CN105547633A - Subsonic speed wind tunnel force test zero resistance correction method - Google Patents
Subsonic speed wind tunnel force test zero resistance correction method Download PDFInfo
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- CN105547633A CN105547633A CN201510889177.6A CN201510889177A CN105547633A CN 105547633 A CN105547633 A CN 105547633A CN 201510889177 A CN201510889177 A CN 201510889177A CN 105547633 A CN105547633 A CN 105547633A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- General Physics & Mathematics (AREA)
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Abstract
The invention provides a subsonic speed wind tunnel force test zero resistance correction method. According to the method, the dimension of a support rod is partially limited to reduce interference, a correction formula is utilized to correct the zero resistance data acquired through a wind tunnel test, and the zero resistance data can be rapidly and accurately acquired after eliminating interference of the support rod. According to the method, limit on support rod selection is only one parameter, and influence on test design is not great; the correction speed is fast, and correction precision satisfies engineering precision application requirements smaller than 3%. As is proved by tests, the data after correction has the high reduction degree, and the method can realize accurate subsonic speed wind tunnel force test zero resistance measurement.
Description
Technical field
The present invention relates to a kind of subsonic wind tunnel dynamometer check zero and hinder modification method, for the correction of wind tunnel test drag data, belong to test and technical field of measurement and test.
Background technology
In force test in wind tunnel, usually need a lever system at present by model support in wind-tunnel, the effect of a lever system mainly comprises bolster model, connects internal balance, regulates model attitude angle etc.Aircraft is there is not a lever system in Live Flying, because the existence of a lever system will certainly have an impact to model Flow Field (especially afterbody flow field) and then have influence on aerodynamic force (especially resistance) measured value.Research shows, the existence of a lever system changes the pressure distribution of model rear and bottom, forms a malleation field of force, form a negative axial force to model at afterbody, hinders reduction 20% ~ 50% before causing model.The geometric parameter of support sting is very large on base pressure impact, wherein D
s/ D
b, L
0/ D
btwo parameter influences are maximum.
At present, the conventional resistance processing mode of force test in wind tunnel is consistent with front far away incoming flow static pressure for being modified to by base pressure, and both base drag was zero.Specific practice for 2 foundation pressure pipe measurement model afterbody pressure, adds in the resistance of balance measurement after the difference then calculating itself and front far away incoming flow static pressure is multiplied by model bottom area and carries out changing.This way can revise the interference that pole is brought to a certain extent, but there is the situations such as shock wave for causing the uneven and afterbody of model afterbody pressure distribution in the too short and high pressure velocity of sound situation of the straight sections such as pole, local pressure is measured can not reflect afterbody flow field overall picture, and the resistance therefore obtained by aforesaid way process still exists larger pole interference.For the impact avoiding pole strong jamming to cause resistance, current correction work is mainly carried out from two aspects: select suitable pole parameter to reduce pole interference on the one hand as far as possible; On the other hand numerical evaluation revised law is utilized to revise keeping away in unavoidable strongly disturbing situation.All there is limitation in above two kinds of methods: owing to will ensure strength and stiffness and the position of model in flow field of pole, and satisfactory pole parameter is difficult to be met simultaneously; Value revision method calculated amount is large, consuming time for viscous effect dyscalculia longlyer cannot carry out real-time correction and provide test findings fast.
Summary of the invention
An object of the present invention is to solve at least the problems referred to above, and the advantage will illustrated at least is below provided.
Technology of the present invention is dealt with problems and is: provide a set of and hinder modification method based on force test in wind tunnel under subsonic zero, by part restriction pole size to reduce premised on interference, correction formula is utilized to revise in real time zero resistance that wind tunnel test records, the accurate zero resistance data after the pole that is finally eliminated interference.
Technical scheme of the present invention is:
A kind of subsonic speed dynamometer check zero hinders modification method, and it comprises the following steps:
(1) moulded dimension is calculated according to the size of wind-tunnel, load value and model internal space requirements;
(2) the gentle support sting size in test sky is determined according to intensity, rigidity requirement and the model status requirement in wind-tunnel;
(3) carry out subsonic wind tunnel test according to the model in step (1) and step (2) and support sting, before obtaining wind axes, hinder coefficient C
dF surveys;
(4) moulded dimension obtained according to step (1) and step (2) and support sting size, determine to expose the straight section distance L such as model trailing strut
0, and according to exposing the straight section distance L such as model trailing strut
0with model afterbody equivalent diameter D
bobtain ratio L
0/ D
b;
(5) parameter will obtained in above-mentioned steps: model blockage ratio ε, support sting first half expand angle θ
1, support sting is later half expands angle θ
2, subsonic wind tunnel test Mach number and ratio L
0/ D
bas judging parameter;
(6) if judge that parameter meets correction conditions, before carrying out wind axes, coefficient C is hindered
dF surveyscorrection, obtain resistance coefficient C before revised wind axes
dF repaiies.
Preferably, described subsonic speed dynamometer check zero hinders in modification method, and correction conditions is:
A. model blockage ratio ε is not more than 1%;
B. support sting first half expands angle θ
1be less than 1.5 °, support sting is later half expands angle θ
2be less than 8.5 °;
C. subsonic wind tunnel test Mach number 0.4≤M≤0.95 in step (3);
D. ratio L
0/ D
b<6.
Preferably, described subsonic speed dynamometer check zero hinders in modification method, and correction formula is: C
dF repaiies=C
dF surveys╳ [1+0.032164 ╳ (6-L
0/ D
b)]
The present invention's beneficial effect is compared with prior art:
To pole selectional restriction few (only a restriction parameter), little on test design impact;
Erection rate is fast, revises precision and meets the meticulous application requirement (being less than 3%) of engineering.
Part is embodied by explanation below by other advantage of the present invention, target and feature, part also will by research and practice of the present invention by those skilled in the art is understood.
Accompanying drawing explanation
Fig. 1 is the process flow diagram that subsonic wind tunnel dynamometer check zero provided by the invention hinders modification method;
Fig. 2 is support sting geometric parameter figure;
Fig. 3 is that different strut lengths drag measures zero resistance with Mach number change curve;
Fig. 4 is that different strut lengths drag correction zero hinders with Mach number change curve;
Fig. 5 is that different strut lengths drag measures zero resistance relative error with Mach number change curve;
Fig. 6 is that different strut lengths drag correction zero hinders relative error with Mach number change curve.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail, can implement according to this with reference to instructions word to make those skilled in the art.
Should be appreciated that used hereinly such as " to have ", other element one or more do not allotted in " comprising " and " comprising " term or the existence of its combination or interpolation.
As shown in Figure 1, the present invention is to reduce premised on interference by part restriction pole size, correction formula is utilized to revise in real time zero resistance that wind tunnel test records, accurate zero resistance data after the pole that is finally eliminated interference, the engine met the demands for accurately choosing thrust provides data supporting.
The present invention includes step as follows:
(1) comprehensive tunnel size, magnitude of load and model internal space requirements Confirming model contracting is than size, requires that model blockage ratio ε is not more than 1%;
(2) determine the gentle support sting size in test sky according to intensity, rigidity requirement and the model status requirement in wind-tunnel, require that support sting first half expands angle θ
1be less than 1.5 °, support sting is later half expands angle θ
2be less than 8.5 °;
(3) carry out subsonic wind tunnel test, before obtaining conventional wind axes, hinder coefficient C
dF surveys;
(4) determine to expose the straight section distance L such as model trailing strut
0with model afterbody equivalent diameter D
bratio L
0/ D
bconcrete numerical value;
(5) judge whether to meet correction conditions, carry out zero resistance correction if met by following formula, if do not met, do not revise.Correction conditions and correction formula as follows:
Test Mach number 0.4≤M≤0.95
Expose the ratio L of the straight section distances such as model trailing strut and model afterbody equivalent diameter
0/ D
b<6
C
dF repaiies=C
dF surveys╳ [1+0.032164 ╳ (6-L
0/ D
b)]
(6) by step (1)-step (5) can be eliminated pole interference wind tunnel test zero hinder test figure.
What in this method, the computational accuracy of correction formula recorded with test frontly hinders C
dF surveysrelevant, C
dF surveyscalculating need use the model base pressure measured in test, therefore arrange when designing a model that suitable bottom pressure stabilizing chamber is very helpful to raising corrected Calculation precision to improve model bottom pressure measurement accuracy.
The course of work of the present invention is further illustrated below with an instantiation.
As shown in Figure 2, wherein, 1 is balance, 2 is model, and 3 is support sting, and 4 is support, carry out once sub-transonic wind tunnel dynamometer check design, test is carried out at the sub-transonic wind tunnel of a test section size 0.6 meter of magnitude, and test Mach number 0.5≤M≤1.05, model is a rotational symmetry low aspect ratio normal arrangement guided missile.
By step (1) according to Model load, blockage ratio, pole rigidity, intensity and the model status requirement in Flow Field in Wind Tunnel considers, and selected model contracting is than being 1:2, and model total length 412, maximum gauge 45mm, maximum obstruction is than 0.73%.
Carry out step (2) and choose support sting size, for verifying the validity of correction formula, select the pole of three kinds of different lengths to test, the parameter of three kinds of poles is respectively:
D
s/D
b＝0.47、θ1＝0.73°、θ2＝7.73°、L1＝260mm
D
s/D
b＝0.56、θ1＝1.15°、θ2＝8.32°、L1＝350mm
D
s/D
b＝0.63、θ1＝0.78°、θ2＝8.20°、L1＝396mm
Model and a lever system are installed and carried out force test in wind tunnel, step (3), carries out hindering (zero resistance) measurement coefficient C before conventional processing obtains wind axes to the data that balance records
dF surveys, as shown in Figure 3.Carry out step (4) afterwards, determine to expose the straight section distance L such as model trailing strut
0with model afterbody equivalent diameter D
bratio L
0/ D
bconcrete numerical value, three kinds of poles are respectively: L
0/ D
b=1.97, L
0/ D
b=4.34, L
0/ D
b=5.55.
Because test condition and three kinds of pole parameters all meet correction conditions, step (5) can be carried out and by correction formula, C is hindered to measurement zero
dF surveysrevise, after the correction corresponding with Fig. 3, data are shown in Fig. 4.So far zero resistance correction work completes, and after revising, data can be used as test final data and provide use.
Fig. 5, Fig. 6 are the relative error curve before and after zero resistance data correction, and data show, zero resistance data of unmodified produce larger error by pole disturbing effect, parameter L
0/ D
bthe error that the pole of=1.97 produces generally more than 10%, parameter L
0/ D
bthe maximum error that the pole of=4.34 produces is 6%, L
0/ D
bthe pole maximum error of=5.55 also has 4%, can not meet technical requirement (less than 3%) to the above-mentioned data revised of the test that drag data accuracy requirement is higher.After correction formula correction, under three kinds of bar states when Mach number is not more than 0.95 maximum relative error about 2%, higher precision has been reached for resistance test data, meet the meticulous application requirement (being less than 3%) of engineering, prove that modification method of the present invention is ripe, effective.Use in Case Experiments On A without pole interference data be same external form guided missile at home many large scale wind-tunnel carry out the wind tunnel data of full-scale test and the result of numerical evaluation aggregation of data, through the textual criticism of flying demonstration checking telemetry, the normal data that these data can be used as without pole interference uses.
Although embodiment of the present invention are open as above, but it is not restricted to listed in instructions and embodiment utilization, it can be applied to various applicable the field of the invention completely, for those skilled in the art, can easily realize other amendment, therefore do not deviating under the universal that claim and equivalency range limit, the present invention is not limited to specific details and illustrates here and the legend described.
Claims (3)
1. subsonic speed dynamometer check zero hinders a modification method, it is characterized in that, comprises the following steps:
(1) moulded dimension is calculated according to the size of wind-tunnel, load value and model internal space requirements;
(2) the gentle support sting size in test sky is determined according to intensity, rigidity requirement and the model status requirement in wind-tunnel;
(3) carry out subsonic wind tunnel test according to the model in step (1) and step (2) and support sting, before obtaining wind axes, hinder coefficient C
dF surveys;
(4) moulded dimension obtained according to step (1) and step (2) and support sting size, determine to expose the straight section distance L such as model trailing strut
0, and according to exposing the straight section distance L such as model trailing strut
0with model afterbody equivalent diameter D
bobtain ratio L
0/ D
b;
(5) parameter will obtained in above-mentioned steps: model blockage ratio ε, support sting first half expand angle θ
1, support sting is later half expands angle θ
2, subsonic wind tunnel test Mach number and ratio L
0/ D
bas judging parameter;
(6) if judge that parameter meets correction conditions, before carrying out wind axes, coefficient C is hindered
dF surveyscorrection, obtain resistance coefficient C before revised wind axes
dF repaiies.
2. subsonic speed dynamometer check zero as claimed in claim 1 hinders modification method, and it is characterized in that, correction conditions is:
A. model blockage ratio ε is not more than 1%;
B. support sting first half expands angle θ
1be less than 1.5 °, support sting is later half expands angle θ
2be less than 8.5 °;
C. subsonic wind tunnel test Mach number 0.4≤M≤0.95 in step (3);
D. ratio L
0/ D
b<6.
3. subsonic speed dynamometer check zero as claimed in claim 2 hinders modification method, and it is characterized in that, correction formula is: C
dF repair=C
dF surveys╳ [1+0.032164 ╳ (6-L
0/ D
b)].
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| CN201510889177.6A CN105547633A (en) | 2015-12-07 | 2015-12-07 | Subsonic speed wind tunnel force test zero resistance correction method |
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|---|---|---|---|
| CN201510889177.6A CN105547633A (en) | 2015-12-07 | 2015-12-07 | Subsonic speed wind tunnel force test zero resistance correction method |
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| CN105547633A true CN105547633A (en) | 2016-05-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring force of interference of jet flow of upstream air for high-speed wind tunnel |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07260622A (en) * | 1994-03-28 | 1995-10-13 | Mitsubishi Heavy Ind Ltd | Resistance measuring apparatus for sample |
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
-
2015
- 2015-12-07 CN CN201510889177.6A patent/CN105547633A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07260622A (en) * | 1994-03-28 | 1995-10-13 | Mitsubishi Heavy Ind Ltd | Resistance measuring apparatus for sample |
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
Non-Patent Citations (3)
| Title |
|---|
| 刘仙名: "战术导弹标模零升阻力相关性修正", 《航空兵器》 * |
| 杜绵银: "巡航导弹风洞试验阻力测量研究", 《第二届全国低跨超声速空气动力学交流会论文集》 * |
| 王一飞: "CK-1C靶机风洞模型实验数据的修正和使用", 《南京航空学院学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring force of interference of jet flow of upstream air for high-speed wind tunnel |
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Application publication date: 20160504 |
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