NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il) Reynolds number: 200,000 Max Cl/Cd: 39.88 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20012-il-200000-n5.txt Download as CSV file: xf-sc20012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0012 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9984 0.08336 0.07878 -0.0187 1.0000 0.0246
-14.500 -1.0455 0.07076 0.06582 -0.0271 1.0000 0.0244
-14.250 -1.0719 0.06348 0.05828 -0.0308 1.0000 0.0245
-14.000 -1.0906 0.05803 0.05259 -0.0326 1.0000 0.0246
-13.750 -1.1045 0.05359 0.04791 -0.0335 1.0000 0.0248
-13.500 -1.1150 0.04980 0.04386 -0.0335 1.0000 0.0251
-13.250 -1.1227 0.04648 0.04028 -0.0330 1.0000 0.0254
-13.000 -1.1277 0.04354 0.03708 -0.0319 1.0000 0.0258
-12.750 -1.1299 0.04093 0.03419 -0.0305 1.0000 0.0261
-12.500 -1.1280 0.03878 0.03183 -0.0290 1.0000 0.0265
-12.250 -1.1216 0.03725 0.03023 -0.0274 1.0000 0.0268
-12.000 -1.1142 0.03589 0.02879 -0.0257 1.0000 0.0271
-11.750 -1.1059 0.03463 0.02742 -0.0239 1.0000 0.0276
-11.500 -1.0967 0.03341 0.02609 -0.0219 1.0000 0.0281
-11.250 -1.0846 0.03216 0.02471 -0.0203 1.0000 0.0287
-11.000 -1.0707 0.03086 0.02325 -0.0189 1.0000 0.0295
-10.750 -1.0554 0.02956 0.02174 -0.0176 1.0000 0.0304
-10.500 -1.0391 0.02845 0.02054 -0.0164 1.0000 0.0312
-10.250 -1.0215 0.02763 0.01969 -0.0153 1.0000 0.0320
-10.000 -1.0027 0.02683 0.01882 -0.0144 1.0000 0.0332
-9.750 -0.9832 0.02595 0.01782 -0.0134 1.0000 0.0348
-9.500 -0.9636 0.02506 0.01682 -0.0125 1.0000 0.0362
-9.250 -0.9433 0.02437 0.01612 -0.0117 1.0000 0.0375
-9.000 -0.9224 0.02366 0.01535 -0.0108 1.0000 0.0392
-8.750 -0.9009 0.02291 0.01446 -0.0100 1.0000 0.0410
-8.500 -0.8801 0.02219 0.01374 -0.0092 1.0000 0.0426
-8.250 -0.8582 0.02162 0.01316 -0.0085 1.0000 0.0446
-8.000 -0.8358 0.02106 0.01250 -0.0078 1.0000 0.0471
-7.750 -0.8143 0.02042 0.01186 -0.0070 1.0000 0.0492
-7.500 -0.7921 0.01992 0.01136 -0.0062 1.0000 0.0517
-7.250 -0.7697 0.01944 0.01081 -0.0054 1.0000 0.0545
-7.000 -0.7489 0.01884 0.01023 -0.0045 1.0000 0.0570
-6.750 -0.7278 0.01838 0.00979 -0.0035 1.0000 0.0598
-6.500 -0.7075 0.01797 0.00934 -0.0023 1.0000 0.0627
-6.250 -0.6807 0.01740 0.00879 -0.0026 0.9948 0.0659
-6.000 -0.6481 0.01689 0.00829 -0.0040 0.9855 0.0698
-5.750 -0.6157 0.01642 0.00779 -0.0053 0.9756 0.0740
-5.500 -0.5841 0.01590 0.00730 -0.0065 0.9657 0.0788
-5.250 -0.5522 0.01551 0.00686 -0.0075 0.9552 0.0843
-5.000 -0.5226 0.01504 0.00646 -0.0082 0.9437 0.0913
-4.750 -0.4930 0.01465 0.00607 -0.0087 0.9331 0.0999
-4.500 -0.4648 0.01428 0.00573 -0.0090 0.9222 0.1118
-4.250 -0.4379 0.01389 0.00541 -0.0089 0.9121 0.1281
-4.000 -0.4114 0.01350 0.00510 -0.0088 0.9030 0.1514
-3.750 -0.3861 0.01306 0.00482 -0.0085 0.8942 0.1843
-3.500 -0.3615 0.01257 0.00454 -0.0081 0.8861 0.2348
-3.250 -0.3378 0.01200 0.00426 -0.0076 0.8791 0.3036
-3.000 -0.3156 0.01129 0.00399 -0.0069 0.8719 0.4017
-2.750 -0.2950 0.01057 0.00385 -0.0055 0.8656 0.5253
-2.500 -0.2717 0.01034 0.00403 -0.0043 0.8595 0.6275
-2.250 -0.2448 0.01034 0.00406 -0.0038 0.8533 0.6668
-2.000 -0.2177 0.01037 0.00407 -0.0034 0.8482 0.6936
-1.750 -0.1908 0.01039 0.00410 -0.0029 0.8439 0.7151
-1.500 -0.1634 0.01041 0.00415 -0.0025 0.8384 0.7335
-1.250 -0.1361 0.01044 0.00419 -0.0022 0.8333 0.7497
-1.000 -0.1091 0.01047 0.00425 -0.0016 0.8290 0.7637
-0.750 -0.0819 0.01050 0.00430 -0.0011 0.8252 0.7764
-0.500 -0.0543 0.01054 0.00435 -0.0009 0.8202 0.7890
-0.250 -0.0272 0.01056 0.00443 -0.0004 0.8150 0.7998
0.000 0.0000 0.01057 0.00443 0.0000 0.8091 0.8091
0.250 0.0272 0.01056 0.00443 0.0004 0.7998 0.8150
0.500 0.0543 0.01054 0.00435 0.0009 0.7890 0.8202
0.750 0.0819 0.01050 0.00430 0.0011 0.7762 0.8252
1.000 0.1091 0.01047 0.00425 0.0016 0.7637 0.8290
1.250 0.1361 0.01044 0.00419 0.0022 0.7497 0.8333
1.500 0.1634 0.01041 0.00415 0.0025 0.7335 0.8384
1.750 0.1908 0.01039 0.00410 0.0029 0.7151 0.8439
2.000 0.2177 0.01037 0.00407 0.0034 0.6935 0.8482
2.250 0.2448 0.01034 0.00406 0.0038 0.6667 0.8533
2.500 0.2717 0.01034 0.00402 0.0043 0.6274 0.8595
2.750 0.2950 0.01057 0.00385 0.0055 0.5252 0.8656
3.000 0.3156 0.01129 0.00399 0.0069 0.4017 0.8719
3.250 0.3378 0.01200 0.00426 0.0076 0.3036 0.8791
3.500 0.3615 0.01257 0.00454 0.0081 0.2349 0.8861
3.750 0.3861 0.01306 0.00482 0.0085 0.1843 0.8942
4.000 0.4114 0.01350 0.00510 0.0088 0.1513 0.9030
4.250 0.4379 0.01389 0.00541 0.0089 0.1281 0.9121
4.500 0.4648 0.01428 0.00573 0.0089 0.1118 0.9222
4.750 0.4931 0.01465 0.00607 0.0087 0.0999 0.9331
5.000 0.5227 0.01504 0.00646 0.0082 0.0913 0.9437
5.250 0.5523 0.01551 0.00686 0.0075 0.0843 0.9553
5.500 0.5841 0.01590 0.00730 0.0065 0.0788 0.9657
5.750 0.6158 0.01642 0.00779 0.0053 0.0739 0.9757
6.000 0.6481 0.01689 0.00828 0.0040 0.0698 0.9855
6.250 0.6808 0.01740 0.00879 0.0026 0.0659 0.9949
6.500 0.7074 0.01797 0.00933 0.0023 0.0627 1.0000
6.750 0.7278 0.01838 0.00979 0.0035 0.0598 1.0000
7.000 0.7489 0.01884 0.01023 0.0045 0.0570 1.0000
7.250 0.7697 0.01944 0.01080 0.0054 0.0545 1.0000
7.500 0.7921 0.01992 0.01136 0.0062 0.0517 1.0000
7.750 0.8143 0.02042 0.01186 0.0069 0.0492 1.0000
8.000 0.8358 0.02106 0.01250 0.0077 0.0471 1.0000
8.250 0.8582 0.02162 0.01316 0.0085 0.0446 1.0000
8.500 0.8802 0.02219 0.01374 0.0092 0.0426 1.0000
8.750 0.9011 0.02291 0.01446 0.0100 0.0410 1.0000
9.000 0.9225 0.02366 0.01535 0.0108 0.0392 1.0000
9.250 0.9435 0.02437 0.01612 0.0116 0.0375 1.0000
9.500 0.9637 0.02506 0.01682 0.0124 0.0362 1.0000
9.750 0.9834 0.02595 0.01782 0.0134 0.0347 1.0000
10.000 1.0029 0.02683 0.01882 0.0143 0.0332 1.0000
10.250 1.0217 0.02763 0.01969 0.0153 0.0320 1.0000
10.500 1.0394 0.02845 0.02054 0.0163 0.0312 1.0000
10.750 1.0557 0.02956 0.02175 0.0175 0.0304 1.0000
11.000 1.0711 0.03087 0.02325 0.0188 0.0295 1.0000
11.250 1.0850 0.03216 0.02471 0.0203 0.0287 1.0000
11.500 1.0971 0.03341 0.02609 0.0218 0.0281 1.0000
11.750 1.1064 0.03463 0.02743 0.0238 0.0276 1.0000
12.000 1.1147 0.03589 0.02879 0.0256 0.0271 1.0000
12.250 1.1223 0.03725 0.03023 0.0273 0.0268 1.0000
12.500 1.1287 0.03879 0.03183 0.0288 0.0265 1.0000
12.750 1.1305 0.04095 0.03421 0.0304 0.0261 1.0000
13.000 1.1284 0.04356 0.03710 0.0318 0.0258 1.0000
13.250 1.1235 0.04649 0.04030 0.0328 0.0254 1.0000
13.500 1.1159 0.04981 0.04387 0.0334 0.0251 1.0000
13.750 1.1053 0.05361 0.04793 0.0333 0.0248 1.0000
14.000 1.0914 0.05807 0.05263 0.0325 0.0246 1.0000
14.250 1.0729 0.06351 0.05831 0.0306 0.0245 1.0000
14.500 1.0465 0.07081 0.06589 0.0268 0.0244 1.0000
14.750 0.9985 0.08363 0.07907 0.0182 0.0246 1.0000
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