CN104296957A - Method and system for measuring water drop collecting coefficient of aerodynamic surface - Google Patents
Method and system for measuring water drop collecting coefficient of aerodynamic surface Download PDFInfo
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- CN104296957A CN104296957A CN201410461886.XA CN201410461886A CN104296957A CN 104296957 A CN104296957 A CN 104296957A CN 201410461886 A CN201410461886 A CN 201410461886A CN 104296957 A CN104296957 A CN 104296957A
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- power density
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Abstract
The invention provides a method and system for measuring a water drop collecting coefficient of an aerodynamic surface. The method comprises the steps that the aerodynamic surface is heated to the preset outer surface temperature with the first power density under the dry air with the specific speed and the specific temperature; the aerodynamic surface is heated to the preset outer surface temperature with the second power density under the wet air with the specific speed and the specific temperature, wherein the wet air comprises the specific liquid water content; the water drop collecting coefficient of the aerodynamic surface is obtained based on the specific speed, the specific temperature, the liquid water content, the first power density, the second power density and the preset outer surface temperature. According to the method and system, the water drop collecting coefficient on the aerodynamic surface under any state can be continuously measured, and the method and system are especially used for measuring the water drop collecting coefficient of the aerodynamic surface such as wings and engine air inlets of an airplane.
Description
Technical field
The present invention relates to a kind of method and system measuring the drop collection coefficient on aerodynamic force surface.
Background technology
When carrying out anti-icing or icing simulation analysis, need the hot-fluid solving hot-fluid and water droplet kinetic energy needed for water evaporative heat loss, heating super-cooling waterdrop, three hot-fluids need to solve the shock water yield striking surface, and clashing into the water yield needs to solve this surperficial water droplet collection coefficient.Wherein, clashing into the water yield is drop collection factor beta, air velocity V
0with the function of the Liquid water content LWC in air.For the accuracy of the drop collection coefficient of verification computation software or program computation, need to be measured drop collection coefficient by test.
Known drop collection coefficient method is bibulous paper decoration method.Bibulous paper is arranged in measured surface, and the region bibulous paper color that droplets impact its is many is more black, and the field color that droplets impact its is few is more shallow.Check in the shock water yield according to colour atla, then obtain drop collection coefficient according to the shock water yield and Measuring Time.At list of references " C.S.Bidwell, Cleveland, OH., S.R.Mohler, Jr.etc.. ' Collection Efficiency and Ice Accretion Calculations for a Sphere, a Swept MS (1)-317Wing, a Swept NACA-0012Wing Tip, an Axisymmetric Inlet, and a Boeing737-300Inlet ' AIAA-95-0755 " in adopt the method at the LEWIS icing tunnel of US National Aeronautics and Space Administration (NASA) respectively to spheroid, MS-317 aerofoil profile, NACA-0012 aerofoil profile, a kind of symmetrical engine intake and B737-300 engine intake, measure respective drop collection coefficient, verify the accuracy of LEWICE3D program computation drop collection coefficient.
Bibulous paper staining method is simple to operate, but is limited by the restriction of bibulous paper water-intake capacity, the soft air that liquid towards liquid water content is larger, bibulous paper supersaturation in the short time, to such an extent as to cannot Measurement accuracy.And under each state, need to change bibulous paper, therefore cannot carry out continuous coverage to different conditions.
Summary of the invention
The object of this invention is to provide a kind of method measuring the drop collection coefficient on aerodynamic force surface, the method can measure the drop collection coefficient on the aerodynamic force surface under any state by continuous print, especially for the drop collection coefficient on the aerodynamic force surface (such as, wing, engine intake etc.) of survey aircraft.
According to an aspect of the present invention, provide a kind of method of the drop collection coefficient for measuring aerodynamic force surface, said method comprising the steps of: under the dry air of specific speed and specified temp, heat described aerodynamic force surface to predetermined hull-skin temperature with the first power density; Under the soft air of described specific speed and described specified temp, heat described aerodynamic force surface to described predetermined hull-skin temperature with the second power density, described soft air has particular liquid liquid water content; And based on described specific speed, described specified temp, described Liquid water content, described first power density, described second power density and described predetermined hull-skin temperature, obtain the described drop collection coefficient on described aerodynamic force surface.
In one embodiment, described first power density is unified value, and described second power density is distribution, and described predetermined hull-skin temperature is distribution.
In another embodiment, described first power density is distribution, and described second power density is distribution, and described predetermined hull-skin temperature is unified value.
The subcooled water that described predetermined hull-skin temperature is set to make to strike described aerodynamic force surface evaporates completely at shock place.Such as, described predetermined hull-skin temperature is greater than 40 DEG C.
Advantageously, described obtaining step comprises:
-based on described second power density q
swith described first power density q
g, and according to following formula, rated output density increment Δ q
Δq＝q
s-q
g；
-based on described power density increment Delta q, described predetermined hull-skin temperature t
s, described specified temp t
0with described specific speed V
0, and according to following formula, calculate and clash into water yield W
Wherein said κ is coefficient of efficiency, characterizes and is delivered to the described power density on aerodynamic force surface and the ratio of heating power density, described C
wfor specific heat of water, described L
efor evaporation of water latent heat;
-based on described shock water yield W, described Liquid water content LWC and described specific speed V
0, and according to following formula, calculate described drop collection factor beta
According to another aspect of the present invention, provide a kind of system of the drop collection coefficient for measuring aerodynamic force surface, described system comprises: heater assembly, and it is arranged on described aerodynamic force on the surface, and is configured to heat described aerodynamic force surface; Temperature sensor assembly, it is arranged on described aerodynamic force on the surface, and is configured to the hull-skin temperature measuring described aerodynamic force surface; And controller, it is coupled to described heater assembly and described temperature sensor assembly respectively, and be configured to: based on the feedback of described temperature sensor assembly, control described heater assembly under the dry air of specific speed and specified temp, heat described aerodynamic force surface to predetermined hull-skin temperature with the first power density; Adjust the power density of described heater assembly, and under the soft air of described specific speed and described specified temp, heat described aerodynamic force surface to described predetermined hull-skin temperature with the second power density, described soft air has particular liquid liquid water content; And based on described specific speed, described specified temp, described Liquid water content, described first power density, described second power density and described predetermined hull-skin temperature, calculate the described drop collection coefficient on described aerodynamic force surface.
In one embodiment, described first power density is unified value, and described second power density is distribution, and described predetermined hull-skin temperature is distribution.
In another embodiment, described first power density is distribution, and described second power density is distribution, and described predetermined hull-skin temperature is unified value.
Advantageously, described heater assembly comprise be attached to described aerodynamic force surface inside surface on one group of well heater, described temperature sensor assembly comprise be attached to described aerodynamic force surface outside surface on one group of temperature sensor, and each temperature sensor is arranged on the center of each well heater by correspondence.
Two kinds of heating modes described above are only two embodiments realizing goal of the invention of the present invention, and be understandable that, heating mode of the present invention is not limited to above-mentioned ad hoc fashion.
Advantageously, described controller is configured to the power density of each well heater adjusted individually in described one group of well heater.
Advantageously, described system also comprises: insulation course, and it is between described aerodynamic force surface and described heater assembly; Heat insulation layer, it is positioned at described heater assembly inside surface.
Accompanying drawing explanation
Preferred implementation by describing in detail below in conjunction with accompanying drawing is understood by further feature of the present invention and advantage better, in accompanying drawing, and the same or analogous parts of identical designated, wherein:
Fig. 1 shows the schematic diagram on aerodynamic force surface according to an embodiment of the invention;
Fig. 2 shows the system of the drop collection coefficient on measurement aerodynamic force surface according to an embodiment of the invention.
Embodiment
Specifically describe the architectural feature of the system of the drop collection coefficient according to measurement aerodynamic force surface of the present invention, principle of work and the course of work below.Here, the structural design drawing of example only understands the present invention for being convenient to, but not makes concrete restriction to architectural feature of the present invention.In addition, in specific descriptions below, the term of directivity, such as upper and lower, top etc. all use with reference to the direction described in accompanying drawing, and the term of these directivity is only unrestricted for example.Therefore, the embodiment that the structural design drawing of example and following description the present invention combine is not intended to limit according to all embodiments of the present invention.
Fig. 1 shows the schematic diagram on aerodynamic force surface according to an embodiment of the invention.In figure, the aerodynamic force surface of example is aircraft wing.Be understandable that, the aerodynamic force surface related in the present invention is not limited to aircraft wing, and it can also be aircraft engine air intake opening etc.The technical scheme of various embodiments of the present invention is used for the drop collection coefficient on the exemplary aerodynamic force surface of survey sheet 1.
Fig. 2 shows the system 20 of the drop collection coefficient on measurement aerodynamic force surface according to an embodiment of the invention.This system 20 comprises heater assembly 201, and it is arranged on aerodynamic force surface 30, such as, on the inside surface 301 on aerodynamic force surface 30, for heating aerodynamic force surface.Advantageously, can arrange an insulation course 205 between the inside surface 301 on heater assembly 201 and aerodynamic force surface 30, heater assembly 201 then can arrange a heat insulation layer 206 relative on the another side on aerodynamic force surface 30.
This heater assembly 201 such as can comprise one group of well heater.Advantageously, adiabatic and insulating material 207 can be furnished with between each well heater.Well heater can be any suitable heater element such as resistance wire, resistive film.The number of well heater can be determined according to the area on measured aerodynamic force surface.Usually, there is certain curvature (see Fig. 1) on aerodynamic force surface, and therefore, advantageously, well heater is flexible, thus can be adjacent to the inside surface on aerodynamic force surface.Well heater can adopt heat conductive silica gel to be bonded on the inside surface on aerodynamic force surface, certainly, other suitable connected modes be also applicable to well heater is connected to aerodynamic force surface inside surface on.
Still with reference to Fig. 2, system 20 also comprises temperature sensor assembly 202, and it is arranged on aerodynamic force surface 30, such as, on the outside surface 303 on aerodynamic force surface 30, for measuring the hull-skin temperature on aerodynamic force surface.Such as, temperature sensor assembly 202 can comprise one group of temperature sensor.Advantageously, each temperature sensor can be arranged on the center of each well heater by correspondence.
Temperature sensor can be the sensor of the micro volume types such as such as thermopair.Temperature sensor can adopt bonding or other connected modes be applicable to be fixed on aerodynamic force on the surface.In order to not affect surface flow field, advantageously, multiple groove can be set on the outside surface 303 on aerodynamic force surface 30, each temperature sensor is imbedded in groove, and after filling heat conductive silica gel or other highly heat-conductive materials, milling is put down.
System 20 also comprises controller 203, it is coupled to heater assembly 201 and temperature sensor assembly 202 respectively, aerodynamic force surface 30 is heated for control heater assembly 201, and for obtaining the hull-skin temperature on the aerodynamic force surface 30 that temperature sensor assembly 202 measures.Such as, for group temperature sensor of in temperature sensor assembly 202, it can make connecting line be connected to controller 203 by the pore of respective bottom portion of groove and through the inside surface on aerodynamic force surface respectively.One group of well heater in heater assembly 201 can be connected to controller respectively by connecting line.Advantageously, the heating power of each well heater in heater assembly 201 can be controlled individually by controller 203.
Be in operation, each well heater in controller 203 control heater assembly 201 under the dry air of specific speed and specified temp, with the first power density heating aerodynamic force surface 30 to predetermined hull-skin temperature; Then controller 203 adjusts the power density of each well heater in heater assembly 201, and at identical specific speed and identical specified temp, and under the soft air of particular liquid liquid water content, with the second power density heating aerodynamic force surface 30 to this predetermined hull-skin temperature.
The subcooled water that this predetermined hull-skin temperature is set to make to strike described aerodynamic force surface evaporates completely at shock place.Such as, this predetermined hull-skin temperature is for being greater than 40 DEG C.
In one embodiment, controller 203 each well heater first in control heater assembly 201 with identical a kind of power density (is also, each power density values in first power density is identical) heating aerodynamic force surface 30, and obtain predetermined hull-skin temperature by temperature sensor assembly 202 measurement.Because the local flow field of aerodynamic surface is different with For Determining The Droplet Trajectories, therefore, each well heater measures the predetermined hull-skin temperature that obtains for distribution afterwards with identical a kind of power density heating aerodynamic force surface, also namely, the hull-skin temperature on the aerodynamic force surface in whole heating region is different with the change of locus.Then, under the soft air of identical specific speed and identical specified temp and particular liquid liquid water content, the power density that controller 203 adjusts each well heater heats aerodynamic force surface 30 to another kind of power density (each power density values in the second power density is different), and obtain described predetermined hull-skin temperature (also namely, consistent with the hull-skin temperature be heated under dry air) by temperature sensor assembly 202 measurement.
In another embodiment, first controller 203 regulates the power density of each well heater in heater assembly 201 to heat aerodynamic force surface 30, make the temperature of each measurement point identical, and obtain predetermined hull-skin temperature (this predetermined hull-skin temperature is unified value, is also that the hull-skin temperature in whole heating region is consistent) by temperature sensor assembly 202 measurement.Because the local flow field of aerodynamic surface is different with For Determining The Droplet Trajectories, for reaching identical Temperature Distribution, the heating power density difference (each power density values also namely, in the first power density is different) required for each well heater.Then, under the soft air of identical specific speed and identical specified temp and particular liquid liquid water content, power density to the second power density (each power density values in the second power density is different) that controller 203 adjusts each well heater heats aerodynamic force surface 30, and obtain this predetermined hull-skin temperature (also namely, consistent with the hull-skin temperature be heated under dry air) by temperature sensor assembly 202 measurement.
Finally, controller 203, based on specific speed, specified temp, Liquid water content, the first power density, the second power density and predetermined hull-skin temperature, obtains the drop collection coefficient on aerodynamic force surface 30.
Such as, controller 203 can obtain the drop collection coefficient on aerodynamic force surface 30 in the following manner.Particularly, first, controller 203 is based on the second power density q
swith the first power density q
g, and according to following formula, rated output density increment Δ q
Δq＝q
s-q
g。
Then, controller 203 is based on power density increment Delta q, predetermined hull-skin temperature t
s, specified temp t
0with specific speed V
0, and according to following formula, calculate and clash into water yield W
Wherein, κ is coefficient of efficiency, characterizes and is delivered to the power density on aerodynamic force surface and the ratio of heating power density, C
wfor specific heat of water, L
efor evaporation of water latent heat.
Then, controller 203 is based on shock water yield W, Liquid water content LWC and specific speed V
0, and according to following formula, calculate drop collection factor beta
Controller 203 can be such as microprocessor.
Technology contents of the present invention and technical characterstic have disclosed as above, should be understood that, above-mentioned embodiment exists many alter modes, and these modes are clearly concerning various equivalent modifications.These amendment/modification fall into association area of the present invention, also should be included in the scope of appended claim.
Claims (6)
1., for measuring a method for the drop collection coefficient on aerodynamic force surface, said method comprising the steps of:
-under the dry air of specific speed and specified temp, heat described aerodynamic force surface to predetermined hull-skin temperature with the first power density;
-under the soft air of described specific speed and described specified temp, heat described aerodynamic force surface to described predetermined hull-skin temperature with the second power density, described soft air has particular liquid liquid water content;
-based on described specific speed, described specified temp, described Liquid water content, described first power density, described second power density and described predetermined hull-skin temperature, obtain the described drop collection coefficient on described aerodynamic force surface.
2. method according to claim 1, is characterized in that, the subcooled water that described predetermined hull-skin temperature is set to make to strike described aerodynamic force surface evaporates completely at shock place.
3. method according to claim 1, is characterized in that, described obtaining step comprises:
-based on described second power density q
swith described first power density q
g, and according to following formula, rated output density increment Δ q
Δq＝q
s-q
g；
-based on described power density increment Delta q, described predetermined hull-skin temperature t
s, described specified temp t
0with described specific speed V
0, and according to following formula, calculate and clash into water yield W
Wherein said κ is coefficient of efficiency, characterizes and is delivered to the described power density on aerodynamic force surface and the ratio of heating power density, described C
wfor specific heat of water, described L
efor evaporation of water latent heat;
-based on described shock water yield W, described Liquid water content LWC and described specific speed V
0, and according to following formula, calculate described drop collection factor beta
4., for measuring a system for the drop collection coefficient on aerodynamic force surface, described system comprises:
Heater assembly, it is arranged on described aerodynamic force on the surface, and is configured to heat described aerodynamic force surface;
Temperature sensor assembly, it is arranged on described aerodynamic force on the surface, and is configured to the hull-skin temperature measuring described aerodynamic force surface;
Controller, it is coupled to described heater assembly and described temperature sensor assembly respectively, and is configured to:
Based on the feedback of described temperature sensor assembly, control described heater assembly under the dry air of specific speed and specified temp, heat described aerodynamic force surface to predetermined hull-skin temperature with the first power density;
Adjust the power density of described heater assembly, and under the soft air of described specific speed and described specified temp, heat described aerodynamic force surface to described predetermined hull-skin temperature with the second power density, described soft air has particular liquid liquid water content; And
Based on described specific speed, described specified temp, described Liquid water content, described first power density, described second power density and described predetermined hull-skin temperature, calculate the described drop collection coefficient on described aerodynamic force surface.
5. system according to claim 4, is characterized in that, the subcooled water that described predetermined hull-skin temperature is set to make to strike described aerodynamic force surface evaporates completely at shock place.
6. system according to claim 4, is characterized in that, described controller is configured to further:
-based on described second power density q
swith described first power density q
g, and according to following formula, rated output density increment Δ q
Δq＝q
s-q
g；
-based on described power density increment Delta q, described predetermined hull-skin temperature t
s, described specified temp t
0with described specific speed V
0, and according to following formula, calculate and clash into water yield W
Wherein said κ is coefficient of efficiency, characterizes and is delivered to the described power density on aerodynamic force surface and the ratio of heating power density, described C
wfor specific heat of water, described L
efor evaporation of water latent heat;
-based on described shock water yield W, described Liquid water content LWC and described specific speed V
0, and according to following formula, calculate described drop collection factor beta
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Cited By (6)
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| US10435161B1 (en) | 2018-05-02 | 2019-10-08 | Rosemount Aerospace Inc. | Surface sensing for droplet size differentiation |
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| CN111537182A (en) * | 2020-05-28 | 2020-08-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Power configuration method for hypersonic wind tunnel directly-heated electric heater |
| US11472562B2 (en) * | 2019-06-14 | 2022-10-18 | Rosemount Aerospace Inc. | Health monitoring of an electrical heater of an air data probe |
| US11639954B2 (en) | 2019-05-29 | 2023-05-02 | Rosemount Aerospace Inc. | Differential leakage current measurement for heater health monitoring |
| US11930563B2 (en) | 2019-09-16 | 2024-03-12 | Rosemount Aerospace Inc. | Monitoring and extending heater life through power supply polarity switching |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US10435161B1 (en) | 2018-05-02 | 2019-10-08 | Rosemount Aerospace Inc. | Surface sensing for droplet size differentiation |
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