CN113062816B - Injection nozzle device for simulating subsonic/transonic outflow - Google Patents
Injection nozzle device for simulating subsonic/transonic outflow Download PDFInfo
- Publication number
- CN113062816B CN113062816B CN202110197098.4A CN202110197098A CN113062816B CN 113062816 B CN113062816 B CN 113062816B CN 202110197098 A CN202110197098 A CN 202110197098A CN 113062816 B CN113062816 B CN 113062816B
- Authority
- CN
- China
- Prior art keywords
- spray pipe
- flow
- nozzle
- secondary flow
- tertiary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
Abstract
The invention discloses a jet nozzle device for simulating subsonic/transonic outflow, which comprises a circular main nozzle section, a secondary flow nozzle section and a tertiary flow nozzle section, wherein the secondary flow nozzle section and the tertiary flow nozzle section surround the main nozzle section; the air outlet of the main jet pipe is extended along the air flow direction and is positioned behind the air outlet of the secondary flow jet pipe, and the flow field of the jet pipe with sub/transonic outflow is simulated under the condition of static outflow on the ground by designing a tertiary flow air inlet structure and adjusting the equivalent expansion ratio of the jet pipe, so that the similarity between the flow field in the jet pipe for ground test and the flow field in the real jet pipe is ensured. The simulation device has the advantages of simple pneumatic principle, easy realization of structure, no need of carrying out tests in a free jet wind tunnel and reforming the wind tunnel structure, realization of accurate simulation of subsonic/transonic outflow only through a conventional spray pipe ground test bed, effective avoidance of the problem of extremely choking wind tunnels in a transonic state, and effective saving of test cost and workload.
Description
Technical Field
The invention relates to the field of aircraft aerodynamic experiments, in particular to a jet nozzle device capable of simulating subsonic/transonic outflow.
Background
The TBCC has the characteristics of wide application, high durability, good economy, good low-speed performance, small environmental pollution, good reusability, normal take-off and landing and the like, and has good engineering application prospect. The main function of the TBCC tail pipe is to make the fuel gas at the outlet of the engine fully expand in the tail pipe, and convert the heat energy and the pressure energy carried by the fuel gas into kinetic energy so as to increase the impulse of the airflow at the outlet of the engine and further increase the thrust of the engine. As the TBCC exhaust nozzle works in a large falling pressure ratio range, the expansion ratio of the TBCC exhaust nozzle is changed from 2 in a take-off state to 15-20 in a supersonic cruise state, and the adjustment of the throat and the expansion angle of the exhaust nozzle must be realized by adopting a certain technical means. Currently, the main adjusting methods are mechanical adjusting methods, such as link driving adjusting, hydraulic actuating adjusting and the like, but the complexity of the nozzle configuration is increased.
The pneumatic adjustable spray pipe has a simpler configuration, is low in engineering realization difficulty and does not bring additional resistance, and obtains wide attention. In the existing injection nozzle scale test, a high-pressure air source is usually arranged at the inlet of a nozzle to simulate the upstream boundary condition, and the outlet of the nozzle is connected with a low-pressure air source or atmosphere to simulate the downstream condition. The method can simulate the working state of the spray pipe on the premise of low difficulty and high economy, but cannot accurately simulate the outflow condition, particularly the mutual coupling between the outflow and the main flow and further influences the flow field of the main flow.
In order to simulate high-speed airflow outside the Ejector Nozzle, the existing method is mainly to develop a high-speed wind tunnel experiment and simulate the high-speed airflow through the wind tunnel Nozzle (Bresnaban D.L, Performance of an aerodyne Nozzle positioned Autoxiliary Inet Ejector Nozzle No. 0 to 2.0, NASA TM-X-2023). However, the scheme is very complex, a special supporting system needs to be designed to supply air to the primary flow and the secondary flow of the ejector nozzle, a fairing needs to be specially designed to eliminate the influence of the upstream profile of the ejector nozzle on the flow field, and the scheme is high in cost.
In the prior art, for example, chinese patent application No. 202010847794.0 discloses an ejector nozzle experimental apparatus capable of simulating outflow of an aircraft, which can simulate supersonic airflow of an aircraft outer flow field without performing a high-speed wind tunnel experiment. However, the device is only limited to simulating supersonic airflow of the aircraft external flow field, and cannot simulate sub/transonic airflow of the aircraft external flow field.
However, simulation of the subsonic/transonic airflow of the aircraft external flow field, particularly simulation of the transonic inflow state, is very difficult, mainly because the flow field of the wind tunnel is easy to be choked in the transonic state, so that the test model has very small scale, the corresponding blockage degree is usually between 1% and 3%, the test with subsonic/transonic outflow and injection nozzle inflow interference is difficult to carry out, and even if the test can be carried out at very high cost.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects, the invention provides the ejector nozzle device for simulating the sub/transonic outflow, which can accurately simulate the coupling interference flow field of the sub/transonic outflow and the inner flow of the ejector nozzle of the aircraft on the premise of not carrying out a high-speed wind tunnel experiment by setting a tertiary flow path to simulate the sub/transonic outflow and adjusting the equivalent expansion ratio of the ejector nozzle.
The technical scheme is as follows: in order to solve the problems, the invention adopts a jet nozzle device for simulating subsonic/transonic outflow, which comprises a circular main nozzle section, a secondary flow nozzle section and a tertiary flow nozzle section, wherein the secondary flow nozzle section surrounds the main nozzle section; the main nozzle section comprises a main nozzle channel and a main nozzle air outlet connected with the main nozzle channel;
the secondary flow spray pipe section comprises a secondary flow spray pipe channel surrounding the main spray pipe section and extending backwards, and a secondary flow spray pipe air outlet connected with the secondary flow spray pipe channel, wherein the main spray pipe air outlet is extended along the air flow direction and is positioned behind the secondary flow spray pipe air outlet;
the tertiary flow spray pipe section comprises a tertiary flow spray pipe channel surrounding the secondary flow spray pipe section and extending backwards and a tertiary flow spray pipe air outlet connected with the tertiary flow spray pipe channel, the axial projection of the tertiary flow spray pipe air outlet and the axial projection of the secondary flow spray pipe air outlet are overlapped, and the convergence half angle of the secondary flow spray pipe air outlet is larger than that of the tertiary flow spray pipe air outlet.
Has the advantages that: compared with the prior art, the simulation device has the obvious advantages of simple pneumatic principle, easy realization of structure, no need of carrying out tests in a free jet wind tunnel and reconstruction of the wind tunnel structure, can realize accurate simulation of sub/transonic outflow only through a conventional nozzle ground experiment table, can effectively avoid the problem of extremely congested wind tunnels in a transonic state, effectively saves the test cost and workload, and provides a feasible test scheme for carrying out research on the internal and external flow coupling mechanism of the rear body/ejector nozzle of the aircraft. The invention properly prolongs the outlet of the main jet pipe along the direction of the gas streamline, and adjusts the equivalent expansion ratio of the injection jet pipe, so that the structure of the outflow flow field of the simulation test is consistent with the real condition.
Furthermore, the secondary flow spray pipe channel comprises a secondary flow spray pipe air inlet and a secondary flow spray pipe main body, the secondary flow spray pipe air inlet is a contraction pipeline with a lip, the secondary flow spray pipe air inlet and the secondary flow spray pipe air outlet are connected through the secondary flow spray pipe main body, the secondary flow spray pipe section further comprises a secondary flow total pressure regulator, and the secondary flow total pressure regulator is used for regulating total pressure loss and secondary flow rate of the secondary flow spray pipe section.
Furthermore, the secondary flow total pressure regulator is an annular plate which is in contact with the outer surface of the main nozzle section, the plane where the annular plate is located is parallel to the cross section of the main nozzle section, a plurality of round holes are formed in the annular plate, and the secondary flow total pressure regulator is arranged between the air inlet of the secondary flow nozzle and the main body of the secondary flow nozzle.
Furthermore, the tertiary flow spray pipe channel comprises an annular inlet, a tertiary flow spray pipe air inlet and a tertiary flow spray pipe main body, wherein the tertiary flow spray pipe air inlet is connected with the annular inlet, the tertiary flow spray pipe air outlet is connected with the tertiary flow spray pipe main body, the annular inlet is provided with a plurality of air inlets, and the tertiary flow spray pipe air inlet is a tapered pipeline along the air flow direction.
Further, the annular inlet aperture has a porosity greater than 34%.
Further, the air inlet hole of the annular inlet is circular.
Further, under test conditions, the main nozzle flow
Flow rate of secondary flow
And tertiary flow rate
The calculation formula is as follows:
wherein the content of the first and second substances,
the main jet flow, the secondary flow and the tertiary flow under the actual working condition are respectively;
respectively setting the total temperature of a main spray pipe section, the total temperature of a secondary flow spray pipe section and the total temperature of a tertiary flow spray pipe section under the actual working condition;
the total temperature of the main spray pipe section, the total temperature of the secondary flow spray pipe section and the total temperature of the tertiary flow spray pipe section under the test conditions are respectively.
Drawings
FIG. 1 is a cross-sectional view of an induction nozzle assembly of the present invention;
FIG. 2 is a perspective view of a half-mold of the induction nozzle assembly of the present invention;
FIG. 3 is a meridian Mach number cloud chart obtained by numerical simulation of the ejector nozzle device of the present invention.
Detailed Description
As shown in figures 1 and 2, in the transonic wind tunnel test of the outflow aircraft, the size of the test device needs to be very small to ensure that the choking degree of the wind tunnel is between 1% and 3%. In the injection spray pipe device, the size of the test device is not limited, the test device can be processed into a reasonable size, and the processing difficulty is greatly simplified, and the device comprises a circular main spray pipe section 1, a secondary flow spray pipe section 2, a tertiary flow spray pipe section 3 and a support plate 4; the support plate 4 is used for fixing the positions of the main spray pipe section 1, the secondary flow spray pipe section 2 and the tertiary flow spray pipe section 3, the main spray pipe section 1, the secondary flow spray pipe section 2 and the tertiary flow spray pipe section 3 are annular pipelines with a common central shaft, the secondary flow spray pipe section 2 surrounds the outer side of the main spray pipe section 1, and the tertiary flow spray pipe section 3 surrounds the outer side of the secondary flow spray pipe section 2. The main jet pipe section 1 and the secondary jet pipe section 2 are respectively used for simulating an injection flow path of a main flow 13 and a secondary flow 14 of an aircraft.
The main spray pipe section 1 comprises a main spray pipe channel and a main spray pipe air outlet connected with the main spray pipe channel; the secondary flow spray pipe section 2 comprises a secondary flow spray pipe channel which surrounds the main spray pipe section 1 and extends backwards, a secondary flow spray pipe air outlet 7 connected with the secondary flow spray pipe channel, and a secondary flow total pressure regulator 8, wherein the secondary flow spray pipe channel comprises a secondary flow spray pipe air inlet 5 and a secondary flow spray pipe main body 6, the secondary flow spray pipe air inlet 5 and the secondary flow spray pipe air outlet 7 are connected through the secondary flow spray pipe main body 6, and the secondary flow spray pipe air inlet 5 is a contraction pipeline with a lip; the secondary flow main pressure regulator 8 is a circular ring plate which is in contact with the outer surface of the main spray pipe section 1, the plane where the circular ring plate is located is parallel to the cross section of the main spray pipe section 1, a plurality of circular holes are formed in the circular ring plate, the secondary flow main pressure regulator 8 is arranged between the secondary flow spray pipe air inlet 5 and the secondary flow spray pipe main body 6, the total pressure loss and the secondary flow of the secondary flow spray pipe section 2 are regulated by regulating the porosity, and the pressure drop ratio of the secondary flow spray pipe section 2 is not more than 1. The secondary flow spray pipe air inlet 5 directly inhales air from the environment, and the structure of the three-flow-path jet spray pipe testing device for simulating transonic outflow is greatly simplified on the premise of ensuring an accurate secondary flow field simulating structure.
The air outlet of the main jet pipe is extended along the air flow direction and is positioned behind the air outlet 7 of the secondary flow jet pipe, and the air outlet is used for reducing the equivalent expansion ratio of the jet pipe so as to simulate the constraint effect of outflow on the inner flow of the jet pipe.
The tertiary flow spray pipe section 3 comprises a tertiary flow spray pipe channel surrounding the secondary flow spray pipe section 2 and extending backwards, and a tertiary flow spray pipe air outlet 9 connected with the tertiary flow spray pipe channel, the tertiary flow spray pipe channel comprises an annular inlet 12, a tertiary flow spray pipe air inlet 11 connected with the annular inlet 12, and a tertiary flow spray pipe main body 10, the tertiary flow spray pipe air inlet 11 and the tertiary flow spray pipe air outlet 9 are connected through the tertiary flow spray pipe main body 10, the tertiary flow spray pipe air inlet 11 is a tapered pipeline along the air flow direction, the tertiary flow spray pipe main body 10 is a circular pipeline with a constant diameter, and the circular pipeline surrounds the secondary flow spray pipe section 2 in parallel to provide air flow of axial air inlet, so that the internal flow field of the ground test injection spray pipe is similar to a real internal flow field. The axial projection of the air outlet 9 of the tertiary flow spray pipe is superposed with the axial projection of the air outlet 7 of the secondary flow spray pipe, the convergence half angle of the air outlet 7 of the secondary flow spray pipe is larger than that of the air outlet 9 of the tertiary flow spray pipe, an inclined expanded circular pipeline is formed between the inner surface of the air outlet 9 of the tertiary flow spray pipe and the outer surface of the air outlet 7 of the secondary flow spray pipe, and the tertiary flow 15 passes through the air outlet 9 of the tertiary flow spray pipe and then is mixed with the secondary flow 14.
The annular inlet 12 is uniformly provided with a plurality of circular air inlets, the porosity of the air inlets of the annular inlet 12 is more than 34%, the high-pressure air supply sources of the existing test bed are all circular channels, and the air inlet 11 of the tertiary flow spray pipe is of an annular structure. Therefore, the annular inlet 12 distributed with a plurality of circular air inlets is arranged at the air inlet 11 of the tertiary flow spray pipe, the gradually expanding circular structure is connected at the position of the high-pressure air supply source of the external flow, the same circular air supply holes are distributed, and then the PV hose is connected through the pagoda head for air conveying, so that the problem that the circular high-pressure air supply source supplies air for the annular structure is solved. The drop pressure ratio of the tertiary flow spray pipe section 3 is larger than 1 by adjusting the flow rate of the air flow supplied to the tertiary flow spray pipe section 3 by the high-pressure air supply source.
In the test, the drop pressure ratio of the main nozzle, the injection coefficients of the secondary flow and the tertiary flow are consistent with those in actual flight. Calculating to obtain the main nozzle flow under the test condition according to the geometric dimension of the nozzle model and the critical condition of the main nozzle throat
Flow rate of secondary flow
And tertiary flow rate
The calculation formula is as follows:
wherein the content of the first and second substances,
are respectively asMain nozzle flow, secondary flow and tertiary flow under actual working conditions;
respectively setting the total temperature of a main spray pipe section, the total temperature of a secondary flow spray pipe section and the total temperature of a tertiary flow spray pipe section under the actual working condition;
the total temperature of the main spray pipe section, the total temperature of the secondary flow spray pipe section and the total temperature of the tertiary flow spray pipe section under the test conditions are respectively.
Aiming at the injection nozzle device in the embodiment, the effect of the injection nozzle device is verified by adopting a numerical simulation method. Based on the initial working condition of the transonic three-flow-path ejector nozzle with Ma being 1.2, a reasonable tertiary flow nozzle air inlet 11 and a reasonable tertiary flow nozzle main body 10 are designed to adjust the equivalent expansion ratio of the ejector nozzle, so that the nozzle flow field structure obtained by a simulation test is matched with the original flow field structure, and the design purpose is achieved.
The device capable of simulating the outflow test provided by the invention has the advantages of simple pneumatic principle, easy structure realization, great utilization of the original test assembly and great reduction of the test cost. On the premise of ensuring similar flow, a reasonable tertiary flow air inlet structure is designed. And the outlet of the main jet pipe is properly prolonged along the gas streamline direction, and the equivalent expansion ratio of the injection jet pipe is adjusted, so that the outflow flow field structure of the simulation test is consistent with the real condition. Therefore, the reasonable three-time flow air inlet structure and the equivalent expansion ratio of the injection nozzle are more important than a three-flow path injection nozzle test for simulating transonic outflow.
Claims (7)
1. A jet nozzle device for simulating subsonic/transonic outflow is characterized by comprising a circular main jet pipe section, a secondary flow jet pipe section and a tertiary flow jet pipe section, wherein the secondary flow jet pipe section and the tertiary flow jet pipe section surround the main jet pipe section; the main nozzle section comprises a main nozzle channel and a main nozzle air outlet connected with the main nozzle channel;
the secondary flow spray pipe section comprises a secondary flow spray pipe channel surrounding the main spray pipe section and extending backwards, and a secondary flow spray pipe air outlet connected with the secondary flow spray pipe channel, and the main spray pipe air outlet is backwards extended to the rear of the secondary flow spray pipe air outlet from the rear end of the main spray pipe channel;
the tertiary flow spray pipe section comprises a tertiary flow spray pipe channel surrounding the secondary flow spray pipe section and extending backwards and a tertiary flow spray pipe air outlet connected with the tertiary flow spray pipe channel, the axial projection of the tertiary flow spray pipe air outlet and the axial projection of the secondary flow spray pipe air outlet are overlapped, and the convergence half angle of the secondary flow spray pipe air outlet is larger than that of the tertiary flow spray pipe air outlet.
2. The ejector nozzle assembly of claim 1, wherein the secondary flow nozzle passage comprises a secondary flow nozzle inlet and a secondary flow nozzle body, the secondary flow nozzle inlet is a necked-down tube, the secondary flow nozzle inlet and the secondary flow nozzle outlet are connected by the secondary flow nozzle body, the secondary flow nozzle section further comprises a secondary flow total pressure regulator for regulating total pressure loss and secondary flow rate of the secondary flow nozzle section.
3. The induction nozzle assembly of claim 2, wherein the total secondary flow pressure regulator is an annular plate in contact with the outer surface of the primary nozzle segment, the plane of the annular plate is parallel to the cross section of the primary nozzle segment, the annular plate is provided with a plurality of circular holes, and the total secondary flow pressure regulator is arranged between the air inlet of the secondary flow nozzle and the main body of the secondary flow nozzle.
4. The induction nozzle device as claimed in claim 1, wherein the tertiary flow nozzle passage comprises an annular inlet, a tertiary flow nozzle inlet connected to the annular inlet, and a tertiary flow nozzle body, the tertiary flow nozzle inlet and the tertiary flow nozzle outlet are connected through the tertiary flow nozzle body, the annular inlet is provided with a plurality of air inlets, and the tertiary flow nozzle inlet is a tapered duct from front to back.
5. The ejector nozzle assembly of claim 4, wherein the annular inlet bleed has a porosity greater than 34%.
6. The ejector nozzle assembly of claim 4, wherein the annular inlet air inlet is circular.
7. The ejector nozzle assembly of any one of claims 1-6 wherein the primary nozzle flow rate is at test conditions
Flow rate of secondary flow
And tertiary flow rate
The calculation formula is as follows:
wherein the content of the first and second substances,
the main jet flow, the secondary flow and the tertiary flow under the actual working condition are respectively;
respectively setting the total temperature of a main spray pipe section, the total temperature of a secondary flow spray pipe section and the total temperature of a tertiary flow spray pipe section under the actual working condition;
the total temperature of the main spray pipe section, the total temperature of the secondary flow spray pipe section and the total temperature of the tertiary flow spray pipe section under the test conditions are respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197098.4A CN113062816B (en) | 2021-02-22 | 2021-02-22 | Injection nozzle device for simulating subsonic/transonic outflow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110197098.4A CN113062816B (en) | 2021-02-22 | 2021-02-22 | Injection nozzle device for simulating subsonic/transonic outflow |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113062816A CN113062816A (en) | 2021-07-02 |
| CN113062816B true CN113062816B (en) | 2022-04-19 |
Family
ID=76558823
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110197098.4A Active CN113062816B (en) | 2021-02-22 | 2021-02-22 | Injection nozzle device for simulating subsonic/transonic outflow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113062816B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3409228A (en) * | 1966-02-10 | 1968-11-05 | Gen Electric | Ejector nozzle |
| CN108999725B (en) * | 2018-07-19 | 2020-07-24 | 北京航空航天大学 | Jet nozzle with double-bell-shaped jet sleeve |
| CN109918839B (en) * | 2019-03-27 | 2020-06-09 | 南京航空航天大学 | Modeling method and infrared radiation prediction method for turbofan engine with pilot nozzle |
| CN110985231B (en) * | 2019-11-19 | 2020-10-13 | 中国人民解放军国防科技大学 | Closed-loop self-adaptive adjusting ejector and rocket nozzle |
| CN212177293U (en) * | 2019-12-06 | 2020-12-18 | 中国民用航空飞行学院 | Double-contraction-expansion type tail nozzle structure with three ducts for injection |
| CN112035952B (en) * | 2020-08-21 | 2021-07-27 | 南京航空航天大学 | Design method of ejector nozzle experimental device for simulating outflow of aircraft |
-
2021
- 2021-02-22 CN CN202110197098.4A patent/CN113062816B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN113062816A (en) | 2021-07-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108168832B (en) | A kind of throat structure improving tube wind tunnel test Reynolds number | |
| CN112035952B (en) | Design method of ejector nozzle experimental device for simulating outflow of aircraft | |
| CN104632411B (en) | Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways | |
| CN110284994B (en) | Parallel thrust vector exhaust system based on throat offset type pneumatic vector spray pipe | |
| CN108195544B (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN104359644B (en) | Hypersonic low density wind tunnel variable Mach number nozzle | |
| Ran et al. | Preliminary design of a 2D supersonic inlet to maximize total pressure recovery | |
| CN110657043B (en) | Mechanical disturbance type throat offset pneumatic vectoring nozzle | |
| US8800259B2 (en) | Thrust vector system | |
| CN114279714B (en) | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application | |
| CN111426445B (en) | road-de-Wickel tube wind tunnel and method for expanding high Mach number thereof | |
| CN104807610A (en) | Sprayer nozzle used for tail jet flow interference test | |
| CN113029573B (en) | Low-Reynolds-number plane cascade high-altitude flow simulation device | |
| CN103149009A (en) | Supersonic isolating section wind tunnel test device | |
| CN113049210A (en) | Measuring system for air flow energy mixing | |
| CN208310917U (en) | A kind of switching segment structure solving S bending nozzle and fanjet matching problem | |
| CN112240831A (en) | Design method of aero-engine intake temperature distortion generator | |
| US9546618B2 (en) | Methods and apparatus for passive thrust vectoring and plume deflection | |
| CN113062816B (en) | Injection nozzle device for simulating subsonic/transonic outflow | |
| CN212903808U (en) | Ejector and wind tunnel test device with same | |
| CN112179605B (en) | Ejector nozzle experimental device for simulating outflow of aircraft | |
| CN104614183A (en) | Nose cone and test device for combined dynamic air inlet passage modal transformation test | |
| JP2021037938A (en) | Propulsion system for aircraft and method of manufacturing propulsion system for aircraft | |
| CN114942116B (en) | Method for simulating supersonic flow field of front fuselage of aircraft with layout of air inlet channel under abdomen | |
| CN112964448B (en) | Airflow mixer for plane blade grid high-altitude flow simulation device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |