Experimental data


The data shown in this page are measured on the 2.16% NASA-CRM model using JAXA wind tunnel test.

Reference Area, S = 0.179014 m2

Reference Chord, c = 0.15131 m( = MAC)

Reference Span, b = 1.26927 m( = span)

Moment Reference (X,Y,Z) = (0.72741, 0.0, 0.097627) m


For more details on the data, see the following reference (available from the NASA Common Research Model website here):

Shunsuke Koike, Makoto Ueno, Kazuyuki Nakakita and Atsushi Hashimoto, "Unsteady Pressure Measurement of Transonic Buffet on NASA Common Research Model", AIAA 2016-4044, June 2016.


Information on trip dots

Trip Aeronautical trip dot (CAD Cut)
Diameter [mm] 1.27
Distance (between dot centers) [mm] 2.54
Height (main wing) [mm] 0.11430 (inner-wing)
0.09906 (mid-wing)
0.08890 (outer-wing)
Location (main wing) 10% chord (upper and lower sides)
Height (horizontal stabilizers) [mm] 0.09906
Location (horizontal stabilizers) 10% chord (upper and lower sides)
Height (body) [mm] 0.08890
Location (body) 1.5% body length (azimuthally around the nose)

Inner wing: wing-body junction to Yehudi break (trailing-edge discontinuous bend); Mid/Outer wing: equally divided from Yehudi break to wing-tip.

Aerodynamic coefficients

The values are corrected for JAXA wind tunnel test.



RunNo. CaseNo. Re P0 T0 M α CD CL CmS CSV file
4912 20 1.52 80.0 323 0.849 1.22 0.0209 0.2718 6.503e-2 buffet_cdclcm_dpw8.csv
(Data from CaseNo.16 to 45)
4912 21 1.52 80.0 323 0.849 2.29 0.0249 0.4237 2.508e-2
4912 31 1.52 80.0 323 0.849 4.84 0.0588 0.6872 -0.193e-2
4912 41 1.52 80.0 323 0.848 5.89 0.0780 0.7598 0.984e-2
Re : Reynolds number [million] based on MAC
P0 : Total pressure [kPa]
T0 : Total temperature [K]
M : Corrected Mach number [-]
α : Corrected angle of attack [deg]
CD : Corrected drag coefficient [-]
CL : Corrected lift coefficient [-]
CmS : Corrected pitching moment coefficient [-]


Cp distributions (Average,RMS)

Cp data was measured by:

- Cp by steady pressure sensor (ESP)

- Cp of average and RMS by unsteady pressure sensor (Kulite)

NOTE: The full-span model has a right "steady" wing and a left "unsteady" wing. Due to different equipment, right and left wings are structurally different, and therefore do not deform in the same way. Deformation measurements and CAD refer to the left "unsteady" wing, for which Kulite data are provided. Steady pressure sensor measurements from the right "steady" wing are also provided for reference. Differences in deformations result in slight differences between the steady (ESP) and time-averaged unsteady (Kulite) pressure measurements.



Span location y[mm] η Cp data (CSV format)
Section E 317.318 0.500 buffet_wingcp_dpw8.csv
Section F 380.781 0.600


Unsteady pressure data (Time history,PSD)

Cp data by unsteady pressure sensor (Kulite)


Port
No.		 x/c
(Upper surface)		 Span location Cp data
(CSV format)
CH1 0.2819 Section E
η = 0.500

Time history(α=1.22deg):
buffet_cp_time_aoa122.csv

Time history(α=2.29deg):
buffet_cp_time_aoa229.csv

Time history(α=4.84deg):
buffet_cp_time_aoa484.csv

Time history(α=5.89deg):
buffet_cp_time_aoa589.csv


PSD [1/Hz](α=1.22deg):
buffet_cp_psd_aoa122.csv

PSD [1/Hz](α=2.29deg):
buffet_cp_psd_aoa229.csv

PSD [1/Hz](α=4.84deg):
buffet_cp_psd_aoa484.csv

PSD [1/Hz](α=5.89deg):
buffet_cp_psd_aoa589.csv
CH2 0.3040
CH3 0.3260
CH4 0.3480
CH5 0.3700
CH6 0.3920
CH7 0.4140
CH8 0.4360
CH9 0.4581
CH10 0.5700
CH11 0.6800
CH12 0.7903
CH13 0.1605 Section F
η = 0.600
CH14 0.1854
CH15 0.2102
CH16 0.2351
CH17 0.2600
CH18 0.2848
CH19 0.3097
CH20 0.3346
CH21 0.3595
CH22 0.4950
CH23 0.6310
CH24 0.7677

*PSD of Cp are calculated from time history data under the following conditions

Δt [s] : 0.00002
Number of samples : 499,712
Number of samples per block : 8,192
Number of averages : 121
Overlap : 0.5 (50%)
Window function : Not used
Output values : One-sided power spectral density
Unit : 1/Hz
Normalization : The integral value of PSD corresponds to the RMS in the time direction.


Deformation informations



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


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