CN114323540A - Half-mode blowing lift-increasing wind tunnel test method and device for conveyor - Google Patents
Half-mode blowing lift-increasing wind tunnel test method and device for conveyor Download PDFInfo
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Abstract
The invention discloses a half-mode blowing lift-increasing wind tunnel test method and a half-mode blowing lift-increasing wind tunnel test device for a conveyor, wherein the test method comprises the following steps: step a: calibrating the influence of high-pressure air on the balance load after the high-pressure air passes through the air bridge; step b: mounting a test device and a test model, and adjusting the attitude angle of the test model to a zero point; step c: calibrating a momentum coefficient; step d: adjusting the attitude angle of the test model to zero, and collecting an initial reading; step e: adjusting the wind speed to a test wind speed, and adjusting the blowing momentum coefficient to a test state; step f: adjusting the attitude angle of the test model, and recording a balance signal, an attitude angle signal, a pressure sensor signal and a temperature sensor signal; step g: processing balance data; step h: balance data was analyzed. By adopting the semi-module blowing and lift-increasing wind tunnel test method and the test device for the conveyor, the accuracy of blowing parameter control and aerodynamic force measurement is improved; reliable wind tunnel test data are provided for the evaluation of the blowing and lift-increasing pneumatic performance of the transport aircraft.
Description
Technical Field
The invention relates to a half-mode blowing lift-increasing wind tunnel test method for a conveyor, and belongs to the technical field of wind tunnel tests.
Background
The wings of modern transportation aircraft are often provided with movable parts such as front and rear edge flaps, slats and the like. The shape of the surface of the wing can be changed within a certain range by controlling the deflection of the movable parts, and the airflow directions of the upper surface and the lower surface of the wing are influenced, so that the lifting force of the wing is increased, and the aim of improving the take-off and landing performance of the airplane is fulfilled. The flow field becomes very complicated by the seam between the movable control surfaces such as slat, flap and the like, wherein the flow field comprises boundary transition, flow separation, mutual interference of wake flow and the like, and the complicated flow phenomena influence the flow quality on the airfoil surface, thereby bringing a series of problems of overlarge noise, increased oil consumption and the like.
The flap blowing lift-increasing technology is characterized in that partial airflow of an engine (air compressor) is led out, the energy of the airflow on the surfaces of wings and flaps is increased by means of the jetting effect of the airflow, boundary layer control is effectively carried out to increase the circulation of the wings, and therefore the purpose of improving the maximum lift coefficient is achieved. The flap blowing high lift technology has wide application prospect because the constraint conditions of the traditional high lift device on structure, aerodynamics and system are avoided and the take-off and landing distance of the airplane can be further shortened.
Wind tunnel testing has been and is now the primary means of discovering and validating flow phenomena, exploring and revealing flow mechanisms, seeking and understanding flow laws, and providing superior aerodynamic layout and aerodynamic performance data for aircraft design. The wind tunnel test can accurately control test conditions such as the speed, pressure, temperature and the like of airflow, and the simulation is real and reliable in general; compared with theoretical research and scientific calculation, the data precision of the wind tunnel test is higher.
The development of flap blowing lift-increasing tests in wind tunnels must follow certain similarity criteria, which require similar momentum coefficients in addition to the geometric similarity and flow similarity of conventional wind tunnel tests. The momentum coefficient is related to the flow and the speed of the blowing slot, so how to accurately measure and control the momentum coefficient is the difficulty of the flap blowing lift-increasing wind tunnel test.
When high-pressure airflow acts on a wing surface flow field in the flap blowing and lift increasing technology, the flow field around the wing becomes very complex, and an accurate result is difficult to be given by a calculation method at present. In recent years, with the improvement of performance requirements of domestic transport aircraft, flap blowing high lift technology is receiving more and more attention. A flap blowing high lift wind tunnel test method is researched, and is a key for further perfecting a test technical system of a high lift device of a transportation aircraft.
Disclosure of Invention
The invention aims to: aiming at the existing problems, the invention provides a half-mode blowing and lift-increasing wind tunnel test method for a conveyor, which improves the accuracy of blowing parameter control and aerodynamic force measurement; reliable wind tunnel test data are provided for the evaluation of the blowing and lift-increasing pneumatic performance of the transport aircraft.
The technical scheme adopted by the invention is as follows:
a half-mode blowing lift-increasing wind tunnel test method for a conveyor comprises the following steps:
step a: carrying out calibration of the influence of high-pressure air on balance load after the high-pressure air passes through an air bridge, wherein the calibration comprises pressure influence calibration, temperature influence calibration and flow influence calibration;
step b: mounting a test device and a test model, and adjusting the attitude angle of the test model to a zero point;
step c: calibrating a momentum coefficient, and recording the flow and the position of a needle valve of each channel flow control unit;
step d: adjusting the attitude angle of the test model to zero, and collecting an initial reading;
step e: adjusting the wind speed to a test wind speed, and adjusting the blowing momentum coefficient to a test state;
step f: adjusting the attitude angle of the test model, and recording balance signals, attitude angle signals, pressure sensor signals and temperature sensor signals after the rapid pressure is stable;
step g: processing balance data according to a flap blowing data processing method;
step h: and d, analyzing balance data, ending the test if the data are normal, and returning to the step c for testing again after the test device and the model are checked if the data are abnormal.
Preferably, in step a, the pressure influence calibration is as follows: sealing the air outlet, pressurizing the air bridge, and recording the relation between the pressure and the balance output; the temperature effect calibration is: using a standard spray pipe, ventilating and heating the air bridge, and recording the relationship between the temperature of the air bridge and the output of the balance in the natural cooling process of the air bridge; the flow effect calibration is: obtained using a standard nozzle forward and reverse jet.
Preferably, the flow rate in step c is measured by a venturi flow meter in the flow control unit.
Preferably, in step c, the momentum coefficient is represented by the formula
Obtaining, wherein mjMeasuring mass flow, U, by a Venturi flowmeterjThe speed of an outlet of the blowing seam is shown, q is the test rapid pressure, and S' is the reference area of the blowing airfoil;
the outlet velocity of the blowing gap is represented by the formula
Obtaining wherein p is0For the pressure in the pressure chamber, P, measured by the pressure sensoraIs atmospheric pressure, R is the gas constant, T0Gamma is the specific heat capacity value of air for the total temperature of the gas.
Preferably, in step h, the data processing comprises the following steps in sequence:
subtraction of readings: subtracting the windless original data from the windy original data corresponding to the attitude angle of the model;
balance formula calculation: calculating the pneumatic load of the test model according to a balance formula by subtracting the data of the initial reading;
conversion of moment center: the first step is as follows: coordinate translation, namely translating the origin of a balance shaft system to the origin of the body axis coordinate of the model; the second step is that: coordinate rotation (namely a rotor axis), namely rotating the translated balance axis to form a model body axis by taking the origin of coordinates of the model body axis as the center; (in the case where the moment reference point (generally the position of the centre of gravity of the aircraft) does not coincide with the moment centre of the balance, it is necessary to convert the moment measured by the balance relative to the centre of the balance into a moment relative to the moment reference point required for the test)
Correcting the lift effect: the method comprises the steps of airflow washing correction and streamline bending correction; compared with the wind tunnel test which flies in free atmosphere, the wind tunnel test has the advantages that the flowing state around the model is changed due to the existence of the tunnel wall, so that the model is subjected to different aerodynamic forces, as a result, under a given attack angle, the lift force is larger, the resistance is smaller, the longitudinal static stability is larger, and the correction of the aerodynamic force is the correction of the lift effect
Conversion of aerodynamic coefficients: converting the pneumatic load measured by the test into a dimensionless pneumatic coefficient, and then converting the data into a wind axis system;
shafting conversion: converting the data into different coordinate shafting according to different requirements for the use of the test data;
and (4) outputting a result: and outputting the obtained data and drawing a curve.
Preferably, the balance formula is corrected by air bridge influence: the air bridge pressure is changed by adjusting the high-pressure air supply flow, the scale reading is measured under each pressure and state, a relation curve of the scale reading change and the air bridge pressure is drawn, and an air bridge influence correction formula is fitted according to the curve.
Preferably, the conversion of the moment center: the first step is as follows: coordinate translation, which means translating the origin of a balance shaft system to the origin of the body axis coordinate of the model, and adopting the following formula:
YTm＝YT
XTm＝XT
MZTm＝MZT-YT·x0-XT·y0
ZTm＝ZT
MYTm＝MYT+ZT·x0+XT·z0
MXTm＝MXT+YT·z0-ZT·y0
in the formula, the parameter x0、y0、z0The coordinate value of the origin of the body axis coordinate of the model in the balance axis system, namely the positive and negative of the coordinate value are determined by the corresponding balance axis system;
the second step is that: coordinate rotation, namely rotating the translated balance shaft system by taking the origin of coordinates of the model body shaft as a center to form the model body shaft, and adopting the following formula:
Yt＝YTM·cosγancosαAn+XTM(cosβAn·sinαAn·cosγAn-sinγAn·sinβAn)+ZTM(cosγAnsinβAn·sinαAn+sinγAncosβAn)
Xt＝-YTM·sinαAn+XTM·cosβAn·cosαAn+ZTM·sinβAn·cosαAn
Mzt＝-MyTM sinγAncosαAn+MZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)+MXTM(cosγAnsinβAn+sinγAnsinαAncosβAn)
Zt＝ZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)-YTMsinγAncosαAn-XTM(sinβAncosγAn+sinγAnsinαAncosβAn)
Myt＝MyTM cosγAncosαAn+MxTM(sinγAnsinβAn-cosγAncosβAnsinαAn)+MZTM(cosγAnsinαAnsinβAn+sinγAncosβAn)
Mxt＝MxTM·cosαAn·cosβAn-MzTM·sinβAn·cosαAn+MyTM·sinαAn
In the formula, the parameter alphaAn、βAn、γAnThree initial mounting angles for each balance.
Preferably, the conversion of the aerodynamic coefficient: and (3) converting the aerodynamic load measured by the test into a dimensionless aerodynamic coefficient, and then converting the data into a wind axis system.
(1) Changing the coefficient by the following formula
Wherein s represents a reference area, bARepresents a longitudinal reference length, l represents a transverse reference length, and q represents a rapid compression;
(2) the method comprises the following steps of (1) converting data under a body axis system into data under a wind axis system by a body axis-to-wind axis conversion formula:
cyq＝cyt·cosα-cxt·sinα
cxq＝(cyt·sinα+cxt·cosα)·cosβ-czt·sinβ
mzq＝mzt·cosβ-l/bA·mxt·sinβ·cosα+l/bA·myt·sinα·sinβ
czq＝czt·cosβ+(cxt·cosα+cyt·sinα)·sinβ
myq＝myt·cosα+mxt·sinα
mxq＝(mxt·cosα-myt·sinα)·cosβ+bA/l·mzt·sinβ。
preferably, the main conversion relationship of the shafting conversion is as follows:
a. converting an airflow coordinate axis system into a machine body coordinate axis system:
b. converting a machine body coordinate axis system into an airflow coordinate axis system:
c. converting an airflow coordinate axis system into a half-body coordinate axis system:
the invention also comprises a semi-module blowing lift-increasing wind tunnel test device for the transporter, which comprises a test model, an electric push rod, a cross beam, a floor, a model supporting frame, a semi-module balance, a model connecting piece, a flow control unit, an air bridge, an air supply pipeline and a wind tunnel lower turntable;
the test model is arranged on a floor, the floor is arranged on a cross beam, and two ends of the electric push rod are respectively connected with the cross beam and the wind tunnel lower rotary disc;
the semi-module balance is positioned outside the test model, the fixed end of the semi-module balance is connected with the model supporting frame, and the floating end of the semi-module balance is connected with the test model through the model connecting piece; the model supporting frame is arranged on the wind tunnel lower turntable;
one end of the air bridge is communicated with the flow control unit, and the other end of the air bridge is communicated with an air supply system through an air supply pipeline;
and the flow control unit is communicated with a ventilation pipeline of the test model through a model connecting piece.
The test model is a half-mode test model with a ventilation pipeline and a blowing seam; the half-mold balance is a device for measuring model aerodynamic force, the flow control unit is used for accurately distributing and measuring air supply flow, the air bridge is used for reducing the influence of an air supply pipeline on balance load, the air supply system provides compressed air required by a test, and the air supply pipeline conveys the compressed air.
Preferably, the air bridge comprises two vertically arranged flexible joints and a transversely arranged flexible joint, and the middle part of the air bridge is fixed on the model supporting frame.
Preferably, a balance windshield is arranged outside the half-die balance, and a flow control unit windshield is arranged outside the flow control unit.
Preferably, the flow control unit is arranged on a flow control unit mounting frame, and the flow control unit mounting frame is connected with the model connecting piece.
According to the semi-module blowing lift-increasing wind tunnel test device for the conveyor, the test device can be more conveniently arranged in an open wind tunnel; the flow control unit can accurately measure and distribute flow, and the test is more precise; the air bridge can reduce the constraint influence problem of an air supply pipeline on the balance, the test result is more accurate, and the half-mode blowing lift-increasing verification and evaluation capability of the domestic open wind tunnel is improved
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that: based on the open wind tunnel and the flap blowing lift-increasing test device, the flap blowing parameter control and the half-mode model aerodynamic force measurement accuracy are improved, and reliable wind tunnel test data are provided for flap blowing lift-increasing aerodynamic performance evaluation of the transport aircraft.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic flow chart illustrating the steps of the present invention;
FIG. 2 is a data processing flow diagram of the present invention;
FIG. 3 is a side view of the test device;
fig. 4 is an axial view of the test apparatus.
The labels in the figure are: 1-test model, 2-electric push rod, 3-beam, 4-floor, 5-model support frame, 6-half-mold balance, 7-balance windshield, 8-model connecting piece, 9-flow control unit mounting rack, 10-flow control unit windshield, 11-flow control unit, 12-air bridge, 13-air supply pipeline and 14-wind tunnel lower rotary table.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
A half-module blowing lift-increasing wind tunnel test device for a conveyor comprises a half-module test model with a ventilation pipeline and a blowing seam, an electric push rod, a cross beam, a floor, a model supporting frame, a half-module balance, a model connecting piece, a flow control unit, an air bridge, an air supply pipeline and a wind tunnel lower turntable;
the test model is arranged on a floor, the floor is arranged on the beam, and the four electric push rods are respectively connected with the beam and the wind tunnel lower rotary disc through flange plates at two ends; the half-mode balance is positioned outside the test model, a balance wind shield is arranged outside the half-mode balance, the fixed end of the half-mode balance is connected with the model supporting frame, and the floating end of the half-mode balance is connected with the test model through a model connecting piece; the model supporting frame is arranged on the wind tunnel lower turntable; the air bridge comprises two vertically arranged flexible joints and a horizontally arranged flexible joint, one end of the air bridge is communicated with the flow control unit, the other end of the air bridge is communicated with the air supply system through an air supply pipeline, and the middle of the air bridge is fixed on the model support frame; the flow control unit is provided with a flow control unit wind cap outside, the flow control unit is arranged on the flow control unit mounting frame, the flow control unit mounting frame is connected with the model connecting piece, and the flow control unit is communicated with the ventilation pipeline of the test model through the model connecting piece.
In this embodiment, after the air supply system gives a total flow, compressed air enters the air bridge through the air supply pipeline, then enters the two-channel flow control unit, distributes the flow through the flow control unit, and then enters the ventilation pipeline of the model through the model connecting piece in two channels; after the flow is adjusted and the wind speed of the wind tunnel is stable, aerodynamic force is measured through a half-mode balance, the change of the attack angle of the model is realized by utilizing a lower rotating disc of the wind tunnel, and the change of the blowing momentum coefficient is realized by adjusting the total flow of a gas supply system and the distribution of a flow control unit.
A half-mode blowing lift-increasing wind tunnel test method for a conveyor comprises the following steps:
step a: carrying out calibration of the influence of high-pressure air on balance load after the high-pressure air passes through an air bridge, wherein the calibration comprises pressure influence calibration, temperature influence calibration and flow influence calibration; the pressure effect calibration is: sealing the air outlet, pressurizing the air bridge, and recording the relation between the pressure and the balance output; the temperature effect calibration is: using a standard spray pipe, ventilating and heating the air bridge, and recording the relationship between the temperature of the air bridge and the output of the balance in the natural cooling process of the air bridge; the flow effect calibration is: using a standard spray pipe to jet forward and backward;
step b: mounting a test device and a test model, and adjusting the attitude angle of the test model to a zero point;
step c: calibrating a momentum coefficient, and recording the flow and the position of a needle valve of each channel flow control unit;
step d: adjusting the attitude angle of the test model to zero, and collecting an initial reading;
step e: adjusting the wind speed to a test wind speed, and adjusting the blowing momentum coefficient to a test state; the flow is measured by a Venturi flow meter in the flow control unit; coefficient of momentum is represented by
Obtaining, wherein mjMeasuring mass flow, U, by a Venturi flowmeterjThe speed of an outlet of the blowing seam is shown, q is the test rapid pressure, and S' is the reference area of the blowing airfoil; the outlet velocity of the blowing gap is represented by the formula
Obtaining wherein p is0For the pressure in the pressure chamber, P, measured by the pressure sensoraIs atmospheric pressure, R is the gas constant, T0The total temperature of the gas is shown, and gamma is the specific heat capacity value of the air;
step f: adjusting the attitude angle of the test model, and recording balance signals, attitude angle signals, pressure sensor signals and temperature sensor signals after the rapid pressure is stable;
step g: processing balance data according to a flap blowing data processing method;
step h: and d, analyzing balance data, ending the test if the data are normal, and returning to the step c for testing again after the test device and the model are checked if the data are abnormal.
In the step h, the data processing sequentially comprises the following steps:
subtraction of readings: subtracting the windless original data from the windy original data corresponding to the attitude angle of the model;
balance formula calculation: calculating the pneumatic load of the test model according to a balance formula by subtracting the data of the initial reading; the balance formula is corrected by the air bridge influence: the method comprises the steps of changing the pressure of an air bridge by adjusting the flow of high-pressure air supply, measuring the reading of the balance under each pressure and state, drawing a relation curve between the change of the reading of the balance and the pressure of the air bridge, and fitting an air bridge influence correction formula according to the curve;
conversion of moment center: firstly, coordinate translation refers to translating the origin of a balance shaft system to the origin of a model body shaft coordinate, and the following formula is adopted:
YTm＝YT
XTm＝XT
MZTm＝MZT-YT·x0-XT·y0
ZTm＝ZT
MYTm＝MYT+ZT·x0+XT·z0
MXTm＝MXT+YT·z0-ZT·y0
in the formula, the parameter x0、y0、z0The coordinate value of the origin of the body axis coordinate of the model in the balance axis system, namely the positive and negative of the coordinate value are determined by the corresponding balance axis system;
and secondly, rotating coordinates, namely rotating the translated balance shaft system into a model body shaft by taking the origin of coordinates of the model body shaft as the center, wherein the following formula is adopted:
Yt＝YTM·cosγancosαAn+XTM(cosβAn·sinαAn·cosγAn-sinγAn·sinβAn)+ZTM(cosγAnsinβAn·sinαAn+sinγAncosβAn)
Xt＝-YTM·sinαAn+XTM·cosβAn·cosαAn+ZTM·sinβAn·cosαAn
Mzt＝-MyTMsinγAncosαAn+MZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)+MXTM(cosγAnsinβAn+sinγAnsinαAncosβAn)
Zt＝ZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)-YTM sinγAncosαAn-XTM(sinβAncosγAn+sinγAnsinαAncosβAn)
Myt＝MyTM cosγAncosαAn+MxTM(sinγAnsinβAn-cosγAncosβAnsinαAn)+MZTM(cosγAnsinαAnsinβAn+sinγAncosβAn)
Mxt＝MxTM·cosαAn·cosβAn-MzTM·sinβAn·cosαAn+MyTM·sinαAn
In the formula, the parameter alphaAn、βAn、γAnThree initial mounting angles for each balance.
Correcting the lift effect: the method comprises the steps of airflow washing correction and streamline bending correction;
conversion of aerodynamic coefficients:
(1) the pneumatic load measured by the test is converted into a dimensionless pneumatic coefficient, and the conversion coefficient adopts the following formula:
wherein s represents a reference area, bARepresents a longitudinal reference length, l represents a transverse reference length, and q represents a rapid compression;
(2) the method comprises the following steps of (1) converting data under a body axis system into data under a wind axis system by a body axis-to-wind axis conversion formula:
cyq＝cyt·cosα-cxt·sinα
cxq＝(cyt·sinα+cxt·cosα)·cosβ-czt·sinβ
mzq＝mzt·cosβ-l/bA·mxt·sinβ·cosα+l/bA·myt·sinα·sinβ
czq＝czt·cosβ+(cxt·cosα+cyt·sinα)·sinβ
myq＝myt·cosα+mxt·sinα
mxq＝(mxi·cosα-myt·sinα)·cosβ+bA/l·mzt·sinβ
shafting conversion: according to different requirements for the use of test data, converting the data into different coordinate shafting:
a. converting an airflow coordinate axis system into a machine body coordinate axis system:
b. converting a machine body coordinate axis system into an airflow coordinate axis system:
c. converting an airflow coordinate axis system into a half-body coordinate axis system:
and (4) outputting a result: and outputting the obtained data and drawing a curve.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (10)
1. A half-mode blowing lift-increasing wind tunnel test method for a conveyor is characterized by comprising the following steps: the method comprises the following steps:
step a: carrying out calibration of the influence of high-pressure air on balance load after the high-pressure air passes through an air bridge, wherein the calibration comprises pressure influence calibration, temperature influence calibration and flow influence calibration;
step b: mounting a test device and a test model, and adjusting the attitude angle of the test model to a zero point;
step c: calibrating a momentum coefficient, and recording the flow and the position of a needle valve of each channel flow control unit;
step d: adjusting the attitude angle of the test model to zero, and collecting an initial reading;
step e: adjusting the wind speed to a test wind speed, and adjusting the blowing momentum coefficient to a test state;
step f: adjusting the attitude angle of the test model, and recording balance signals, attitude angle signals, pressure sensor signals and temperature sensor signals after the rapid pressure is stable;
step g: processing balance data according to a flap blowing data processing method;
step h: and d, analyzing balance data, ending the test if the data are normal, and returning to the step c for testing again after the test device and the model are checked if the data are abnormal.
2. The transporter half-mold blowing high-lift wind tunnel test method according to claim 1, characterized in that: in step a, the pressure influence calibration is as follows: sealing the air outlet, pressurizing the air bridge, and recording the relation between the pressure and the balance output; the temperature effect calibration is: using a standard spray pipe, ventilating and heating the air bridge, and recording the relationship between the temperature of the air bridge and the output of the balance in the natural cooling process of the air bridge; the flow effect calibration is: obtained using a standard nozzle forward and reverse jet.
3. The transporter half-mold blowing high-lift wind tunnel test method according to claim 1, characterized in that: in step c, the momentum coefficient is represented by the formula
Obtaining, wherein mjMeasuring mass flow, U, by a Venturi flowmeterjFor blowing slot exit velocity, q for test velocity pressure, S' for blowing airfoilA reference area;
the outlet velocity of the blowing gap is represented by the formula
Obtaining wherein p is0For the pressure in the pressure chamber, P, measured by the pressure sensoraIs atmospheric pressure, R is the gas constant, T0Gamma is the specific heat capacity value of air for the total temperature of the gas.
4. The transporter half-mold blowing high-lift wind tunnel test method according to claim 1, characterized in that: in step h, the data processing comprises the following steps in sequence:
subtraction of readings: subtracting the windless original data from the windy original data corresponding to the attitude angle of the model;
balance formula calculation: calculating the pneumatic load of the test model according to a balance formula by subtracting the data of the initial reading;
conversion of moment center: the first step is as follows: coordinate translation, namely translating the origin of a balance shaft system to the origin of the body axis coordinate of the model; the second step is that: coordinate rotation, namely rotating the translated balance shaft system to form a model body shaft by taking the origin of coordinates of the model body shaft as a center;
correcting the lift effect: the method comprises the steps of airflow washing correction and streamline bending correction;
conversion of aerodynamic coefficients: converting the pneumatic load measured by the test into a dimensionless pneumatic coefficient, and then converting the data into a wind axis system;
shafting conversion: converting the data into different coordinate shafting according to different requirements for the use of the test data;
and (4) outputting a result: and outputting the obtained data and drawing a curve.
5. The transporter half-mold blowing high-lift wind tunnel test method according to claim 4, characterized in that: the balance formula is corrected by the air bridge influence: the air bridge pressure is changed by adjusting the air supply flow, the scale reading is measured under each pressure and state, the relation curve of the scale reading change and the air bridge pressure is drawn, and an air bridge influence correction formula is fitted according to the curve.
6. The transporter half-mold blowing high-lift wind tunnel test method according to claim 4, characterized in that: conversion of moment center: the first step is as follows: coordinate translation, which means translating the origin of a balance shaft system to the origin of the body axis coordinate of the model, and adopting the following formula:
YTm＝YT
XTm＝XT
MZTm＝MZT-YT～x0-XT·y0
ZTm＝ZT
MYTm＝MYT+ZT·x0+XT·z0
MXTm＝MXT+YT·z0-ZT·y0
in the formula, the parameter x0、y0、z0The coordinate value of the origin of the body axis coordinate of the model in the balance shaft system is shown;
the second step is that: coordinate rotation, namely rotating the translated balance shaft system by taking the origin of coordinates of the model body shaft as a center to form the model body shaft, and adopting the following formula:
Yt＝YTM·cosγancosαAn+XTM(cosβAn·sinαAn·cosγAn-sinγAn·sinβAn)+ZTM(cosγAnsinβAn·sinαAn+sinγAncosβAn)
Xt＝-YTM·sinαAn+XTM·cosβAn·cosαAn+ZTM·sinβAn·cosαAn
Mzt＝-MyTMsinγAncosαAn+MZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)+MXTM(cosγAnsinβAn+sinγAnsinαAncosβAn)
Zt＝ZTM(cosγAncosβAn-sinγAnsinαAnsinβAn)-YTMsinγAncosαAn-XTM(sinβAncosγAn+sinγAnsinαAncosβAn)
Myt＝MyTMcosγAncosαAn+MxTM(sinγAnsinβAn-cosγAncosβAnsinαAn)+MZTM(cosγAnsinαAnsinβAn+sinγAncosβAn)
Mxt＝MxTM·cosαAn·cosβAn-MzTM·sinβAn·cosαAn+MyTM·sinαAn
In the formula, the parameter alphaAn、βAn、γAnThree initial mounting angles for each balance.
7. The transporter half-mold blowing high-lift wind tunnel test method according to claim 4, characterized in that: conversion of aerodynamic coefficients: and (3) converting the aerodynamic load measured by the test into a dimensionless aerodynamic coefficient, and then converting the data into a wind axis system.
(1) Changing the coefficient by the following formula
Wherein s represents a reference area, bARepresents a longitudinal reference length, l represents a transverse reference length, and q represents a rapid compression;
(2) the method comprises the following steps of (1) converting data under a body axis system into data under a wind axis system by a body axis-to-wind axis conversion formula:
cyq＝cyt·cosα-cxt·sinα
cxq＝(cyt·sinα+cxt·cosα)·cosβ-czt·sinβ
mzq＝mzt·cosβ-l/bA·mxt·sinβ·cosα+l/bA·myt·sinα·sinβ
czq＝czt·cosβ+(cxt·cosα+cyt·sinα)·sinβ
myq＝myt·cosα+mxt·sinα
mxq＝(mxt·cosα-myt·sinα)·cosβ+bA/l·mst·sinβ。
8. the transporter half-mold blowing high-lift wind tunnel test method according to claim 4, characterized in that: the main conversion relationship of shafting conversion is as follows:
a. converting an airflow coordinate axis system into a machine body coordinate axis system:
b. converting a machine body coordinate axis system into an airflow coordinate axis system:
c. converting an airflow coordinate axis system into a half-body coordinate axis system:
9. the utility model provides a half mould blowing lift-increasing wind tunnel test device of conveyer which characterized in that: the device comprises a test model, an electric push rod, a cross beam, a floor, a model support frame, a half-mode balance, a model connecting piece, a flow control unit, an air bridge, an air supply pipeline and a wind tunnel lower turntable;
the test model is arranged on a floor, the floor is arranged on a cross beam, and two ends of the electric push rod are respectively connected with the cross beam and the wind tunnel lower rotary disc;
the semi-module balance is positioned outside the test model, the fixed end of the semi-module balance is connected with the model supporting frame, and the floating end of the semi-module balance is connected with the test model through the model connecting piece; the model supporting frame is arranged on the wind tunnel lower turntable;
one end of the air bridge is communicated with the flow control unit, and the other end of the air bridge is communicated with an air supply system through an air supply pipeline;
and the flow control unit is communicated with a ventilation pipeline of the test model through a model connecting piece.
10. The transporter half-mold blowing high-lift wind tunnel test device according to claim 9, characterized in that: and a balance windproof cover is arranged outside the half-mode balance, and a flow control unit windproof cover is arranged outside the flow control unit.
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