental design, each flow tube can calculate one m e through the measured data,Representing a summation operation performed on m e of the n stations.
2. Calculation method for pneumatic resistance D MF of outflow pressure-measuring harrow II nacelle
In the process of measuring by adopting the outflow pressure measuring rake II, the measuring points of the two quadrants and the four quadrants are bilaterally symmetrical to the two quadrants and the three quadrants during data processing as shown in fig. 6. According to the numerical calculation result, the outlet section is divided into a plurality of flow pipes corresponding to the outlet area of each flow pipe according to the distribution mode of the total pressure detection pipe of the pressure measuring rake, the whole internal flow channel is divided into 8 areas, each area comprises 18 total pressure measuring points P 0j and 2 static pressure measuring points P j, and 11, 19, 31, 39, 51, 59, 71, 79, 91 and 99 are static pressure points. The aerodynamic coefficient of the outer surface of the nacelle is obtained by integrating the wake harrow pressure data of different bus sections of the outer surface of the nacelle, and the main processing process is as follows:
wherein, P 0, The unit is Pa for total pressure and static pressure of incoming flow; p 0j、Pj is the total hydrostatic pressure of the wake calandria, and the unit is Pa; Δd MFjmax is the maximum value of Δd MFj in the wake region; is the dimensionless outer diameter of the tailstock total pressure tube relative to the nacelle reference length, father D MF is the resistance correction term, Δd MFj is the wake resistance factor, u j is the flow tube exit velocity, For incoming flow velocity, U is the flow tube outlet dimensionless velocity relative to the incoming flow velocity, M j is the flow tube outlet Mach number, and M ∞ is the incoming flow Mach number.
According to the invention, the pneumatic resistance of the nacelle is measured in a balance-free manner, so that the measurement manner is simplified, and the contradiction between the model and the equal straight section, which is required to be sealed and not to be transferred, during balance force measurement is effectively avoided.
The above is merely illustrative of a preferred embodiment, but is not limited thereto. In practicing the present invention, appropriate substitutions and/or modifications may be made according to the needs of the user.
Although embodiments of the invention have been disclosed above, they are not limited to the use listed in the specification and embodiments. It can be applied to various fields suitable for the present invention. Additional modifications will readily occur to those skilled in the art. Therefore, the invention is not to be limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (5)
1. A wind tunnel test method for resistance characteristics of a nacelle of a civil aircraft engine is characterized by comprising the following steps:
s1, simulating the air inlet state of a nacelle by directly ventilating the nacelle based on incoming flow simulation conditions provided by a wind tunnel;
S2, regulating the inlet air flow of the nacelle so as to obtain the total static pressure I of the local section through a pressure measuring rake I arranged at the outlet of the nacelle, and obtaining the total static pressure II of the local section through a pressure measuring rake II arranged in the middle of the equal straight section;
S3, acquiring internal resistance D in and aerodynamic resistance D MF of the nacelle through a momentum integration mode based on the total section static pressure I and the total section static pressure II obtained in the step S2;
S4, correcting the D in、DMF obtained in the S3, and calculating to obtain corresponding nacelle cover resistance D cowl;
in S3, the internal resistance D in is obtained by:
S310, dividing an outlet section into a plurality of areas based on a total pressure detection tube distribution mode in the pressure measuring rake I, wherein each area corresponds to an area where an outlet area A e is located and comprises 11 total pressure measuring points P 0e and 1 static pressure measuring point P e;
S311, calculating a corresponding outlet Mach number M e based on P 0e、Pe;
S312, calculating the corresponding flow tube flow M e based on M e obtained in S311:
In the above formula, q (M e) represents a flow function, and T 0 is the total temperature;
S313, based on m e obtained in the step S312, calculating a corresponding internal resistance D in according to the following formula:
In the above-mentioned method, the step of, The incoming flow rate is indicated by the velocity of the incoming flow,Representing the nacelle angle of attack, V e represents the nacelle exit velocity,Representing incoming static pressure;
in S311, when P e/P0e is not less than 1, M e =0;
When 0.528< p e/P0e <1, ；
When P e/P0e <0.528, M e is solved by:
；
In S3, the nacelle aerodynamic drag D MF is obtained by:
S320, dividing the outlet section into a plurality of areas based on a total pressure detection tube distribution mode in the pressure measuring rake II, wherein each area corresponds to an area where the outlet area A j is located and comprises 18 total pressure measuring points P 0j and 2 static pressure measuring points P j;
S321, integrating the wake harrow pressure data of different bus sections on the outer surface of the nacelle to obtain aerodynamic drag D MF of the nacelle:
In the above equation, father D MF represents the resistance correction term, D(s) represents the area integration region along the peripheral rake sector, and D MFj represents the wake resistance factor.
2. The method for testing the resistance characteristics of the nacelle of the civil aircraft engine according to claim 1, wherein in S2, the nacelle air intake flow is adjusted in the following manner:
the forward and backward movement position of the flow control cone on the nacelle resistance characteristic test device is adjusted, so that the air inlet flow of the nacelle is changed.
3. The method for testing the resistance characteristics of the nacelle of the civil aircraft engine according to claim 2, wherein the nacelle resistance characteristics testing device comprises:
The front end of the support rod is provided with a rectifying cone;
the nacelle is arranged at the front section of the support rod through the support piece;
The isolation equal straight sections are arranged on the supporting rods through a plurality of brackets and are adjacently arranged with the rear end of the nacelle;
The pressure measuring harrow I is arranged at the front end of the straight section of the isolation and the like to measure the internal resistance of the nacelle;
the pressure measuring harrow II is arranged on the outer ring of the middle part of the straight section of the isolation and the like so as to measure the aerodynamic resistance of the nacelle;
the inner side wall of the rear end of the isolation equal-straight section is provided with a conical surface, the supporting rod is provided with a cone matched with the conical surface, and the cone is arranged on the supporting rod through a driving mechanism;
the nacelle is in radial sealing connection with the isolated straight section through the sealing ring 1, and the nacelle is not in contact with the axial end face of the isolated straight section.
4. A method for testing the resistance characteristics of a nacelle of a civil aircraft engine according to claim 2, wherein a nacelle liner extending from the maximum flow cross section to the nacelle tail end surface is arranged inside the nacelle;
and the end face of the tail step of the nacelle lining is respectively provided with an outer pressure measuring point and an inner pressure measuring point.
5. The method for testing the resistance characteristics of the nacelle of the civil aircraft engine according to claim 1, wherein in S4, the nacelle cover resistance D cowl is obtained by: the nacelle aerodynamic drag D MF and the nacelle internal resistance D in are obtained through momentum integration, and are corrected, and the nacelle aerodynamic drag D MF is the sum of the nacelle internal resistance D in and the nacelle cover resistance D cowl, so that the nacelle cover resistance D cowl is calculated.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410459747.7A CN118067351B (en) | 2024-04-17 | Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine |
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| CN202410459747.7A CN118067351B (en) | 2024-04-17 | Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine |
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| CN118067351B true CN118067351B (en) | 2024-06-28 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
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