WO2000060328A1 - Wind tunnel airfoil mounting apparatus - Google Patents

Wind tunnel airfoil mounting apparatus Download PDF

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Publication number
WO2000060328A1
WO2000060328A1 PCT/GB2000/001046 GB0001046W WO0060328A1 WO 2000060328 A1 WO2000060328 A1 WO 2000060328A1 GB 0001046 W GB0001046 W GB 0001046W WO 0060328 A1 WO0060328 A1 WO 0060328A1
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WO
WIPO (PCT)
Prior art keywords
airfoil
mounting block
intersection
mounting
bores
Prior art date
Application number
PCT/GB2000/001046
Other languages
French (fr)
Inventor
Michael John Guatieri
Original Assignee
Bae Systems Plc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Bae Systems Plc filed Critical Bae Systems Plc
Priority to AU33096/00A priority Critical patent/AU3309600A/en
Publication of WO2000060328A1 publication Critical patent/WO2000060328A1/en

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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

Definitions

  • This invention relates to apparatus for reieasably mounting at least one airfoil in a wind tunnel.
  • a number of aerodynamic design iterations are required to arrive at the final configuration for an airfoil such as a wing for a new project.
  • the number of design iterations tested annually in a wind tunnel has been limited to one or two iterations, primarily because the time taken to machine and assemble the associated model components is so significant.
  • Such testing has conventionally been carried out by means of machining and mounting model wings on a model fuselage, and typical configurations of model components, described with reference to Figure 6 of the accompanying drawings, have included two wing root block extensions, 23, 24 each of which is bolted on inside to a fuselage component 25 and both of which engage with and are connected together by a bottom strap 26.
  • the wing root block extensions 23, 24 are in one piece with the wing profile 27, 28 and the means of attachment thereof to the fuselage component 25.
  • the time required to machine these components is significant, and represents one of the major time factors in a complete design iteration.
  • attachment of the wing root block extensions 23, 24 to the fuselage component 25 and bottom strap 26 is exceedingly time consuming due to the accuracy required in engagement of the components with respect to one another. This accuracy is essential in order confidently to use the aerodynamic and mechanical characteristics of the models as part of the design iteration.
  • wind tunnel airfoil mounting apparatus including an airfoil and a mounting block for the airfoil, the airfoil being mounted to the mounting block at an intersection, wherein the intersection is defined substantially in a single plane.
  • intersection may be defined at a section taken through a root extremity of the airfoil and may occur at an interface of a generally planar surface defined on one of the mounting block and airfoil and a relieved generally planar surface on the other of the mounting block and airfoil.
  • the relieved generally planar surface may be centrally relieved leaving a peripheral contact area for the two generally planar surfaces adjacent an aerodynamic outer surface of the airfoil.
  • the mounting block and airfoil may be connected together by at least one tensile fastener extending therebetween and passing through the relief whereby to form a known moment arm between a longitudinal axis of the fastener and the peripheral contact area, for the transmission of aerodynamic loads between the airfoil and the mounting block.
  • the apparatus may include at least 2 locating pins extending between the mounting block and the airfoil to locate the mounting block and airfoil with respect to each other in the plane of the intersection.
  • the apparatus may include a number of tensile fasteners to secure the airfoil to the mounting block, each tensile fastener being adjusted to pass through a clearance bore in the mounting block into a threaded bore in the airfoil.
  • the apparatus may include a pair of said airfoils mounted to the mounting block.
  • the mounting block may define a chamber therein to receive at least one tensile fastener for attaching a said airfoil to the mounting block.
  • intersection may define at least one aperture to receive means to transmit information about aerodynamic pressure at at least one position on the airfoil surface.
  • the releasable connecting means includes at least two first bores, each extending through the first mounting surface into the mounting block, at least two second blind bores, each extending through the second mounting surface into the at least one airfoil, at least two locating pins, each locatable in respective first bores at one end and engageable in respective second blind bores at the other end so as to provide a face to face relationship when the at least.
  • one airfoil is offered up to the mounting block, a series of internally threaded blind bores each extending through the second mounting surface into the at least one airfoil, a series of open-ended clearance bores each opening at one end through the first mounting surface, extending through the mounting block, and opening at an end remote from the first surface through a further surface of the mounting block, and a series of threaded shank bolts insertable through said open-ended clearance bores via the further surface in the mounting block for engagement with the correspondingly threaded bores in the at least one airfoil so as to connect said at least one airfoil with said mounting block when in the pin-located face to face relationship.
  • the at least two first bores are blind bores.
  • the mounting block includes a first elongated part, which first elongated part has a channel extending therealong, with the first mounting surface, the first bores and the clearance bores being provided on or in said first part, and with the further surface being provided by a wall of one or more access recesses located in a surface of the first elongated part opposite to the channel, a second elongated part, which second elongated part has a key shaped to fit into the channel, and bolt means for releasably securing together said first and second elongated parts.
  • the second airfoil has a third mounting surface at or adjacent to one end thereof.
  • the mounting block has a fourth mounting surface, which fourth mounting surface is spaced from said first mounting surface such that the first and fourth mounting surfaces are symmetrically located about a longitudinal axis of the mounting block.
  • the second and third mounting surfaces are substantially perpendicular to an upper lifting surface of each said airfoil.
  • Figure 1 is a perspective view of apparatus for releasably mounting one airfoil according to a first embodiment of the present invention
  • Figure 2 is a perspective view from below of the apparatus of Figure 1 , showing releasable connecting means
  • Figure 3 is a perspective view of apparatus for releasably mounting two airfoils according to a second embodiment of the present invention
  • Figure 4 is a perspective view from below of the apparatus of Figure 3,
  • Figure 5a, 5b, 5c show respectively plan, end and perspective views of a jig supporting an airfoil according to the first or second embodiments of the present invention.
  • Figure 6 is a perspective view of conventional apparatus for the positioning of model aircraft wings in wind tunnels, according to the prior art.
  • Apparatus for releasably mounting at least one airfoil in a wind tunnel is intended for use in wind tunnels where the aerodynamic and mechanical characteristics of scale models of airfoils are tested and the test results used by a design team, wholly or partially to redesign the airfoil and/or manufacture another airfoil made to a new design. This is necessarily an iterative process, and both the time taken to machine a number of airfoils and the time taken to interchange therebetween during wind tunnel testing is significant to the overall design budget.
  • apparatus for releasably mounting an airfoil 1 in a wind tunnel includes a mounting block 2 locatable in a wind tunnel and defining an intersection 23 at a first mounting surface 3, an airfoil 1 having a second mounting surface 4 at a root extremity thereof and releasable connecting means 5, shown in Figure 2, for releasably connecting the first and second mounting surfaces 3, 4 together at the intersection 23.
  • the surface 3 is relieved in the area 24 bound by the line 25.
  • a peripheral contact area 28 is defined between the line 25 and the dotted line 26.
  • the dotted line 26 represents a line of contact of a root peripheral edge 27 of the airfoil with the surface 3, when the airfoil is attached to the mounting block.
  • the releasable connecting means 5 includes first bores 6a, 6b which are blind bores, each extending through the first mounting surface 3 into the mounting block 2.
  • Two second blind bores 7a, 7b each extend through the second mounting surface 4 into the airfoil 1
  • two locating pins 8a, 8b each locate in respective first bores 6a, 6b at one end and engage in respective blind mounting bores 7a, 7b at the other end so as to locate the mounting block and airfoil with respect to each other in the plane of the intersection when the airfoil 1 is offered up to the mounting block 2.
  • the releasable connecting means 5 also includes a series of internally threaded blind bores 9 each extending through the second mounting surface 4 into the airfoil 1 , a series of open-ended clearance bores 10 opening through the first mounting surface 3, extending through the mounting block 2 and opening through a further surface 3b of the mounting block 2, and a series of threaded shank bolts 11, 11b.
  • the bolts 11 , 11b are inserted into the clearance bores 10 at an open end thereof 10b via the further surface 3b so as to protrude from the surface 3 for engagement with the correspondingly threaded bores 9 in the airfoil 1.
  • the bolts 11 , 11b rigidly connect the airfoil 1 to the mounting block 2 when in the pin-located face to face relationship, as shown in exploded detail in Figure 2.
  • the threaded shank bolts, clearance bores and threaded bores 11b, 10b, 9b differ from threaded shank bolts, clearance bores and threaded bores 11, 10, 9 by their size and position with respect to the blind bores and locating pins 6a, 6b, 7a, 7b, 8a, 8b.
  • the mounting block 2 shown in Figure 1 includes a first elongated part 12 which has a channel 15 extending therealong, with the first mounting surface 3, the first bores 6a, 6b and the clearance bores 10 being provided on or in said first elongated part 12.
  • the first mounting surface 3 extends substantially parallel to the channel 15.
  • the mounting block also includes a second elongated part 13 having a key 16 shaped to fit into a recess 30 in the channel 15, and bolts 14 for releasably securing together said first and second elongated parts 12, 13 of the mounting block 2 after connection of the airfoil 1 to the first part 12.
  • the first part 12 also provides access for the threaded shank bolts 11, 11b to be inserted into the clearance bores 10 and thence into the internally threaded bores 9, 9a by means of access recesses 15b, 15c, 15d located in a surface 15a.
  • the recesses 15b, 15c, 15d are dimensioned with respect to the length of the bolts 11 , 11b such that sufficient access is afforded thereto when securing or removing the airfoil 1 to or from the first part 12.
  • the mounting block 2 defines, at the intersection 23, an aperture 29 (mirrored by a co-operating aperture (not shown) in the airfoil 1 ) to receive means to transmit information about aerodynamic pressure at at least one position on the airfoil surface. These transmission means are in the form of pressure taps.
  • Figures 3 and 4 show apparatus generally similar to that of Figures 1 and
  • the second airfoil 17 has a third mounting surface 18 at one end thereof.
  • the mounting block 2 has a fourth mounting surface 19, which is spaced from the first mounting surface 3, such that the first and fourth mounting surfaces 3, 19 are symmetrically located about a longitudinal axis 20 of the mounting block 2.
  • the second and third mounting surfaces 4, 18 are substantially perpendicular to an upper lifting surface 21 , shown in Figure 4, of both airfoils 1 , 17.
  • Disassembly of the parts of the second embodiment involves firstly removing the bolts 14 and the second part 13 of the mounting block 2 from the first part 12.
  • the airfoils 1 , 17 are then detached from the first part 12 of the mounting block 2 by removal of the threaded shank bolts 11 , 11b, which bolts are accessible through recesses 15b, 15c, 15d located in the underside 15a of the first part 12. Removal of said bolts 11 , 11b is typically effected for each of the two airfoils 1, 17 in turn, and for the purposes of this description it is assumed that airfoil 1 is removed first.
  • a jig 22 is positioned to prop the airfoil 1 as the bolts 11 , 11b are removed through the recesses 15b, 15c, 15d in order to provide support to the locating pins 8a, 8b which are engaged in all four bores 6a, 6b, 7a, 7b.
  • the airfoil 1 can be withdrawn from the first part 12 of the mounting block 2, and separated from the locating pins 8a, 8b.
  • These pins are preferably dowels which are a shrink fit into the first bores 6a, 6b and a close clearance fit on the second blind bores 7a, 7b.
  • the removal of the second airfoil 17 is carried out in the same manner as described above.

Abstract

Wind tunnel airfoil mounting apparatus includes an airfoil (1) and a mounting block (2) for the airfoil. The airfoil (1) is mounted to the mounting block (2) at an intersection (23) at the root end of the airfoil, such that the intersection is defined substantially in a single plane.

Description

WIND TUNNEL AIRFOIL MOUNTING APPARATUS
This invention relates to apparatus for reieasably mounting at least one airfoil in a wind tunnel.
A number of aerodynamic design iterations are required to arrive at the final configuration for an airfoil such as a wing for a new project. Traditionally the number of design iterations tested annually in a wind tunnel has been limited to one or two iterations, primarily because the time taken to machine and assemble the associated model components is so significant. Such testing has conventionally been carried out by means of machining and mounting model wings on a model fuselage, and typical configurations of model components, described with reference to Figure 6 of the accompanying drawings, have included two wing root block extensions, 23, 24 each of which is bolted on inside to a fuselage component 25 and both of which engage with and are connected together by a bottom strap 26. Conventionally, the wing root block extensions 23, 24 are in one piece with the wing profile 27, 28 and the means of attachment thereof to the fuselage component 25. The time required to machine these components is significant, and represents one of the major time factors in a complete design iteration. Moreover, attachment of the wing root block extensions 23, 24 to the fuselage component 25 and bottom strap 26 is exceedingly time consuming due to the accuracy required in engagement of the components with respect to one another. This accuracy is essential in order confidently to use the aerodynamic and mechanical characteristics of the models as part of the design iteration.
There is therefore a need for apparatus for releasably mounting at least one airfoil in a wind tunnel, which apparatus requires less machining and shorter assembly times.
According to the present invention there is provided wind tunnel airfoil mounting apparatus including an airfoil and a mounting block for the airfoil, the airfoil being mounted to the mounting block at an intersection, wherein the intersection is defined substantially in a single plane.
The intersection may be defined at a section taken through a root extremity of the airfoil and may occur at an interface of a generally planar surface defined on one of the mounting block and airfoil and a relieved generally planar surface on the other of the mounting block and airfoil.
The relieved generally planar surface may be centrally relieved leaving a peripheral contact area for the two generally planar surfaces adjacent an aerodynamic outer surface of the airfoil.
The mounting block and airfoil may be connected together by at least one tensile fastener extending therebetween and passing through the relief whereby to form a known moment arm between a longitudinal axis of the fastener and the peripheral contact area, for the transmission of aerodynamic loads between the airfoil and the mounting block.
The apparatus may include at least 2 locating pins extending between the mounting block and the airfoil to locate the mounting block and airfoil with respect to each other in the plane of the intersection. The apparatus may include a number of tensile fasteners to secure the airfoil to the mounting block, each tensile fastener being adjusted to pass through a clearance bore in the mounting block into a threaded bore in the airfoil.
The apparatus may include a pair of said airfoils mounted to the mounting block.
The mounting block may define a chamber therein to receive at least one tensile fastener for attaching a said airfoil to the mounting block.
The intersection may define at least one aperture to receive means to transmit information about aerodynamic pressure at at least one position on the airfoil surface.
Preferably the releasable connecting means includes at least two first bores, each extending through the first mounting surface into the mounting block, at least two second blind bores, each extending through the second mounting surface into the at least one airfoil, at least two locating pins, each locatable in respective first bores at one end and engageable in respective second blind bores at the other end so as to provide a face to face relationship when the at least. one airfoil is offered up to the mounting block, a series of internally threaded blind bores each extending through the second mounting surface into the at least one airfoil, a series of open-ended clearance bores each opening at one end through the first mounting surface, extending through the mounting block, and opening at an end remote from the first surface through a further surface of the mounting block, and a series of threaded shank bolts insertable through said open-ended clearance bores via the further surface in the mounting block for engagement with the correspondingly threaded bores in the at least one airfoil so as to connect said at least one airfoil with said mounting block when in the pin-located face to face relationship.
Conveniently the at least two first bores are blind bores.
Advantageously the mounting block includes a first elongated part, which first elongated part has a channel extending therealong, with the first mounting surface, the first bores and the clearance bores being provided on or in said first part, and with the further surface being provided by a wall of one or more access recesses located in a surface of the first elongated part opposite to the channel, a second elongated part, which second elongated part has a key shaped to fit into the channel, and bolt means for releasably securing together said first and second elongated parts.
Preferably, where there are two airfoils, the second airfoil has a third mounting surface at or adjacent to one end thereof.
Conveniently the mounting block has a fourth mounting surface, which fourth mounting surface is spaced from said first mounting surface such that the first and fourth mounting surfaces are symmetrically located about a longitudinal axis of the mounting block.
Advantageously the second and third mounting surfaces are substantially perpendicular to an upper lifting surface of each said airfoil.
For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which: Figure 1 is a perspective view of apparatus for releasably mounting one airfoil according to a first embodiment of the present invention,
Figure 2 is a perspective view from below of the apparatus of Figure 1 , showing releasable connecting means,
Figure 3 is a perspective view of apparatus for releasably mounting two airfoils according to a second embodiment of the present invention,
Figure 4 is a perspective view from below of the apparatus of Figure 3,
Figure 5a, 5b, 5c show respectively plan, end and perspective views of a jig supporting an airfoil according to the first or second embodiments of the present invention, and
Figure 6 is a perspective view of conventional apparatus for the positioning of model aircraft wings in wind tunnels, according to the prior art.
Apparatus for releasably mounting at least one airfoil in a wind tunnel, as shown in Figures 1 to 5c of the accompanying drawings, is intended for use in wind tunnels where the aerodynamic and mechanical characteristics of scale models of airfoils are tested and the test results used by a design team, wholly or partially to redesign the airfoil and/or manufacture another airfoil made to a new design. This is necessarily an iterative process, and both the time taken to machine a number of airfoils and the time taken to interchange therebetween during wind tunnel testing is significant to the overall design budget.
Thus as shown in Figure 1 of the accompanying drawings, apparatus for releasably mounting an airfoil 1 in a wind tunnel according to a first embodiment of the present invention includes a mounting block 2 locatable in a wind tunnel and defining an intersection 23 at a first mounting surface 3, an airfoil 1 having a second mounting surface 4 at a root extremity thereof and releasable connecting means 5, shown in Figure 2, for releasably connecting the first and second mounting surfaces 3, 4 together at the intersection 23. The surface 3 is relieved in the area 24 bound by the line 25. A peripheral contact area 28 is defined between the line 25 and the dotted line 26. The dotted line 26 represents a line of contact of a root peripheral edge 27 of the airfoil with the surface 3, when the airfoil is attached to the mounting block.
The releasable connecting means 5 includes first bores 6a, 6b which are blind bores, each extending through the first mounting surface 3 into the mounting block 2. Two second blind bores 7a, 7b, each extend through the second mounting surface 4 into the airfoil 1 , and two locating pins 8a, 8b, each locate in respective first bores 6a, 6b at one end and engage in respective blind mounting bores 7a, 7b at the other end so as to locate the mounting block and airfoil with respect to each other in the plane of the intersection when the airfoil 1 is offered up to the mounting block 2.
The releasable connecting means 5 also includes a series of internally threaded blind bores 9 each extending through the second mounting surface 4 into the airfoil 1 , a series of open-ended clearance bores 10 opening through the first mounting surface 3, extending through the mounting block 2 and opening through a further surface 3b of the mounting block 2, and a series of threaded shank bolts 11, 11b. The bolts 11 , 11b are inserted into the clearance bores 10 at an open end thereof 10b via the further surface 3b so as to protrude from the surface 3 for engagement with the correspondingly threaded bores 9 in the airfoil 1. The bolts 11 , 11b rigidly connect the airfoil 1 to the mounting block 2 when in the pin-located face to face relationship, as shown in exploded detail in Figure 2. The threaded shank bolts, clearance bores and threaded bores 11b, 10b, 9b differ from threaded shank bolts, clearance bores and threaded bores 11, 10, 9 by their size and position with respect to the blind bores and locating pins 6a, 6b, 7a, 7b, 8a, 8b.
The mounting block 2 shown in Figure 1 includes a first elongated part 12 which has a channel 15 extending therealong, with the first mounting surface 3, the first bores 6a, 6b and the clearance bores 10 being provided on or in said first elongated part 12. The first mounting surface 3 extends substantially parallel to the channel 15. The mounting block also includes a second elongated part 13 having a key 16 shaped to fit into a recess 30 in the channel 15, and bolts 14 for releasably securing together said first and second elongated parts 12, 13 of the mounting block 2 after connection of the airfoil 1 to the first part 12. The first part 12 also provides access for the threaded shank bolts 11, 11b to be inserted into the clearance bores 10 and thence into the internally threaded bores 9, 9a by means of access recesses 15b, 15c, 15d located in a surface 15a. The recesses 15b, 15c, 15d are dimensioned with respect to the length of the bolts 11 , 11b such that sufficient access is afforded thereto when securing or removing the airfoil 1 to or from the first part 12.
The mounting block 2 defines, at the intersection 23, an aperture 29 (mirrored by a co-operating aperture (not shown) in the airfoil 1 ) to receive means to transmit information about aerodynamic pressure at at least one position on the airfoil surface. These transmission means are in the form of pressure taps. Figures 3 and 4 show apparatus generally similar to that of Figures 1 and
2, in which like parts have been given like reference numerals and will not be described further in detail. In this second embodiment, and as shown in Figure
3, there are two airfoils 1 , 17, and the second airfoil 17 has a third mounting surface 18 at one end thereof. The mounting block 2 has a fourth mounting surface 19, which is spaced from the first mounting surface 3, such that the first and fourth mounting surfaces 3, 19 are symmetrically located about a longitudinal axis 20 of the mounting block 2. As can be seen from both Figures 1 and 3, the second and third mounting surfaces 4, 18 are substantially perpendicular to an upper lifting surface 21 , shown in Figure 4, of both airfoils 1 , 17.
In both embodiments of the present invention, the simplicity afforded by the reduced number of parts and reduced number of contact surfaces compared to conventional attachment assemblies such as that of Figure 6 is striking.
Disassembly of the parts of the second embodiment involves firstly removing the bolts 14 and the second part 13 of the mounting block 2 from the first part 12. The airfoils 1 , 17 are then detached from the first part 12 of the mounting block 2 by removal of the threaded shank bolts 11 , 11b, which bolts are accessible through recesses 15b, 15c, 15d located in the underside 15a of the first part 12. Removal of said bolts 11 , 11b is typically effected for each of the two airfoils 1, 17 in turn, and for the purposes of this description it is assumed that airfoil 1 is removed first. As shown in Figures 5a, 5b and 5c, a jig 22 is positioned to prop the airfoil 1 as the bolts 11 , 11b are removed through the recesses 15b, 15c, 15d in order to provide support to the locating pins 8a, 8b which are engaged in all four bores 6a, 6b, 7a, 7b.
Once the bolts 11 , 11b have been removed, the airfoil 1 can be withdrawn from the first part 12 of the mounting block 2, and separated from the locating pins 8a, 8b. These pins are preferably dowels which are a shrink fit into the first bores 6a, 6b and a close clearance fit on the second blind bores 7a, 7b. The removal of the second airfoil 17 is carried out in the same manner as described above.

Claims

1. Wind tunnel airfoil mounting apparatus including an airfoil and a mounting block for the airfoil, the airfoil being mounted to the mounting block at an intersection, wherein the intersection is defined substantially in a single plane.
2. Apparatus as in claim 1 in which the intersection is defined at a section taken through a root extremity of the airfoil.
3. Apparatus as in claim 1 or 2 in which the intersection occurs at an interface of a generally planar surface defined on one of the mounting block and airfoil and a relieved generally planar surface on the other of the mounting block and airfoil.
4. Apparatus as in claim 3 in which the relieved generally planar surface is centrally relieved leaving a peripheral contact area for the two generally planar surfaces adjacent an aerodynamic outer surface of the airfoil.
5. Apparatus as in claim 4 in which the mounting block and airfoil are connected together by at least one tensile fastener extending therebetween and passing through the relief whereby to form a known moment arm between a longitudinal axis of the fastener and the peripheral contact area, for the transmission of aerodynamic loads between the airfoil and the mounting block.
6. Apparatus as in any preceding claim including at least 2 locating pins extending between the mounting block and the airfoil to locate the mounting block and airfoil with respect to each other in the plane of the intersection.
7. Apparatus as in any preceding claim including a number of tensile fasteners to secure the airfoil to the mounting block, each tensile fastener being adapted to pass through a clearance bore in the mounting block into a threaded bore in the airfoil.
8. Apparatus as in any preceding claim including a pair of said airfoils mounted to the mounting block.
9. Apparatus as in any preceding claim in which the mounting block defines a chamber therein to receive at least one tensile fastener for attaching a said airfoil to the mounting block.
10. Apparatus as in any preceding claim in which the intersection defines at least one aperture to receive means to transmit information about aerodynamic pressure at at least one position on the airfoil surface.
PCT/GB2000/001046 1999-04-07 2000-03-21 Wind tunnel airfoil mounting apparatus WO2000060328A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU33096/00A AU3309600A (en) 1999-04-07 2000-03-21 Wind tunnel airfoil mounting apparatus

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9907785.1 1999-04-07
GBGB9907785.1A GB9907785D0 (en) 1999-04-07 1999-04-07 Mounting apparatus for airfoil apparatus

Publications (1)

Publication Number Publication Date
WO2000060328A1 true WO2000060328A1 (en) 2000-10-12

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GB (1) GB9907785D0 (en)
WO (1) WO2000060328A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2065693A2 (en) * 2007-11-28 2009-06-03 Airbus Espana, S.L. Use of a device to join the parts of a model designed for use in tests in a wind tunnel and the corresponding device

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2767577A (en) * 1954-01-13 1956-10-23 Gilbert Charles Allen X-beam strain gauge dynamometer
US4475385A (en) * 1983-03-31 1984-10-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Model mount system for testing flutter
US5056361A (en) * 1990-09-18 1991-10-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Dual strain gage balance system for measuring light loads

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2767577A (en) * 1954-01-13 1956-10-23 Gilbert Charles Allen X-beam strain gauge dynamometer
US4475385A (en) * 1983-03-31 1984-10-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Model mount system for testing flutter
US5056361A (en) * 1990-09-18 1991-10-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Dual strain gage balance system for measuring light loads

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2065693A2 (en) * 2007-11-28 2009-06-03 Airbus Espana, S.L. Use of a device to join the parts of a model designed for use in tests in a wind tunnel and the corresponding device
EP2065693A3 (en) * 2007-11-28 2011-01-12 Airbus Operations S.L. Use of a device to join the parts of a model designed for use in tests in a wind tunnel and the corresponding device

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Publication number Publication date
AU3309600A (en) 2000-10-23
GB9907785D0 (en) 1999-06-02

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