CN115824562A - Active cooling front edge test system applied to air film of electric arc wind tunnel - Google Patents
Active cooling front edge test system applied to air film of electric arc wind tunnel Download PDFInfo
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- CN115824562A CN115824562A CN202211193714.XA CN202211193714A CN115824562A CN 115824562 A CN115824562 A CN 115824562A CN 202211193714 A CN202211193714 A CN 202211193714A CN 115824562 A CN115824562 A CN 115824562A
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Abstract
The invention provides a test system for a front edge of an air film active cooling wing applied to an electric arc wind tunnel. The invention comprises a sonic throat, an electric pressure regulating valve, a pressure sensor, an electromagnetic switch valve and a heat flow sensor, wherein a plurality of cooling air holes are uniformly arranged at intervals along the highest heat flow line on the front edge of the wing, the ratio of the radius of the cooling air holes to the radius of the front edge of the wing ranges from 1/10 to 1/5, two to three heat flow measuring points are arranged between two air holes and used for detecting the heat flow density between the two air holes, and simultaneously, two heat flow measuring points are respectively arranged on two sides of the cold air holes. Before the test, the air flow is changed by replacing the sound velocity throats with different diameters, and the pressure of the branch is adjusted by adjusting the electric adjusting valves on the branch pipelines according to the distribution condition of the measured values of the heat flow sensors, so that the problem of the active air film cooling thermal protection aerodynamic heat test of the hypersonic aircraft wing leading edge material is solved.
Description
Technical Field
The invention relates to the field of an aerospace aerodynamic thermal ablation test, in particular to a reusable aircraft heat-proof material.
Background
When the hypersonic aircraft flies at high speed in the atmospheric layer, the hypersonic aircraft is subjected to severe aerodynamic heating, and as an important part of the hypersonic aircraft, the leading edge of the wing is subjected to severe aerodynamic heating. Along with the development of hypersonic reusable aircrafts, the heat-proof materials on the surfaces of the aircrafts are required to be repeatedly used for many times, the traditional passive heat protection mode, such as an ablation heat protection mode, cannot meet the heat-proof requirements of the aircrafts, most of the passive heat protection mode adopts active heat protection, and the principle is that most of heat flows are taken away by means of cooling working media.
Because the power problem of the hypersonic aircraft is limited, the mass of each part of the aircraft is limited to a certain extent, and for the active air film cooling front edge, the minimum air flow is required to realize a uniform test effect, which puts higher requirements on the position of a cold wall heat flow measuring point on the front edge and the control of the pressure of cooling air. Firstly, cold air flow meets supersonic incoming flow on the front edge, if the total pressure of the cold air is high, shock waves are easily generated on the upstream of the cold air hole, so that a local high heat flow area appears on the front edge, if the total pressure of the cold air is low, high-temperature incoming flow is forced to enter the cold air hole, and the cooling effect is poor. Therefore, a proper dimensionless ratio of the total pressure of the cold air flow to the surface pressure of the leading edge must be found by a ground test system, so that the cold air flow flows through the boundary layer on the leading edge, and the method can be formally applied to models.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the air film active cooling wing leading edge test system applied to the arc wind tunnel is provided, and the air film cooling effect of the wing leading edge is improved by adjusting the pressure of each cold air branch.
The technical scheme of the invention is as follows: the invention relates to a test system for an active film cooling wing leading edge applied to an electric arc wind tunnel, wherein the wing leading edge is positioned in a high-temperature flow field at the downstream of a spray pipe outlet;
each cooling branch comprises an electric regulating pressure valve, a pressure sensor and a second electromagnetic switch valve; the front edge of the wing is provided with N cooling air holes, 4N-1 heat flow measuring points and N cooling channels, the cooling channels are connected to the cooling air holes, and the heat flow sensors are arranged at the heat flow measuring points; the upstream of the acoustic throat is communicated with normal-temperature air under standard atmospheric pressure to provide a cold air source, the downstream of the acoustic throat is connected with a first electromagnetic switch valve and is arranged outside the test cabin together, the output of the first electromagnetic switch valve is connected into the test cabin through a connecting pipe and is connected with N cooling branches, and the N cooling branches are connected to N cooling channels at the front edge of the wing; on each cooling branch, the output of the electric regulating pressure valve is connected with the input of the second electromagnetic switch valve, and the pressure sensor measures the pressure between the electric regulating pressure valve and the second electromagnetic switch valve; adjusting the pressure of each branch by adjusting an electric adjusting valve on each cooling branch according to the distribution condition of the measured value of each heat flow sensor on the front edge of the wing, so as to improve the air film cooling effect of the front edge of the wing; n is more than or equal to 1.
Furthermore, the acoustic throat is a contracted circular flow channel, and the large-aperture end is the upstream of the acoustic throat and is communicated with the atmosphere; the small-caliber end is the downstream of the acoustic throat and is connected with N cooling branches through connecting pipes, and N is more than or equal to 1.
Furthermore, electricity pressure regulating valve and second electromagnetic switch valve all are connected to the cooling branch on the way through sealing joint, and pressure sensor is connected to the cooling branch on the way through the three-way valve, and N cooling branch, wing leading edge and heat flow sensor all place in the test chamber.
Further, the vacuum degree in the test chamber is less than 1kPa.
Furthermore, N cooling air holes are uniformly formed in the front edge of the wing along the direction of the highest heat flow line on the cambered surface, the interval between every two adjacent cooling air holes is 20-30 mm, the diameter of each cooling air hole is 1/10-1/5 of the radius of the cambered surface of the front edge of the wing, and N is larger than or equal to 1.
Further, the distribution of the positions of the heat flow measuring points is as follows:
(1) Symmetrically arranging a heat flow measuring point on each of two sides of each cooling air hole, which are perpendicular to the inflow direction of the spray pipe, by taking the center of the cooling air hole as a center, wherein the distance between each heat flow measuring point and the center of the current cooling air hole is 3-5 mm;
(2) Flowing along the spray pipe, arranging a heat flow measuring point on the highest heat flow line at the upstream position of each cooling air hole, wherein the distance between the heat flow measuring point and the center of the cooling air hole is 5-10 mm;
(3) A heat flow measuring point is arranged between two adjacent cooling air holes.
Further, the method for determining the position of the highest heat flow line of the leading edge of the wing comprises the following steps: defining a straight line connecting the midpoints of arcs at two ends of the arc surface of the front edge of the wing as a central line, and for the front edge of the wing without a deflection angle, locating the highest heat flow line on the central line of the arc surface of the front edge of the wing; for the deflected wing leading edge, the highest heat flow line is positioned on the wing leading edge surface of the windward side determined by the following formula and is parallel to the central line of the circular arc surface of the wing leading edge;
in the above formula: epsilon is an included angle between a plane passing through the highest heat flow line and the circle center of the arc surface and a plane passing through the center line of the arc surface and the circle center of the arc surface, alpha is a deflection angle, and beta is a windward angle.
Furthermore, the heat flow sensor comprises a heat measuring block, a heat insulation sleeve and a K-type thermocouple, the heat insulation sleeve is sleeved outside the heat measuring block, and the axial bottom end of the heat measuring block is communicated with the K-type thermocouple.
Further, a control signal of the electric pressure regulating valve 2 is direct current P-Q milliampere, a current value of the control signal is in a linear relation with the opening degree of the valve, the valve is closed when P milliampere, the valve is fully opened when Q milliampere, P is more than 1, Q is >1, P is restricted to Q;
according to the measured value distribution of the heat flow on the wing leading edge 5, the pressure of each cooling branch is adjusted by adjusting the electric pressure adjusting valve 2, and the method specifically comprises the following steps:
if the heat flow value around the current cooling air hole is higher than the heat flow value at the middle position of the current cooling air hole and the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is large, the current value of the control signal is reduced, the air inlet pressure is reduced, and the air inflow is reduced until the heat flow value of a measuring point around the current cooling air hole is lower than or equal to the heat flow value between the two cooling air holes;
if the heat flow value around the current cooling air hole is lower than the heat flow value between the current cooling air hole and the middle position of the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is small, the current value of the control signal is increased, the air inflow pressure is increased, and the air inflow is increased until the heat flow value of a measuring point around the current cooling air hole is higher than or equal to the heat flow value between the two cooling air holes;
the current signal is converted into corresponding linear displacement, and the opening degree of the valve is correspondingly and linearly increased by increasing the current value of the control signal.
Further, the mass calculation formula of the cold air source is as follows:
in the above formula, m is the mass of cold air, unit: kg/s;
is the area of the downstream outlet of the sonic throat, and the unit is as follows: m is 2 ；p 0 Atmospheric pressure, which is 0.1MPa; t is 0 Is the atmospheric ambient temperature, in units: K.
compared with the prior art, the invention has the beneficial effects that:
(1) The invention takes the atmospheric environment as a cooling gas supply source, and directly calculates the mass flow of air by combining the sonic throat according to the principle of aerodynamic isentropic flow, and simultaneously, the mass flow of the cooling gas can be changed by replacing the sonic throats with different outlet diameters as required by the test, and the operation is simple and convenient.
(2) The invention arranges heat flow measuring points at the center positions of the upstream cooling air hole, the two sides and the downstream cooling air hole at the cooling air hole of the front edge of the wing, and can monitor the heat flow uniformity of key parts on the front edge of the wing in real time.
(3) According to the distribution condition of the measured values of the heat flow measuring points on the front edge of the wing, the pressure of each branch can be adjusted through the electric pressure regulating valves on different cold air branches, so that the air film cooling effect on the front edge of the wing is further improved.
Drawings
FIG. 1 is a schematic view of an active film cooling test system for a leading edge of an airfoil in accordance with an embodiment of the present invention;
FIG. 2 is a schematic view of a flow channel of a sonic throat according to an embodiment of the present invention;
FIG. 3 is a schematic view of the distribution of heat flow measurement points on the leading edge of the film cooling airfoil in accordance with the present invention;
Detailed Description
The invention is described in further detail below with reference to the attached drawing figures:
the invention provides a test system applied to an active cooling wing front edge of an arc wind tunnel air film, which takes an atmospheric environment as an air source, changes the mass flow of cold air by replacing sound velocity throats 1 with different outlet diameters, simultaneously adjusts the pressure in each cold air branch, finally finds out the dimensionless ratio of the total pressure of the cold air of each branch to the static pressure on the front edge, realizes the better cooling effect of the active air film on the front edge, and lays a foundation for model application.
FIG. 1 shows a schematic diagram of an active film cooling test system for a leading edge of an airfoil, which comprises a sonic throat 1, a first electromagnetic switch valve, N cooling branches and a heat flow sensor.
Each cooling branch comprises an electric pressure regulating valve 2, a pressure sensor 3 and a second electromagnetic switch valve 4; the wing front edge 5 is provided with N cooling air holes, heat flow measuring points and N cooling channels, the cooling channels are connected to the cooling air holes, and the heat flow sensors are arranged at the heat flow measuring points; the upstream of the acoustic throat 1 is communicated with normal temperature air under standard atmospheric pressure, the downstream of the acoustic throat 1 is connected with a first electromagnetic switch valve and is arranged outside the test cabin together, the output of the first electromagnetic switch valve is connected into the test cabin through a connecting pipe and is connected with each cooling branch, and each cooling branch is connected to a cooling channel of the wing leading edge 5; on every cooling branch, the output of electricity accent pressure valve 2 is connected with the input of second electromagnetic switch valve 4, and pressure sensor 3 measures the pressure between electricity accent pressure valve 2 and second electromagnetic switch valve 4. The N cooling branches, the wing leading edge 5 and the heat flow sensor are all placed in the test cabin; the airfoil leading edge 5 is placed in the high temperature flow field downstream of the nozzle exit.
Air enters the test chamber through the sonic throat 1 and a first electromagnetic switch valve at the downstream of the sonic throat 1 under the condition of standard atmospheric pressure, enters each cold air branch, and is connected to a cooling air hole on the front edge through a cooling channel of the electric pressure regulating valve 2, the pressure sensor 3, the second electromagnetic switch valve 4 and the wing front edge 5. In this embodiment, the electricity is transferred and is pressed valve 2 and second electromagnetic switch valve 4 and all be connected to the cooling branch through sealing joint on the way, and pressure sensor 3 is connected to the cooling branch through the three-way valve on the way.
In order to ensure the required supersonic flow field at the nozzle outlet in the front of the wing front edge and ensure the sonic flow at the sonic throat outlet, a certain vacuum degree is required to be maintained in the test chamber, and the vacuum degree is recommended to be less than 1kPa.
FIG. 2 is a schematic view of a flow channel of the sonic throat, and the required cold air mass flow passing through the sonic throat can be derived through isentropic flow by combining a motion equation and an energy equation, wherein the calculation formula is as follows:
wherein m is mass flow, unit: kg/s;
is the area of the exit of the acoustic throat, and the unit is: m is 2 ；p 0 Atmospheric pressure, which is 0.1MPa; t is 0 Atmospheric ambient temperature, K.
The electric pressure regulating valve 2 in the test chamber can regulate the pressure according to the distribution condition of heat flow near the cooling air holes on each cold air branch and the wing front edge 5. The pressure sensor 3 at the downstream of the electric pressure regulating valve 2 is used for measuring the surface pressure of the front edge of the wing in the high-temperature supersonic flow field, the first electromagnetic switch valve at the downstream of the sonic throat 1 is closed, the second electromagnetic switch valve 4 of each branch is opened, and the surface pressure of each cooling air hole position on the front edge of the wing during the test can be measured through the pressure sensor 3 of each branch, which is expressed as P b1 、P b2 、P b3 ，……，P bM . Similarly, the first electromagnetic switch valve is opened and the second electromagnetic switch valve 4 on each branch is closed, and the measured value of each branch pressure sensor 3 is the total pressure of the cooling air of each branch, which is expressed as P 01 、P 02 、P 03 ，……，P 0M . The ratio of the total pressure of each branch cooling gas to the surface pressure of the corresponding cooling gas hole isDimensionless ratio of total cold air pressure to pressure of leading edge 5, i.e. P, on each branch 01 /P b1 、P 02 /P b2 、P 03 /P b3 ,……，P 0M /P bM 。
The wing front edge 5 at the downstream of the second electromagnetic switch valve 4 on each branch is triangular or rectangular or trapezoidal in section, and the top of the wing front edge is formed by splicing arc surfaces; which is fixed in a high-temperature supersonic flow field at the outlet of the spray pipe through a water-cooling bracket. The cooling air holes are uniformly arranged along the flow field direction, the interval between every two adjacent cooling air holes is 20-30 mm, the diameter of each cooling air hole is 1/10-1/5 of the diameter of the front edge 5 of the wing, and a cooling channel connected with the cooling air holes is arranged in the front edge 5 of the wing and is wrapped by a heat insulating material to avoid ablation by hot air flow.
The position of a cold air inlet hole on the wing front edge 5 is arranged at the position with the highest heat flow on a certain section of the wing front edge 5, a straight line connecting the midpoints of arcs at two ends of the arc surface of the wing front edge 5 is defined as a central line, and for the wing front edge 5 without a deflection angle, the highest heat flow line is positioned on the central line of the arc surface of the wing front edge 5; for the deflected wing leading edge 5, the highest heat flow line is positioned on the surface of the wing leading edge 5 on the windward side determined by the following formula and is parallel to the central line of the arc surface of the wing leading edge 5;
in the above formula: epsilon is an included angle between a plane passing through the highest heat flow line and the circle center of the arc surface and a plane passing through the center line of the arc surface and the circle center of the arc surface, alpha is a deflection angle, and beta is a windward angle.
Fig. 3 shows a schematic diagram of the distribution of the cold air holes and cold wall heat flow on the leading edge 5 of the airfoil, the distribution of the positions of the heat flow points being:
(1) Two sides of each cooling air hole, which are vertical to the incoming flow direction of the spray pipe, are symmetrically provided with a heat flow measuring point by the center of the cooling air hole respectively, and the distance between each heat flow measuring point and the center of the current cooling air hole is 3-5 mm;
(2) Flowing along the spray pipe, arranging a heat flow measuring point on the highest heat flow line at the upstream position of each cooling air hole, wherein the distance between the heat flow measuring point and the center of the cooling air hole is 5-10 mm;
(3) A heat flow measuring point is arranged between two adjacent cooling air holes.
When the pressure of the cooling air is high, the supersonic incoming flow is blocked, shock waves are generated at the upstream of the cold air hole, high heat flow areas are generated at the upstream and two sides of the cold air hole, finally, the cold air can only flow in the front edge boundary layer along with the reduction of the pressure of the cold air, the shock waves disappear, local high heat flow areas disappear, the heat flow of the cold wall on the front edge surface between the two cold air holes is obviously reduced compared with that when the cold air is not available, and a good cooling effect is achieved. The pressure of each cooling branch needs to be adjusted by adjusting the electric regulating pressure valve 2, and the method comprises the following steps:
the control signal of the electric pressure regulating valve 2 is DC 4-20 milliampere, the current value of the control signal and the opening of the valve are in a linear relation, the valve is closed at 4 milliampere, and the valve is fully opened at 20 milliampere;
if the heat flow value around the current cooling air hole is higher than the heat flow value at the middle position of the current cooling air hole and the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is large, the current value of the control signal is reduced, the air inlet pressure is reduced, and the air inflow is reduced until the heat flow value of a measuring point around the current cooling air hole is lower than or equal to the heat flow value between the two cooling air holes;
if the heat flow value around the current cooling air hole is lower than the heat flow value between the current cooling air hole and the middle position of the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is small, the current value of the control signal is increased, the air inflow pressure is increased, and the air inflow is increased until the heat flow value of the measuring points around the current cooling air hole is higher than or equal to the heat flow value between the two cooling air holes;
the current signal is converted into corresponding linear displacement, and the opening degree of the valve is correspondingly and linearly increased by increasing the current value of the control signal.
And the active film cooling test of the leading edge of the wing under different flow conditions is realized by replacing the acoustic throat 1.
The heat flow sensor used in this embodiment is a plug calorimeter; a heat measuring block is vertically arranged in the heat flow sensor; the heat measuring block is made of oxygen-free red copper material; the heat measuring block is of a cylindrical structure; the diameter of the calorimetric block is 3mm; the axial length of the calorimetric block is 5mm. A heat insulation sleeve is sleeved outside the heat measuring block, and the axial length of the heat insulation sleeve is 6.5mm; the wall thickness of the heat insulation sleeve is 1mm; the axial bottom end of the heat measuring block is communicated with the K-type thermocouple; the range of the K-type thermocouple is 0-1300 ℃. The thermocouple is led out from the inner channel of the wing leading edge 5 through a water-cooled bracket.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (9)
1. The utility model provides an air film initiative cooling wing leading edge test system for electric arc wind-tunnel, wing leading edge (5) are arranged in the flow field of test cabin spray tube export low reaches which characterized in that: the device comprises a sound velocity throat (1), a first electromagnetic switch valve, N cooling branches and a heat flow sensor;
each cooling branch comprises an electric regulating pressure valve (2), a pressure sensor (3) and a second electromagnetic switch valve (4); n cooling air holes, 4N-1 heat flow measuring points and N cooling channels are arranged on the wing front edge (5), the cooling channels are connected to the cooling air holes, and the heat flow sensors are arranged at the heat flow measuring points; the upstream of the acoustic throat (1) is communicated with normal-temperature air under standard atmospheric pressure to supply a cold air source, the downstream of the acoustic throat (1) is connected with a first electromagnetic switch valve and is arranged outside the test cabin together, the output of the first electromagnetic switch valve is connected into the test cabin through a connecting pipe and is connected with N cooling branches, and the N cooling branches are connected to N cooling channels of the wing leading edge (5); on each cooling branch, the output of the electric regulating pressure valve (2) is connected with the input of the second electromagnetic switch valve (4), and the pressure sensor (3) measures the pressure between the electric regulating pressure valve (2) and the second electromagnetic switch valve (4); according to the distribution condition of the measured values of the heat flow sensors on the wing front edge (5), adjusting the electric adjusting valves (2) on the cooling branches to adjust the pressure of the branches, and improving the air film cooling effect of the wing front edge (5); n is more than or equal to 1.
2. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: the acoustic throat (1) is a contracted circular flow channel, and the large-aperture end is the upstream of the acoustic throat (1) and communicated with the atmosphere; the small-caliber end is the downstream of the sonic throat (1).
3. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: the electric pressure regulating valve (2) and the second electromagnetic switch valve (4) are connected to a cooling branch circuit through a sealing joint, and the pressure sensor (3) is connected to the cooling branch circuit through a three-way valve.
4. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: the vacuum degree in the test chamber is less than 1kPa.
5. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: n cooling air holes are uniformly formed in the front edge (5) of the wing along the direction of the highest heat flow line on the cambered surface, the interval between every two adjacent cooling air holes is 20-30 mm, the diameter of each cooling air hole is 1/10-1/5 of the radius of the cambered surface of the front edge of the wing, and N is larger than or equal to 1.
6. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 5, wherein: the distribution of the positions of the heat flow measuring points is as follows:
symmetrically arranging a heat flow measuring point on each of two sides of each cooling air hole, which are perpendicular to the inflow direction of the spray pipe, by taking the center of the cooling air hole as a center, wherein the distance between each heat flow measuring point and the center of the current cooling air hole is 3-5 mm;
flowing along the spray pipe, arranging a heat flow measuring point on the highest heat flow line at the upstream position of each cooling air hole, wherein the distance between the heat flow measuring point and the center of the cooling air hole is 5-10 mm;
and a heat flow measuring point is arranged between two adjacent cooling air holes.
7. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: the heat flow sensor comprises a heat measuring block, a heat insulation sleeve and a K-type thermocouple, the heat insulation sleeve is sleeved outside the heat measuring block, and the axial bottom end of the heat measuring block is communicated with the K-type thermocouple.
8. The system for testing the leading edge of the active film cooling wing applied to the arc wind tunnel according to claim 1, wherein: the control signal of the electric pressure regulating valve (2) is direct current P-Q milliampere, the current value of the control signal and the opening degree of the valve are in a linear relation, the valve is closed when P milliampere, the valve is fully opened when Q milliampere, P is more than 1, Q is more than 1, P is restricted to Q;
according to the distribution condition of the measured value of the heat flow on the wing leading edge (5), the pressure of each cooling branch is adjusted by adjusting the electric pressure adjusting valve (2), and the method specifically comprises the following steps:
if the heat flow value around the current cooling air hole is higher than the heat flow value at the middle position of the current cooling air hole and the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is large, the current value of the control signal is reduced, the air inlet pressure is reduced, and the air inflow is reduced until the heat flow value of a measuring point around the current cooling air hole is lower than or equal to the heat flow value between the two cooling air holes;
if the heat flow value around the current cooling air hole is lower than the heat flow value between the current cooling air hole and the middle position of the adjacent cooling air hole at the downstream, the air inflow of the current cooling air hole is small, the current value of the control signal is increased, the air inflow pressure is increased, and the air inflow is increased until the heat flow value of a measuring point around the current cooling air hole is higher than or equal to the heat flow value between the two cooling air holes;
the current signal is converted into corresponding linear displacement, and the opening degree of the valve is correspondingly and linearly increased by increasing the current value of the control signal.
9. The air film active cooling wing leading edge test system applied to the electric arc wind tunnel according to claim 1, characterized in that: the mass calculation formula of the cold air source is as follows:
in the above formula, m is the mass of cold air, unit: kg/s;
is the area of the downstream outlet of the sonic throat (1), and the unit is as follows: m is 2 ；p 0 Atmospheric pressure, which is 0.1MPa; t is 0 Is the atmospheric ambient temperature, in units: K.
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| CN202211193714.XA CN115824562A (en) | 2022-09-28 | 2022-09-28 | Active cooling front edge test system applied to air film of electric arc wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211193714.XA CN115824562A (en) | 2022-09-28 | 2022-09-28 | Active cooling front edge test system applied to air film of electric arc wind tunnel |
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