Deformed geometries

The CAD models correspond to the NASA-CRM wing-body-horizontal tail.

The wing geometry accounts for the experimentally measured deformation.


Reference Area, S = 594,720.0 in2

Reference Chord, c = 275.80 in

Reference Span, b = 2,313.50 in

Moment Reference (X,Y,Z) = (1,325.90, 468.75, 177.95) in


NOTE: the CAD models are provided in full-scale model (inches). Simulations should be run at JAXA's wind-tunnel-scale model (mm). The scaling factor to convert from full-scale to wind-tunnel-scale is the following:

scaling_factor = full_scale_span_inches / wind_tunnel_scale_span_mm = 2313.50 / 1269.27 = 1.82270124...

IGES Files

Angle of attack File
1.22deg wbh_aoa122_buffet_deformed_updatednose.iges.gz
2.29deg wbh_aoa229_buffet_deformed_updatednose.iges.gz
4.84deg wbh_aoa484_buffet_deformed_updatednose.iges.gz
5.89deg wbh_aoa589_buffet_deformed_updatednose.iges.gz

NOTE: The original geometries have been smoothed and named with the "*_updatednose" suffix (credit: HeldenAero).

Deformation informations

For each angle of attack, the deformation is averaged over 10 images. Each image was taken with two cameras using stereo pattern matching technique and 0.65sec exposure time. Since the main wing vibration time scale is much smaller than the camera exposure time, the wing vibrations cannot be detected and the measured deformation should be considered as an approximate mean deformation.



Position before deformation AoA = 1.22deg AoA = 2.29deg AoA = 4.84deg AoA = 5.89deg
Marker ID x[mm] y[mm] z[mm] Δz[mm] Δα[deg] Δz[mm] Δα[deg] Δz[mm] Δα[deg] Δz[mm] Δα[deg]
201 558.610 105.191 -15.721 0.357 0.389 0.295 0.287
202 651.608 105.191 -22.207 0.439 -0.023 0.463 -0.022 0.382 -0.021 0.393 -0.028
203 744.183 105.191 -35.747 0.425 0.457 0.360 0.374
204 632.574 215.746 -16.204 0.525 0.594 0.447 0.450
205 699.777 215.746 -16.136 0.635 -0.097 0.746 -0.123 0.600 -0.127 0.600 -0.132
206 766.844 215.746 -23.570 0.754 0.882 0.746 0.759
207 729.204 350.702 -9.925 1.071 1.414 1.373 1.414
208 780.545 350.702 -7.286 1.302 -0.263 1.707 -0.333 1.718 -0.418 1.779 -0.423
209 832.002 350.702 -11.605 1.543 2.011 2.122 2.173
210 836.606 498.954 5.173 2.612 3.662 4.345 4.438
211 873.418 498.954 7.676 2.907 -0.456 4.020 -0.560 4.819 -0.722 4.913 -0.721
212 910.394 498.954 5.397 3.199 4.381 5.273 5.365
213 880.023 558.864 13.814 3.440 4.853 5.977 6.094
214 910.963 558.864 16.284 3.678 -0.507 5.182 -0.627 6.364 -0.773 6.456 -0.784
215 942.081 558.864 14.538 3.987 5.530 6.812 6.940
216 923.446 618.774 23.298 4.336 6.146 7.689 7.799
217 948.521 618.774 25.615 4.487 -0.447 6.356 -0.573 7.984 -0.774 8.111 -0.769
218 973.781 618.774 24.835 4.725 6.646 8.364 8.470
Δz : Amount of deflection
Δα : Amount of torsion

*The above values are measured on the 2.16% model using JAXA wind tunnel test.


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