CN117969014A - Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body - Google Patents
Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body Download PDFInfo
- Publication number
- CN117969014A CN117969014A CN202410149533.XA CN202410149533A CN117969014A CN 117969014 A CN117969014 A CN 117969014A CN 202410149533 A CN202410149533 A CN 202410149533A CN 117969014 A CN117969014 A CN 117969014A
- Authority
- CN
- China
- Prior art keywords
- trapezoid
- top surface
- boundary layer
- slope
- length
- 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.)
- Pending
Links
- 230000008719 thickening Effects 0.000 title claims abstract description 37
- 238000013461 design Methods 0.000 title claims abstract description 11
- 238000000034 method Methods 0.000 title claims abstract description 10
- 238000011161 development Methods 0.000 claims abstract description 3
- 230000004323 axial length Effects 0.000 claims description 9
- 238000004088 simulation Methods 0.000 claims description 6
- 230000018109 developmental process Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Landscapes
- Earth Drilling (AREA)
Abstract
The invention discloses an artificial thickening structure of a boundary layer on the surface of a subsonic cylindrical engine body and a design method, wherein the artificial thickening structure comprises a cylindrical engine body and a trapezoid slope array arranged on the surface of the engine body, and the trapezoid slope array comprises a plurality of trapezoid slopes which are uniformly arranged along the circumferential direction of the surface of the engine body; the trapezoid slope comprises a trapezoid bottom surface, a trapezoid top surface and a connecting surface for connecting the trapezoid bottom surface and the trapezoid top surface, the trapezoid bottom surface is positioned on the machine body surface, the trapezoid bottom surface is overlapped with the lower bottom of the trapezoid top surface, the trapezoid top surface and the machine body surface form a certain inclined angle to generate flow direction vortex on the machine body surface, and the vertical distance between the highest point of the trapezoid slope and the machine body surface is not higher than the thickness of a local free development boundary layer of the machine body surface. According to the invention, the flow direction vortex structure is generated through the trapezoid slope structure array, so that the mixing between the main flow and the boundary layer airflow is promoted, the thickness of the boundary layer at the downstream of the cylindrical engine body is effectively increased, and the thickness of the boundary layer is more similar to the actual flight condition of the engine body.
Description
Technical Field
The invention relates to the technical field of aerodynamics, in particular to an artificial thickening structure of a boundary layer on the surface of a subsonic cylindrical engine body and a design method.
Background
The problem of blockage is often encountered in the subsonic wind tunnel test of the slender cylindrical body scaled air inlet channel, and the model dimensions such as the length, the diameter and the like of the body are required to be modified. In order to simulate the thick boundary layer of the body, the thickness of the modified model boundary layer needs to be controlled to be matched with that of the original scaling model boundary layer. At present, for thickening of the boundary layer on the surface of the subsonic cylindrical body, active control and passive control can be mainly classified according to whether external energy is injected. The array of the backward slope structure and the cylindrical detour structure is a currently common passive control thickening structure. The thickening principle of the backward slope structure is that a flow separation lifting streamline is generated after the slope, so that the thickness of a downstream boundary layer is increased, and the backward slope structure has the advantages of obvious thickening, simple structure and the like, but the separation scale is difficult to control, so that the thickness of the boundary layer is difficult to control accurately. The thickening principle of the cylindrical bypass structure array is that a backflow vortex lifting streamline is generated after the cylindrical structure, so that the thickness of a downstream boundary layer is increased, and the thickening principle has the advantages of strong operability, small flow loss and the like, but the thickening effect still cannot completely simulate a thick boundary layer of a machine body.
Disclosure of Invention
The invention aims to: aiming at the defects, the invention provides an artificial thickening structure and a design method for a boundary layer on the surface of a subsonic cylindrical engine body, wherein the artificial thickening structure has a good boundary layer thickening effect.
The technical scheme is as follows: in order to solve the problems, the invention adopts an artificial thickening structure of a boundary layer on the surface of a subsonic cylindrical engine body, which comprises an engine body and a trapezoid slope array arranged on the surface of the engine body, wherein the trapezoid slope array comprises a plurality of trapezoid slopes which are uniformly arranged along the circumferential direction of the surface of the engine body; the trapezoid slope comprises a trapezoid bottom surface, a trapezoid top surface and a connecting surface for connecting the trapezoid bottom surface and the trapezoid top surface, the trapezoid bottom surface is located on the machine body surface, the trapezoid bottom surface is overlapped with the lower bottom of the trapezoid top surface, the trapezoid top surface and the machine body surface form a certain inclination angle to generate flow direction vortex on the machine body surface, and the vertical distance between the highest point of the trapezoid slope and the machine body surface is not higher than the thickness of a local free development boundary layer of the machine body surface.
Further, the connecting surface comprises a first side surface and a second side surface which are connected with the side edge of the trapezoid bottom surface and the side edge of the trapezoid top surface, and a top surface which is connected with the upper bottom of the trapezoid bottom surface and the upper bottom of the trapezoid top surface, one side of the top surface is overlapped with one side of the first side surface, and the other side of the top surface is overlapped with one side of the second side surface.
Furthermore, the bottom surface, the top surface and the top surface of the trapezoid are isosceles trapezoids, and the upper bottom length of the bottom surface of the trapezoid is smaller than the upper bottom length of the top surface of the trapezoid; the plane of the top surface is perpendicular to the axis of the machine body.
Further, the first side surface and the second side surface are triangular, and the plane where the first side surface is located and the plane where the second side surface is located intersect with the axis of the machine body at the same point.
Further, the upper bottom length of the trapezoid top surface is 1/3 of the lower bottom length of the trapezoid top surface.
Further, the included angle between the trapezoid top surface and the machine body surface is 20 degrees.
Further, the plurality of trapezoid slopes comprise a plurality of trapezoid top surfaces, bottoms of the trapezoid top surfaces are arranged on the same circumference, and the distance between the bottoms of the adjacent trapezoid top surfaces is 60% of the length of the bottoms of the trapezoid top surfaces.
Furthermore, the machine body is provided with a downstream air inlet channel inlet, the flow direction distance between the trapezoid slope array and the downstream air inlet channel inlet is a, the axial length of the machine body is b, and a/b is more than or equal to 0.125.
The invention also provides a design method of the artificial thickening structure of the boundary layer on the surface of the subsonic cylindrical engine body, which comprises the following steps:
Step 1, preliminarily determining the height h of the trapezoid slope according to the difference epsilon between the thickness of the boundary layer required by the inlet of the downstream air inlet channel and the thickness of the freely developed boundary layer on the surface of the machine body without the trapezoid slope array, wherein h=fepsilon, and f is smaller than 1;
Step 2, obtaining the axial length l=h/tan alpha of the trapezoid slope according to the height h of the trapezoid slope, wherein alpha is the included angle between the top surface of the trapezoid and the surface of the machine body;
step 3, determining the lower bottom length a=l/sin 60 degrees of the top surface of the trapezoid according to the axial length l of the trapezoid slope;
Step 4, determining that the upper bottom length b of the trapezoid top surface is 1/3 of the lower bottom length a according to the lower bottom length of the trapezoid top surface;
Step 5, determining that the distance between two adjacent trapezoid slopes is 60% of the length a of the bottom of the trapezoid top surface according to the length of the bottom of the trapezoid top surface;
step 6, determining the shape of the connecting surface to enable the trapezoid top surface to be connected with the trapezoid bottom surface;
step 7, determining the number of trapezoid slopes in the trapezoid slope array;
step 8, performing CFD simulation check according to the design Mach number and attack angle;
and 9, adjusting the coefficient f according to the CFD simulation result, and repeating the steps 2-8 until the error between the thickness of the boundary layer at the inlet of the downstream air inlet and the thickness of the boundary layer actually required is smaller than a preset value.
Further, the step 7 specifically includes: and determining the circumferential total length of the trapezoid slope array according to the range of the boundary layer which is required to be thickened by the machine body, wherein the quotient of the circumferential total length of the trapezoid slope array, the bottom length of the trapezoid top surface of the trapezoid slope and the sum of the distances between two adjacent trapezoid slopes is an integer to be used as the number of trapezoid slopes in the trapezoid slope array.
The beneficial effects are that: compared with the prior art, the invention has the remarkable advantages that (1) the flow direction vortex structure is generated through the trapezoid slope array, the mixing between the main flow and the boundary layer airflow is promoted, the thickness of the boundary layer at the downstream of the cylindrical machine body is effectively increased, and the thickness of the boundary layer is more similar to the actual flight condition of the machine body; (2) The trapezoid slope is designed to fit the airflow movement, and is well fitted with the freely developed boundary layer along-path pressure distribution curve with the same thickness, so that the influence on the resistance characteristic of the aircraft is small.
Drawings
FIG. 1 is a schematic view of the overall structure of the artificial thickening structure of the boundary layer of the present invention;
FIG. 2 is a schematic diagram of the overall structure of a trapezoidal ramp array according to the present invention;
FIG. 3 is an enlarged schematic view of a portion of a trapezoidal ramp array according to the present invention;
fig. 4 is a schematic diagram of streamline distribution of a circumferential cross section of a CFD simulation trapezoidal slope array of a two-body embodiment.
Detailed Description
Example 1
As shown in fig. 1, an artificial thickening structure for a boundary layer of a subsonic cylindrical body surface in this embodiment includes a body 1 and a trapezoidal slope array disposed on the body 1 surface, where the trapezoidal slope array includes a plurality of trapezoidal slopes 101 uniformly arranged along the circumferential direction of the body 1 surface. As shown in fig. 2 and 3, the trapezoid slope 101 includes a trapezoid bottom surface 107, a trapezoid top surface 102, and a connecting surface connecting the trapezoid bottom surface 107 and the trapezoid top surface, wherein the trapezoid bottom surface 107 and the trapezoid top surface 102 are isosceles trapezoids, and the upper bottom length of the trapezoid bottom surface 107 is smaller than the upper bottom length of the trapezoid top surface 102. The trapezoidal bottom surface 107 is located on the surface of the machine body 1, the trapezoidal bottom surface 107 coincides with the lower bottom of the trapezoidal top surface 102, and the trapezoidal top surface 102 forms a certain inclination angle with the surface of the machine body 1, so that airflow generates a flow vortex 106 on the surface of the machine body 1. In order to ensure that the downstream boundary layer is sufficiently restored to a state of sufficiently developed turbulence, the ratio of the flow direction distance of the downstream inlet 108 to the trapezoidal slope array to the axial length of the cylindrical body 1 should be not less than 0.125.
The design method of the boundary layer artificial thickening structure in the embodiment specifically comprises the following steps:
Step 1, the height h of the trapezoid slope 101 is primarily determined according to the difference epsilon between the thickness of the boundary layer required by the downstream air inlet 108 and the thickness of the freely developed boundary layer on the surface of the machine body 1 without the trapezoid slope array, wherein h=fepsilon, and f is smaller than 1. In the embodiment, the machine body 1 is cylindrical, the radius of the machine body is 51.11mm, and the length of the machine body is 1200mm. The required thickness of the boundary layer of the downstream inlet 108 at Ma0.5 and 3 DEG attack angle is 20.428mm, the thickness of the freely developed boundary layer on the surface of the cylindrical body 107 without the trapezoid ramp array is 16.510mm, and the difference epsilon between the two is 3.918mm. According to the prior literature and experimental requirements, the coefficient f=0.854 is preliminarily determined, so that the height of the trapezoid slope 101 is h=0.854 epsilon=3.35 mm, which is smaller than the thickness 8.277mm of the local freely developed boundary layer of the trapezoid slope array, and the requirements are met.
Step 2, the axial length l=h++tan α of the trapezoid slope 101 is obtained according to the height h of the trapezoid slope 101, and α is the angle between the trapezoid top surface 102 and the surface of the machine body 1.α=20° in this example, from which l=9.20 mm is calculated.
Step 3, determining the lower bottom length a=l/sin 60°=10.62 mm of the trapezoidal top surface 102 according to the axial length l of the trapezoidal slope 101.
Step 4, according to the lower bottom length of the trapezoid top surface 102, determining that the upper bottom length b of the trapezoid top surface 102 is 1/3 of the lower bottom length a, and b=3.54 mm.
And 5, determining that the distance between two adjacent trapezoid slopes 101 is 60% of the lower bottom length a of the trapezoid top surface 102 according to the lower bottom length of the trapezoid top surface 102, and the distance is 6.37mm.
Step 6, determining the shape of the connecting surface to connect the trapezoid top surface 102 with the trapezoid bottom surface 107. The connecting surface comprises a first side surface 103 and a second side surface 104 which are used for connecting the side edge of the trapezoid bottom surface 107 and the side edge of the trapezoid top surface 102, the first side surface 103 and the second side surface 104 are triangular, and the plane of the first side surface 103 and the plane of the second side surface 104 intersect with the axis of the machine body 1at the same point C (x c,yc). The top surface 105 is connected with the upper bottom of the trapezoid bottom surface 107 and the upper bottom of the trapezoid top surface 102, one side of the top surface 105 is overlapped with one side of the first side surface 103, the other side of the top surface 105 is overlapped with one side of the second side surface 104, the top surface 105 is an isosceles trapezoid, and the plane of the top surface 105 is perpendicular to the axis of the machine body 1.
Step 7, determining the number of the trapezoid slopes 101 in the trapezoid slope array. The total circumferential length of the trapezoidal ramp array is determined according to the geometry of the cylindrical body 1 and the extent to which the boundary layer needs to be thickened. In this embodiment, only the boundary layer within the range of the downstream inlet 108 needs to be thickened, so the circumferential total length of the trapezoidal slope array does not exceed 120mm, the lower bottom length of the trapezoidal top surface 102 of the trapezoidal slope 101 and the distance between two adjacent trapezoidal slopes 101 are 16.99mm, and the two are rounded to obtain 7 trapezoidal slopes 101 in the trapezoidal slope array.
And 8, performing CFD simulation check according to the design Mach number and the attack angle. Under the working conditions of Ma0.5 and 3 degrees of attack, the thickening effect can be seen in Table 1, the thickness of the boundary layer before the inlet 108 of the downstream air inlet after thickening is 19.985mm, and the error is 2.17 percent compared with the thickness of the expected boundary layer 20.428mm, so that the requirements are met.
And 9, if the thickening structure designed according to the initial coefficient f does not meet the requirement of the experiment, resetting the coefficient f, and repeating the steps 2-8 until the thickness of the boundary layer at the inlet of the downstream air inlet channel meets the requirement.
Example two
According to the method, a thickening structure under the working condition of Ma0.6 and 3 degrees is designed, the required thickness of the boundary layer of the downstream air inlet channel inlet 108 is 20.641mm at the attack angle of Ma0.6 and 3 degrees, the thickness of the freely developed boundary layer on the surface of the cylindrical machine body 1 without the trapezoid slope array is 16.714mm, the difference epsilon between the two is 3.927mm, the height h=0.854 epsilon=3.35 mm of the trapezoid slope 101 is determined, the obtained height of the trapezoid slope 101 is consistent with that of Ma0.5 and 3 degrees, and therefore, the thickening effect of the trapezoid slope array structure is the same as that of the first embodiment, and the thickening effect of the finally designed thickening structure is shown in Table 1. As shown in fig. 4, the boundary layer thickness increases significantly after passing through the trapezoidal ramp array. The boundary layer thickness before the thickened downstream inlet 108 is 20.065mm, and the error is 2.79% compared with the expected boundary layer thickness 20.641mm, which meets the requirements.
TABLE 1 Ma0.5,3 Angle of attack and Ma0.6,3 Angle of attack Condition example thickening results
Claims (10)
1. The artificial thickening structure of the boundary layer of the subsonic cylindrical engine body surface is characterized by comprising a cylindrical engine body (1) and a trapezoid slope array arranged on the engine body (1), wherein the trapezoid slope array comprises a plurality of trapezoid slopes (101) which are uniformly arranged along the circumferential direction of the engine body (1); the trapezoid slope (101) comprises a trapezoid bottom surface (107), a trapezoid top surface (102) and a connecting surface for connecting the trapezoid bottom surface (107) and the trapezoid top surface (102), wherein the trapezoid bottom surface (107) is located on the surface of the machine body (1), the trapezoid bottom surface (107) is coincident with the lower bottom of the trapezoid top surface (102), the trapezoid top surface (102) and the surface of the machine body (1) form a certain inclined angle so as to generate flow direction vortex on the surface of the machine body (1), and the vertical distance between the highest point of the trapezoid slope (101) and the surface of the machine body (1) is not higher than the local free development boundary layer thickness of the surface of the machine body (1).
2. The artificial thickening structure of the boundary layer of the subsonic cylindrical body surface according to claim 1, wherein the connecting surface comprises a first side (103) and a second side (104) connecting the side of the trapezoidal bottom surface (107) and the side of the trapezoidal top surface (102), and a top surface (105) connecting the upper bottom of the trapezoidal bottom surface (107) and the upper bottom of the trapezoidal top surface (102), one side of the top surface (105) coincides with one side of the first side (103), and the other side of the top surface (105) coincides with one side of the second side (104).
3. The artificial thickening structure of the boundary layer of the subsonic cylindrical engine body surface according to claim 2, wherein the trapezoid bottom surface (107), the trapezoid top surface (102) and the top surface (105) are all isosceles trapezoids, and the upper bottom length of the trapezoid bottom surface (107) is smaller than the upper bottom length of the trapezoid top surface (102); the plane of the top surface (105) is perpendicular to the axis of the machine body (1).
4. A structure for artificially thickening a boundary layer on a surface of a subsonic cylindrical body according to claim 3, wherein the first side (103) and the second side (104) are triangular, and the plane of the first side (103) and the plane of the second side (104) intersect with the axis of the body (1) at the same point.
5. The artificial thickening structure of the boundary layer of the subsonic cylindrical body surface according to claim 4, wherein the upper base length of the trapezoid top surface (102) is 1/3 of the lower base length of the trapezoid top surface (102).
6. The artificial thickening structure of the boundary layer of the subsonic cylindrical body surface according to claim 5, characterized in that the angle between the trapezoidal top surface (102) and the body (1) surface is 20 °.
7. The artificial thickening structure of the boundary layer of the subsonic cylindrical body surface according to claim 6, wherein the plurality of trapezoid slopes (101) comprises a plurality of trapezoid top surfaces (102), the bottoms of the plurality of trapezoid top surfaces (102) are arranged on the same circumference, and the distance between the bottoms of adjacent trapezoid top surfaces (102) is 60% of the length of the bottoms of the trapezoid top surfaces (102).
8. The artificial thickening structure of the boundary layer on the surface of the subsonic cylindrical engine body according to claim 7, wherein the engine body (1) is provided with a downstream air inlet channel inlet (108), the flow direction distance between the trapezoid slope array and the downstream air inlet channel inlet (108) is a, the axial length of the engine body (1) is b, and a/b is more than or equal to 0.125.
9. A method of designing an artificial thickening structure for a boundary layer of a subsonic cylindrical body surface according to any one of claims 1 to 8, comprising the steps of:
Step 1, preliminarily determining the height h of a trapezoid slope (101) according to the difference epsilon between the thickness of a boundary layer required by an inlet (108) of a downstream air inlet and the thickness of a freely developed boundary layer on the surface of a machine body (1) without a trapezoid slope array, wherein h=fepsilon, and f is less than 1;
Step 2, according to the height h of the trapezoid slope (101), the axial length l=h/tan alpha of the trapezoid slope is obtained, wherein alpha is the included angle between the trapezoid top surface (102) and the surface of the machine body (1);
step 3, determining the length a=l/sin 60 degrees of the bottom of the trapezoid top surface (102) according to the axial length l of the trapezoid slope (101);
step 4, determining that the upper bottom length b of the trapezoid top surface (102) is 1/3 of the lower bottom length a according to the lower bottom length of the trapezoid top surface (102);
step 5, according to the length of the bottom of the trapezoid top surface (102), determining that the distance between two adjacent trapezoid slopes (101) is 60% of the length a of the bottom of the trapezoid top surface (102);
step 6, determining the shape of the connecting surface to enable the trapezoid top surface (102) to be connected with the trapezoid bottom surface (107);
Step 7, determining the number of trapezoid slopes (101) in the trapezoid slope array;
step 8, performing CFD simulation check according to the design Mach number and attack angle;
and 9, adjusting the coefficient f according to the CFD simulation result, and repeating the steps 2-8 until the error between the thickness of the boundary layer at the inlet of the downstream air inlet and the thickness of the boundary layer actually required is smaller than a preset value.
10. The design method according to claim 9, wherein the step 7 specifically comprises: and determining the circumferential total length of the trapezoid slope array according to the range of the machine body (1) needing to thicken the boundary layer, wherein the quotient integer of the circumferential total length of the trapezoid slope array and the sum of the lower bottom length of the trapezoid top surface (102) of the trapezoid slope (101) and the interval between two adjacent trapezoid slopes (101) is used as the number of the trapezoid slopes (101) in the trapezoid slope array.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410149533.XA CN117969014A (en) | 2024-02-02 | 2024-02-02 | Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410149533.XA CN117969014A (en) | 2024-02-02 | 2024-02-02 | Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117969014A true CN117969014A (en) | 2024-05-03 |
Family
ID=90860797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410149533.XA Pending CN117969014A (en) | 2024-02-02 | 2024-02-02 | Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117969014A (en) |
-
2024
- 2024-02-02 CN CN202410149533.XA patent/CN117969014A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101258071B (en) | An element for generating a fluid dynamic force | |
| CN101392685B (en) | Internal waverider hypersonic inlet and design method based on random shock form | |
| EP1214521B1 (en) | Modified wind turbine airfoil | |
| Tang et al. | Passive separation control with blade-end slots in a highly loaded compressor cascade | |
| EP3431750B1 (en) | Method for determining arrangement position of vortex generator on wind turbine blade, method for producing wind turbine blade assembly, and wind turbine blade assembly | |
| CN113946904A (en) | Design method of large-size low-noise spray pipe | |
| CN117969014A (en) | Artificial thickening structure and design method for boundary layer on surface of subsonic cylindrical engine body | |
| CN201301751Y (en) | Inner wave rider type hypersonic speed air inlet channel based on arbitrary shaped shock wave | |
| CN113800001A (en) | Design method of internal shrinkage hypersonic inlet channel integrated with forebody | |
| CN113602473A (en) | Inflatable wing based on obliquely swept gas beam | |
| CN108502204A (en) | Hypersonic group of jib and cotter Waverider design method | |
| CN108304602B (en) | Design method and device for diamond type forced transition device of high-speed aircraft | |
| Kandil et al. | CFD analysis of GOE 387airfoil | |
| Mahallati et al. | Aerodynamics of a low-pressure turbine airfoil at low-reynolds numbers: part 1—steady flow measurements | |
| Shi et al. | Serpentine inlet design and analysis | |
| CN112883575B (en) | Impeller mechanical boundary layer transition model correction method considering surface roughness | |
| McWaters | F-35 conventional mode jet-effects testing methodology | |
| Selig | The design of airfoils at low Reynolds numbers | |
| Zamiri et al. | Influence of the inclined leading edge diffuser vanes on the aerodynamic performance of a transonic centrifugal compressor | |
| Wu et al. | Behaviour of tip-leakage flow in an axial flow compressor rotor | |
| Liu et al. | Design and analysis of HP-turbine for variable cycle engine | |
| CN112733268A (en) | Asymmetric trapezoid-like spray pipe throat design method | |
| Liu et al. | Effect of Bulging Upper Surface on Waverider Performances | |
| Chaney et al. | Expanding wake induction effects on thrust distribution on a rotor disc | |
| Calvert et al. | A quasi-three dimensional calculation system for the flow within transonic compressor blade rows |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination |