CN114112286B - Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method - Google Patents
Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method Download PDFInfo
- Publication number
- CN114112286B CN114112286B CN202111451269.8A CN202111451269A CN114112286B CN 114112286 B CN114112286 B CN 114112286B CN 202111451269 A CN202111451269 A CN 202111451269A CN 114112286 B CN114112286 B CN 114112286B
- Authority
- CN
- China
- Prior art keywords
- fitting
- throat section
- profile
- nozzle
- boundary layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
- G01M9/04—Details
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the technical field of wind tunnel nozzles, in particular to a hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method. The method comprises the steps of designing a fitting reference spray pipe according to a typical running state of a fitting throat section, enabling an inlet radius, a contracted section length, an expanded section length and an outlet radius of the fitting reference spray pipe to be the same as those of an original spray pipe through processing, obtaining a displacement thickness of a reference boundary layer through calculation processing, further obtaining a reverse derivation non-adhesive profile through reverse derivation, fitting on the reverse derivation non-adhesive profile to obtain a non-adhesive profile of the fitting throat section, adding the displacement thickness of the boundary layer at a corresponding position to obtain a physical profile of an expanded part of the fitting throat section, and combining the expanded part and the contracted part of the physical profile of the fitting throat section to obtain a complete physical profile of the fitting throat section. According to the method, the influence of boundary layer displacement thickness caused by operation Mach number, total temperature, total pressure and test medium change of the fitting throat section can be fully considered, the accuracy of the fitting throat is ensured, and throat section fitting with different requirements can be realized.
Description
Technical Field
The invention relates to the technical field of wind tunnel nozzles, in particular to a hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method.
Background
In order to change the Mach number of the spray pipe in the prior art, the throat section (comprising the contraction section of the spray pipe and the partial expansion section connected with the throat part) can be replaced on the basis of the axial symmetric profile spray pipe of the existing hypersonic wind tunnel, and the expansion section is shared, so that the engineering quantity can be greatly reduced, and the equipment construction cost is saved.
At present, the throat fitting design of the axisymmetric profile nozzle of the hypersonic wind tunnel is that the original nozzle (the nozzle of the throat section to be replaced) has no sticky profile L 2 Based on the design of the non-adhesive profile of the fitting section, and then the same seat of the original spray pipe is addedAnd forming a fitting section physical profile by the displacement thickness of the punctuations. The method has the disadvantages that only Mach number change of the fitting throat section and an original nozzle can be considered, and boundary layer thickness change caused by differences of total temperature, total pressure, test medium change, different running typical states and the like cannot be considered, so that the method is not beneficial to accurate fitting of the throat section and can cause larger deviation under certain conditions. Along with the development of aerodynamics, the requirements of throat section fitting with constant nozzle Mach number, total operating temperature, total pressure and gas medium change also appear, and the requirements cannot be met by adopting the original design method.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide a hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method, which can realize accurate fitting of a required throat section according to requirements and solve the problems in the prior art.
(II) technical scheme
In order to achieve the above object, in a first aspect, the present invention provides a method for designing a fitting throat section of a hypersonic wind tunnel axisymmetric profile nozzle, comprising the following steps:
(1) Designing to obtain a fitting reference spray pipe by adopting a design method which is the same as that of the original spray pipe and taking the operation Mach number, the total temperature, the total pressure, the gas medium, the inlet radius and the outlet radius of the fitting throat section as design input conditions;
(2) Processing the fitted reference nozzle using the following relationship:
x N =x N *x E /x NE
y N =y N *y E /y NE
keeping the inlet radius, the contraction section length and the outlet radius of the fitting reference nozzle consistent with the original nozzle;
calculating boundary layer displacement thickness delta of the fitting reference nozzle by adopting the following relational expression N And (3) processing:
δ=δ N *y E /y NE
obtaining the displacement thickness delta of the reference boundary layer;
wherein: x is the number of N To fit the X-coordinate, y, of the reference nozzle N To fit the Y coordinate, x, of the reference nozzle E Expanded length of primary nozzle, x NE To fit the expanded section length of the reference nozzle, y E Is the outlet radius of the original nozzle, y NE Fitting the outlet radius of the reference nozzle;
(3) In the physical profile L of the original spray pipe 1 The displacement thickness delta of the reference boundary layer is subtracted to form a backward derivation non-adhesive profile L 3 ;
(4) In said backward development of the inviscid profile L 3 Completing the design of the inviscid profile of the fitting throat section, and adding the displacement thickness delta of the reference boundary layer at the corresponding position on the inviscid profile of the expansion part of the fitting throat section to form a physical profile L of the fitting throat section 4 The expanding portion of (2);
(5) Designing and obtaining the physical profile L of the fitting throat section according to requirements 4 A constricted portion of (a);
(6) The fitted throat section physical profile L obtained in the steps (4) and (5) is subjected to 4 And the fitted throat section physical profile L 4 Are combined to obtain the physical profile L of the fitting throat section 4 。
Optionally, the fitting reference nozzle is designed by a characteristic line method.
Optionally, the boundary layer displacement thickness of the fitting reference nozzle is obtained by the following method:
and obtaining the value of the boundary layer shape factor H and the value of the momentum thickness theta by solving an axisymmetric Von-Karman momentum equation:
in the formula: x is the number of N To fit the X-coordinate, y, of a reference nozzle N To fit the Y coordinate of the reference nozzle, M e Mach number, C, design for fitting reference nozzle f Is coefficient of friction, θ f The gas flow deflection angle is shown, and gamma is the specific heat ratio of gas;
solving the boundary layer displacement thickness delta by adopting a momentum thickness weighting method N The weighting formula of the momentum thickness weighting method is as follows:
wherein H is the boundary layer shape factor, δ N And k is the boundary layer displacement thickness, k is a weighting coefficient, and theta is the momentum thickness obtained through prediction.
Optionally, the value range of the weighting coefficient k is between 0 and 1, verification is performed by using a numerical simulation method, and determination is performed by using an iteration method.
Optionally, the fitting of the inviscid profile design of the throat section in step (4) comprises the following steps:
(41) Deriving inviscid profile L in the reverse direction 3 The above assumes a fitting point;
(42) And (3) completing the design of the fitting throat inviscid profile by adopting a cubic curve equation:
y=a 0 +a 1 x+a 2 x 2 +a 3 x 3
in the formula a 0 ,a 1 ,a 2 ,a 3 Is the undetermined coefficient;
the boundary conditions of the above cubic curve equation are as follows:
x=0:y=y*;
x=x at :y=y at ;
substituting the boundary conditions into an equation to obtain undetermined coefficients, and substituting the undetermined coefficients into a formula to obtain the following fitting equation of the non-adhesive surface of the fitting throat section:
in the formula: y is the throat radius of the fitting throat section; y is at The fitted point radius of the non-adhesive surface is deduced reversely; x is the number of at Deriving axial coordinates of the fitting point of the unbonded surface in a reverse direction; theta at The dip angle of the fit point inviscid curve of the inviscid profile is reversely deduced, wherein X is the X coordinate of the fit throat section, and Y is the Y coordinate of the fit throat section;
(43) And (3) verifying the flow field quality of the non-adhesive line by adopting a characteristic line method without considering the viscosity influence, finishing the design if the flow field index meets the design requirement, and adjusting the position of a fitting point until the flow field index meets the requirement if the flow field index does not meet the requirement.
Optionally, the fitted throat section physical profile L in step (5) 4 The contraction part of (2) is obtained by calculation by adopting the following Witoszynski empirical formula of ideal incompressible axisymmetric flow:
wherein Y is the throat radius of the fitting throat section, Y L Is the inlet radius, X L For the length of the constriction, X L =2Y L X is the X coordinate of the fitting throat section and Y is the Y coordinate of the fitting throat section.
(III) advantageous effects
The technical scheme of the invention has the following advantages: the invention provides a hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method, which is characterized in that a fitting reference nozzle is designed according to a typical running state of the fitting throat section, the inlet radius, the contraction section length, the expansion section length and the outlet radius of the fitting reference nozzle are made to be the same as those of an original nozzle through processing, the displacement thickness of a reference boundary layer is obtained through calculation processing, then backward derivation non-adhesive profiles are obtained through backward derivation, non-adhesive profiles of the fitting throat section are obtained through fitting on the backward derivation non-adhesive profiles, the displacement thickness of the boundary layer is added at the corresponding position to obtain a physical profile of an expansion part of the fitting throat section, and the expansion part and the contraction part of the physical profile of the fitting throat section are combined to obtain a complete physical profile of the fitting throat section. The method can fully consider the influence of the operation Mach number, the total temperature, the total pressure and the displacement thickness of the boundary layer caused by the change of a test medium of the fitting throat section, ensure the accuracy of the fitting throat and realize the fitting of the throat sections with different requirements.
Drawings
The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the respective parts in the drawings do not necessarily correspond to those of an actual product.
FIG. 1 is a schematic representation of a fitted throat section profile according to an embodiment of the present invention;
fig. 2 is a partially enlarged schematic view of fig. 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The design method of the hypersonic wind tunnel axisymmetric profile nozzle fitting throat section provided by the embodiment of the invention comprises the following steps:
(1) And designing by adopting the same design method as the original spray pipe and taking the operation Mach number, the total temperature, the total pressure, the gas medium, the inlet radius and the outlet radius of the fitting throat section as design input conditions to obtain the fitting reference spray pipe. It should be noted that the original nozzle is a hypersonic wind tunnel axisymmetric profile nozzle of the throat section to be replaced, and the design thereof generally adopts MOC/BL method calculation, i.e. characteristic line method/boundary layer correction, which are mature prior art, and are not described in detail in the present application.
(2) Processing the fitted reference nozzle using the following relationship:
x N =x N *x E /x NE
y N =y N *y E /y NE
and keeping the inlet radius, the contraction section length and the outlet radius of the fitting reference nozzle consistent with the original nozzle.
Calculating boundary layer displacement thickness delta of the fitting reference nozzle by adopting the following relational expression N And (3) processing:
δ=δ N *y E /y NE
obtaining the displacement thickness delta of the reference boundary layer;
wherein: x is the number of N To fit the X-coordinate, y, of a reference nozzle N To fit the Y coordinate, x, of the reference nozzle E Expanded length of primary nozzle, x NE To fit the length of the expanded section of the reference nozzle, y E Is the outlet radius of the original nozzle, y NE To fit the exit radius of the reference nozzle.
In one embodiment, the boundary layer displacement thickness δ of the fitted reference nozzle N The method comprises the following steps:
and obtaining the value of the boundary layer shape factor H and the value of the momentum thickness theta by solving an axisymmetric Von-Karman momentum equation:
in the formula: x is the number of N To fit the X-coordinate, y, of a reference nozzle N To fit the Y coordinate of the reference nozzle, M e Design Mach number, C for fitting reference nozzle f Is coefficient of friction, θ f The gas flow deflection angle is shown, and gamma is the specific heat ratio of gas;
solving the boundary layer displacement thickness delta by adopting a momentum thickness weighting method N The weighting formula of the momentum thickness weighting method is as follows:
wherein H is the boundary layer shape factor, δ N And k is the boundary layer displacement thickness, k is a weighting coefficient, and theta is the momentum thickness obtained through prediction.
Optionally, the value range of the weighting coefficient k is between 0 and 1, verification is performed by using a numerical simulation method, and determination is performed by using an iteration method. It should be noted that, the verification is performed by using a numerical simulation method, and the determination by using an iterative method may all be performed by using the prior art, which is not described herein again.
(3) In the physical profile L of the primary spray pipe 1 The displacement thickness delta of the reference boundary layer is subtracted to form a reversely derived non-adhesive profile L 3 。
(4) In said backward development of the inviscid profile L 3 Completing the design of the inviscid profile of the fitting throat section, and adding the displacement thickness delta of the reference boundary layer at the corresponding position on the inviscid profile of the expansion part of the fitting throat section to form a physical profile L of the fitting throat section 4 The expansion part of (2).
The non-stick profile design of the fitting throat section in step (4) can be performed by the following method, comprising the following steps:
(41) Deriving inviscid profile L in the reverse direction 3 The above assumes a fitting point;
(42) And (3) adopting a cubic curve equation to complete the design of the fitting throat inviscid profile:
y=a 0 +a 1 x+a 2 x 2 +a 3 x 3
in the formula a 0 ,a 1 ,a 2 ,a 3 Is the undetermined coefficient;
the boundary conditions of the cubic curve equation are as follows:
x=0:y=y*;
x=x at :y=y at ;
substituting the boundary conditions into an equation to obtain undetermined coefficients, and substituting the undetermined coefficients into a formula to obtain the following fitting equation of the non-adhesive surface of the fitting throat section:
in the formula: y is the throat radius of the fitting throat section; y is at The fitted point radius of the non-adhesive surface is deduced reversely; x is the number of at Deriving axial coordinates of the fitting point of the non-adhesive surface in a reverse direction; theta at In order to reversely deduce the inclination angle of the fitting point inviscid curve of the inviscid surface, X is the X coordinate of the fitting throat section, and Y is the Y coordinate of the fitting throat section.
On the basis, the displacement thickness delta of the reference boundary layer at the corresponding position is added to the non-adhesive surface of the expansion part of the fitting throat section, namely the fitting formula of the expansion part of the physical surface L4 of the fitting throat section is as follows:
(43) And (3) verifying the flow field quality of the unbonded molded line by adopting a characteristic line method without considering the viscosity influence, finishing the design if the flow field index meets the design requirement, and adjusting the position of a fitting point until the flow field index meets the requirement if the flow field index does not meet the requirement. It should be noted that, the flow field quality of the unbonded line is verified by using the characteristic line method and the fitting point position is adjusted according to the verification result, which is not described herein again.
(5) Designing to obtain a physical profile L of a fitting throat section according to requirements 4 The constriction of (a). It should be noted that the physical profile required can be designed using existing design methods, for example, using the following ideal incompressible axisymmetric flowWitoszynski (Witoscinki) empirical formula is calculated to obtain:
wherein Y is the throat radius of the fitting throat section, Y L Is the entry radius, X L For the length of the constriction, X L =2Y L X is the X coordinate of the fitting throat section and Y is the Y coordinate of the fitting throat section.
In addition, it should be noted that, although the inlet size of the constricted portion of the fitting throat section is generally the same as the inlet size of the constricted portion of the original nozzle, the problem of profile butt joint is not involved in the replacement, and therefore, if there is a special need, the inlet size of the constricted portion of the fitting throat section may not be the same as the inlet size of the constricted portion of the original nozzle, and the implementation method can be implemented by using the prior art, and is not described herein again.
(6) Fitting the physical profile L of the throat section obtained in the steps (4) and (5) 4 And fitting throat section physical profile L 4 The contraction parts are combined together to obtain a fitted throat section physical profile L 4 . Referring to FIGS. 1 and 2, a fitting throat section physical profile obtained by the design method of the present application is schematically shown, L in the figure 1 Is the physical profile of the original nozzle, L 2 Is a non-adhesive molded surface of the original spray pipe, L 3 For deriving the non-adhesive profile in the reverse direction, L 4 And fitting a throat section physical profile.
The method comprises the steps of designing a fitting reference spray pipe according to a typical running state of a fitting throat section, enabling an inlet radius, a contracted section length, an expanded section length and an outlet radius of the fitting reference spray pipe to be the same as those of an original spray pipe through processing, obtaining a displacement thickness of a reference boundary layer through calculation processing, further obtaining a reverse derivation non-adhesive profile through reverse derivation, fitting on the reverse derivation non-adhesive profile to obtain a non-adhesive profile of the fitting throat section, adding the displacement thickness of the boundary layer at a corresponding position to obtain a physical profile of an expanded part of the fitting throat section, and combining the expanded part and the contracted part of the physical profile of the fitting throat section to obtain a complete physical profile of the fitting throat section. The method can fully consider the influence of the operation Mach number, the total temperature, the total pressure and the displacement thickness of the boundary layer caused by the change of a test medium of the fitting throat section, ensure the accuracy of the fitting throat and realize the fitting of the throat sections with different requirements.
It is worth to be noted that the X coordinate and the Y coordinate of the original nozzle, the fitting reference nozzle and the fitting throat section in the present application all adopt the coordinate system commonly adopted in the field of nozzle design, that is, the axial direction of the nozzle is the X axis, the direction perpendicular to the X axis at the throat is the Y axis, and the intersection point of the X axis and the Y axis is the origin of coordinates.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments can be combined in any way to form other embodiments which can be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. A hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method is characterized by comprising the following steps:
(1) Designing to obtain a fitting reference spray pipe by adopting a design method which is the same as that of the original spray pipe and taking the operation Mach number, the total temperature, the total pressure, the gas medium, the inlet radius and the outlet radius of the fitting throat section as design input conditions;
(2) Processing the fitted reference nozzle using the following relationship:
x N =x N *x E /x NE
y N =y N *y E /y NE
keeping the inlet radius, the contracted section length and the outlet radius of the fitting reference spray pipe consistent with the original spray pipe;
the boundary layer displacement thickness delta of the fitting reference nozzle obtained by calculation is subjected to the following relational expression N And (3) processing:
δ=δ N *y E /y NE
obtaining the displacement thickness delta of the reference boundary layer;
wherein: x is the number of N To fit the X-coordinate, y, of a reference nozzle N To fit the Y coordinate, x, of the reference nozzle E Expanded length of primary nozzle, x NE To fit the length of the expanded section of the reference nozzle, y E Is the outlet radius of the original nozzle, y NE Fitting the outlet radius of the reference nozzle;
(3) In the physical profile L of the original spray pipe 1 The displacement thickness delta of the reference boundary layer is subtracted to form a reversely derived non-adhesive profile L 3 ;
(4) In said backward development of the inviscid profile L 3 The design of the non-adhesive profile of the fitting throat section is completed, the displacement thickness delta of the reference boundary layer at the corresponding position is added on the non-adhesive profile of the expansion part of the fitting throat section to form the physical profile L of the fitting throat section 4 The expansion part of (1);
(5) Designing and obtaining the physical profile L of the fitting throat section according to requirements 4 A constricted portion of (a);
(6) The fitted throat section physical profile L obtained in the steps (4) and (5) is subjected to 4 And said fitted throat section physical profile L 4 Are combined to obtain the physical profile L of the fitting throat section 4 。
2. The design method of the hypersonic wind tunnel axisymmetric profile nozzle fitting throat section according to claim 1, characterized in that: and designing by adopting a characteristic line method to obtain the fitting reference spray pipe.
3. The hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method according to claim 2, characterized in that: the boundary layer displacement thickness of the fitting reference nozzle is obtained by the following method:
and obtaining the value of the boundary layer shape factor H and the value of the momentum thickness theta by solving an axisymmetric Von-Karman momentum equation:
in the formula: x is the number of N To fit the X-coordinate, y, of the reference nozzle N To fit the Y coordinate of the reference nozzle, M e Design Mach number, C for fitting reference nozzle f Is coefficient of friction, θ f The gas flow deflection angle is shown, and gamma is the specific heat ratio of gas;
solving the boundary layer displacement thickness delta by adopting a momentum thickness weighting method N The weighting formula of the momentum thickness weighting method is as follows:
wherein H is the boundary layer shape factor, δ N And k is the boundary layer displacement thickness, k is a weighting coefficient, and theta is the momentum thickness obtained through prediction.
4. The hypersonic wind tunnel axisymmetric profile nozzle fitting throat section design method according to claim 3, characterized in that: the value range of the weighting coefficient k is between 0 and 1, the verification is carried out by adopting a numerical simulation method, and the determination is carried out by an iteration method.
5. The design method of the hypersonic wind tunnel axisymmetric profile nozzle fitting throat section according to claim 1, characterized in that: the design of the non-adhesive profile of the fitting throat section in the step (4) comprises the following steps:
(41) Deriving inviscid profile L in the reverse direction 3 The above assumes a fitting point;
(42) And (3) adopting a cubic curve equation to complete the design of the fitting throat inviscid profile:
y=a 0 +a 1 x+a 2 x 2 +a 3 x 3
in the formula a 0 ,a 1 ,a 2 ,a 3 Is the undetermined coefficient;
the boundary conditions of the above cubic curve equation are as follows:
x=0:y=y * ;
x=x at :y=y at ;
substituting the boundary conditions into an equation to obtain undetermined coefficients, and substituting the undetermined coefficients into a formula to obtain the following fitting equation of the non-adhesive surface of the fitting throat section:
in the formula: y is the throat radius of the fitting throat section; y is at Deriving a fitted point radius of the unbonded surface in a reverse direction; x is the number of at Deriving axial coordinates of the fitting point of the non-adhesive surface in a reverse direction; theta at The dip angle of the fit point inviscid curve of the inviscid profile is reversely deduced, wherein X is the X coordinate of the fit throat section, and Y is the Y coordinate of the fit throat section;
(43) And (3) verifying the flow field quality of the non-adhesive line by adopting a characteristic line method without considering the viscosity influence, finishing the design if the flow field index meets the design requirement, and adjusting the position of a fitting point until the flow field index meets the requirement if the flow field index does not meet the requirement.
6. According to the rightThe design method for the fitting throat section of the axially symmetric profile nozzle of the hypersonic wind tunnel according to claim 1, is characterized by comprising the following steps: in the step (5), fitting the throat section physical profile L 4 The contraction part of the flow is obtained by the following Witoszynski empirical formula of ideal incompressible axial symmetric flow:
wherein, y * To fit the throat radius, Y, of the throat section L Is the inlet radius, X L For the length of the constriction, X L =2Y L X is the X coordinate of the fitting throat section and Y is the Y coordinate of the fitting throat section.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202111451269.8A CN114112286B (en) | 2021-12-01 | 2021-12-01 | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202111451269.8A CN114112286B (en) | 2021-12-01 | 2021-12-01 | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method |
Publications (2)
Publication Number | Publication Date |
---|---|
CN114112286A CN114112286A (en) | 2022-03-01 |
CN114112286B true CN114112286B (en) | 2023-02-28 |
Family
ID=80369143
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202111451269.8A Active CN114112286B (en) | 2021-12-01 | 2021-12-01 | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN114112286B (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN115046722B (en) * | 2022-08-16 | 2022-10-25 | 中国航空工业集团公司沈阳空气动力研究所 | Method for calibrating mach number of cross-supersonic-velocity wind tunnel nozzle |
CN115048753B (en) * | 2022-08-16 | 2023-03-28 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel aerodynamic shape design method |
CN115048752B (en) * | 2022-08-16 | 2022-11-01 | 中国航空工业集团公司沈阳空气动力研究所 | Design method of semi-flexible wall spray pipe of cross-supersonic wind tunnel |
CN117007274B (en) * | 2023-10-07 | 2023-12-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Subsonic wind tunnel loop mass flow measurement method |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH08166317A (en) * | 1994-12-14 | 1996-06-25 | Hitachi Ltd | Nozzle for high-temperature wind tunnel |
CN104359647A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Method for determining profile of conical nozzle of hypersonic-velocity low-density wind tunnel |
CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
CN108195544A (en) * | 2016-12-08 | 2018-06-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
CN108240898A (en) * | 2016-12-23 | 2018-07-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
CN112727860A (en) * | 2020-12-22 | 2021-04-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Structure for high-Mach-number molded surface spray pipe water-cooling throat of hypersonic wind tunnel |
CN112809323A (en) * | 2021-01-26 | 2021-05-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Manufacturing process of axisymmetric nozzle of conventional hypersonic wind tunnel |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20020050719A1 (en) * | 2000-06-12 | 2002-05-02 | Caddell Robert I. | Co-probe power generation system |
US20110285139A1 (en) * | 2010-05-24 | 2011-11-24 | Pasquale Gregory Falbo | Windflow modification into electricity-generating wind turbines |
-
2021
- 2021-12-01 CN CN202111451269.8A patent/CN114112286B/en active Active
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH08166317A (en) * | 1994-12-14 | 1996-06-25 | Hitachi Ltd | Nozzle for high-temperature wind tunnel |
CN104359647A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Method for determining profile of conical nozzle of hypersonic-velocity low-density wind tunnel |
CN108195544A (en) * | 2016-12-08 | 2018-06-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
CN108240898A (en) * | 2016-12-23 | 2018-07-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
CN112727860A (en) * | 2020-12-22 | 2021-04-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Structure for high-Mach-number molded surface spray pipe water-cooling throat of hypersonic wind tunnel |
CN112809323A (en) * | 2021-01-26 | 2021-05-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Manufacturing process of axisymmetric nozzle of conventional hypersonic wind tunnel |
Also Published As
Publication number | Publication date |
---|---|
CN114112286A (en) | 2022-03-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN114112286B (en) | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method | |
CN104359647B (en) | The method determining the conical nozzle molded line of hypersonic low density wind tunnel | |
CN103150423B (en) | Rotational symmetry becomes Mach number nozzle and wall defining method thereof continuously | |
CN102302989B (en) | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe | |
CN110555214A (en) | compressor blade profile construction method and compressor blade | |
CN108415367B (en) | Automatic wire laying track global curvature fairing algorithm | |
CN108182319B (en) | Supersonic velocity integrated spray pipe design method | |
CN108038295B (en) | Hypersonic inlet channel and isolation section integrated design method | |
Ahmadabadi et al. | Subsonic and transonic airfoil inverse design via ball-spine algorithm | |
WO2017218841A1 (en) | Two-dimensional supersonic nozzle thrust vectoring using staggered ramps | |
CN105138787A (en) | Supersonic flow field design method based on characteristic line tracing | |
CN115046722B (en) | Method for calibrating mach number of cross-supersonic-velocity wind tunnel nozzle | |
WO2014043847A1 (en) | Numerical method for solving inverse problem of subsonic flow | |
CN110633522A (en) | Supersonic thrust nozzle reverse design method based on maximum thrust theory | |
Korte | Aerodynamic design of axisymmetric hypersonic wind-tunnel nozzles using a least-squares/parabolized Navier-Stokes procedure | |
CN111220341A (en) | Design method of wind tunnel high-Mach-number low-Reynolds-number axisymmetric profile spray pipe | |
CN114781078A (en) | Stealth snakelike air inlet channel design method based on matrix transformation | |
Vallabh et al. | Investigation of nozzle contours in the CSIR supersonic wind tunnel | |
CN115659705B (en) | Fully-parameterized high-stealth air inlet channel design method and high-stealth air inlet channel | |
CN115358101B (en) | Jet pipe design method based on sound velocity solution and characteristic line reverse thrust | |
CN115879216A (en) | Flow field reconstruction design method under internal flow channel strong wave system interference control | |
Guo et al. | Aerodynamic performance-preserving construction method for a near-net-shape blade cross section | |
CN111062097B (en) | Design method of self-adaptive high-enthalpy molded surface spray pipe | |
CN103321779B (en) | Supersonic Nonuniform incoming flow Maximum Thrust Nozzle and wall defining method thereof | |
Tormalm | Design and analysis of compact UAV ducts |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |