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74:, when it was decided to define two standard wind tunnel model configurations (AGARD-A and AGARD-B) to be used for exchange of test data and comparison of test results of same models tested in different wind tunnels. The idea was to establish standards of comparison between wind tunnels and improve the validity of wind tunnel tests. Among the standard wind tunnel models, AGARD model configuration B (AGARD-B) has become by far the most popular. Initially intended for the supersonic wind tunnels, the AGARD-B configuration has since been tested in many wind tunnels at a wide range of
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transition on the model. In order to reduce the scatter of results, in some wind tunnel facilities the model was tested with boundary layer transition trips near the leading edges of the wing and the nose of the body. On the other hand, a number of wind tunnel tests was made without fixed transition.
117:, or large deformations in the plan form of the wing would occur. In the past, this part of the specification was interpreted in different ways by model designers which led to small differences in shapes of the tested models. The recommended solution is to have the leading- and trailing-edge radii of
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Some free-flight tests of the AGARD-B model were performed. For these tests, the standard geometry was modified by adding, at the rear end of the body, two triangular vertical stabilisers, one on the ventral and one on the dorsal side of the body. Size of the vertical stabilizers was 50% of the wing
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configuration. The horizontal tail has an area equal to 1/6 of the wing area. Sections of the vertical and horizontal tail are circular arc profiles defined identically to the profile of the wing. Forward of the 1.5 D body extension, the geometry of the AGARD-C model is identical to that of the
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The longer body of the AGARD-C model and the existence of the tail make it easier to detect (from anomalies in the wind tunnel test results) if the shock waves reflected from the walls of the wind tunnel test section are passing too close to the rear end of the model. The existence of the tail
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In order to reduce cost and produce more versatile wind tunnel models, actual designs of AGARD-B and AGARD-C are sometimes realized as an AGARD-B configuration to which a body segment with the T-tail can be attached at the rear end to form the AGARD-C configuration.
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AGARD-B is a body-wing configuration. All its dimensions are given in terms of the body diameter "D" so that the model can be produced in any scale, as appropriate for a particular wind tunnel. The body is an 8.5 diameters long
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in order to reduce sting interference, but at that moment a number of wind tunnel tests had already been made. Therefore, published test results for the AGARD-B models do not all correspond to theoretical model configuration.
240:. Moments are reduced to a point in the plane of symmetry of the model, at the longitudinal position of 50% of the m.a.c. (however, in some published results, moments were reduced to a point at 25% of the m.a.c.).
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311:, in 1954, it was agreed to add a third model configuration to the family of AGARD calibration models, by extending the body of the AGARD-B by 1.5 diameters and by adding a horizontal and a vertical tail in the
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502:
Piland, R.O., "The Zero-Lift Drag of a 60 Delta-Wing-Body
Combination (AGARD Model 2) Obtained from Free-Flight Tests Between Mach Numbers 0.8 and 1.7", NACA TN-3081, Langley Aeronautical Laboratory, NACA,
31:, left, is joined by Air Force and NASA officials while inspecting two of the models used in the high velocity, high altitude wind tunnels at Arnold Air Force Base. The missiles are Agard-B and
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Anderson C.F., An
Investigation of the Aerodynamic Characteristics of the AGARD Model B for Mach Numbers from 0.1 to 1.0, AEDC-TR-70-100, Arnold Engineering Development Center, 1970
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An AGARD-C model with a body diameter of 115.7 mm. This configuration was assembled by attaching a 1.5-diameters-long body section to the rear end of the AGARD-B model shown in the
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Drag results with and without the fixed boundary layer transition differ, which should not be neglected when comparing test results from different wind tunnel laboratories.
78:, from low subsonic (Mach 0.1), through transonic (Mach 0.7 to 1.4) to hypersonic (up to Mach 8 and above). Therefore, a considerable database of test results is available.
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AGARD-B standard model is intended primarily for the measurement of aerodynamic forces and moments. Test results are most often presented in the form of nondimensional
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A drawing defining the geometry of the AGARD-B standard model and its sting fixture; all dimensions are relative to body diameter D (dimensions according to )
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in the form of an equilateral triangle with a span of four body diameters. Wing section is a symmetric cylindrical arc with a relative thickness t/c of 4%.
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AGARD-C is primarily used in the transonic wind tunnels and the database of published test results is somewhat smaller than the one for the AGARD-B model.
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consisting of a 5.5 diameters long cylindrical segment and a nose with a length of 3 diameters and having a local radius defined by the equation
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Some laboratories have selected to test the AGARD-B standard model for periodic checkouts of the quality of measurements in their wind tunnels.
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standard wind tunnel models. Its origin dates to the year 1952, and the Second
Meeting of the AGARD Wind Tunnel and Model Testing Panel in
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An AGARD-B model installed on a sting is shown in the test section of
Supersonic Wind Tunnel A in the von Kármán Gas Dynamics Facility
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to be used with the AGARD-B model was defined as well. The initial specification of the model called for a sting having a diameter of
54:(calibration model) that is used to verify, by comparison of test results with previously published data, the measurement chain in a
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An AGARD-B model installed on a sting is shown in the tank below
Supersonic Wind Tunnel A in the von Kármán Gas Dynamics Facility
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In some wind tunnel laboratories, AGARD-B was tested in non-standard configurations, e.g. as a half-model (half-span model).
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at the theoretical root chord and to decrease the radii towards the wing tips proportionally to the local chord.
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AGARD-B. Also, the position of the moments reduction point (the aerodynamic centre) is the same as on AGARD-B.
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113:. However, this specification is unclear. It is obvious that the specified radius can not be applied near the
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generally makes this model more sensitive than AGARD-B to flow curvature in the wind tunnel test section.
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491:"AGARD-B Standard Model Tests in JAXA 0.8 m by 0.45 m High Reynolds Number Transonic Wind Tunnel"
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for the AGARD-C model is identical to the sting for the AGARD-B model, having a length of
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The AGARD model in the B configuration is installed in the 16-foot transonic wind tunnel
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The AGARD model in the C configuration is installed in the 16-foot transonic wind tunnel
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175:. Reference area for the calculation of the coefficients is the theoretical wing area
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Specification for AGARD Wind Tunnel
Calibration Models, AGARD memorandum, AGARD, 1955
564:"Observations on Some Transonic Wind Tunnel Tests of a Standard Model with a T-Tail"
493:, JAXA-SP-09-005, Proceedings of the Wind Technology Association 81st meeting, 2009
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A drawing defining the geometry of the AGARD-C standard model and its sting fixture
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characteristics of the AGARD-B model were found to be somewhat sensitive to the
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523:"T-38 Wind-Tunnel Data Quality Assurance Based on Testing of a Standard Model"
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Aoki Y., Kanda H., Sato M., Nagai S., Itabashi Y., Nishijima H., Kimura T.
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while the reference length for the yawing and rolling moment coefficients
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540:"Testing of AGARD-B calibration model in the T-38 Trisonic Wind Tunnel"
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471:, AGARDograph 64, Aircraft Research Association Bedford, England, 1961
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Wind Tunnel
Calibration Models, AGARD Specification 2, AGARD, 1958
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Damljanovic D., Vukovic Ð., Vitic A., Isakovic J., Ocokoljic G.
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computed from the measured base pressure on the model. Likewise,
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529:, Vol. 50, No. 4 (2013), pp. 1141-1149. doi: 10.2514/1.C032081
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462:"A Review of Measurements on AGARD Calibration Models"
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obtained by subtracting, from the total measured drag
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AGARD models used at Arnold Air Force Base, Tennessee
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of the wing should be rounded with a radius equal to
538:Damljanovic D., Vitic A., Vukovic Ð., Isakovic J.,
43:An AGARD-B model with a body diameter of 115.7 mm
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192:pitching moment coefficient
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269:represents forebody lift.
160:size, i.e. their span was
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169:aerodynamic coefficients
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202:mean aerodynamic chord
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527:Journal of Aircraft
84:solid of revolution
29:Theodore von Kármán
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410:Wind tunnel
56:wind tunnel
581:Categories
460:Hills R.,
421:References
124:A support
88:y = x/3 ·
231:wing span
547:Archived
465:Archived
404:See also
229:is the
115:wingtips
35:. (1959)
346:Gallery
299:At the
276:AGARD-C
208:√
200:is the
183:√
171:in the
119:0.002 D
111:0.002 D
103:Leading
60:AGARD-C
48:AGARD-B
313:T-tail
309:France
238:= 4 D)
329:0.5 D
321:sting
305:Paris
301:AGARD
162:2.5 D
134:1.5 D
130:0.5 D
126:sting
99:delta
97:is a
72:Italy
64:AGARD
50:is a
503:1954
222:and
146:drag
144:The
105:and
95:wing
93:The
68:Rome
325:3 D
236:ref
213:D/3
181:= 4
179:ref
138:3 D
583::
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447:^
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331:.
307:,
262:xb
248:xf
234:(B
164:.
90:.
70:,
260:C
255:x
253:C
246:C
226:l
224:C
219:n
217:C
210:3
206:4
197:m
195:C
188:D
185:3
177:S
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