WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 200,000 Max Cl/Cd: 39.17 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-whitcomb-il-200000-n5.txt Download as CSV file: xf-whitcomb-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8749 0.07957 0.07457 -0.0536 1.0000 0.0290
-14.000 -0.9149 0.06941 0.06413 -0.0598 1.0000 0.0289
-13.750 -0.9424 0.06292 0.05741 -0.0626 1.0000 0.0289
-13.500 -0.9639 0.05801 0.05229 -0.0637 1.0000 0.0290
-13.250 -0.9814 0.05403 0.04810 -0.0637 1.0000 0.0291
-13.000 -0.9957 0.05070 0.04457 -0.0630 1.0000 0.0292
-12.750 -1.0076 0.04784 0.04152 -0.0617 1.0000 0.0294
-12.500 -1.0174 0.04535 0.03884 -0.0600 1.0000 0.0296
-12.250 -1.0259 0.04316 0.03646 -0.0578 1.0000 0.0298
-12.000 -1.0335 0.04127 0.03438 -0.0552 1.0000 0.0300
-11.750 -1.0400 0.03966 0.03264 -0.0521 1.0000 0.0302
-11.500 -1.0413 0.03832 0.03124 -0.0494 1.0000 0.0304
-11.250 -1.0364 0.03695 0.02982 -0.0477 1.0000 0.0307
-11.000 -1.0289 0.03563 0.02844 -0.0463 1.0000 0.0310
-10.750 -1.0191 0.03434 0.02708 -0.0452 1.0000 0.0314
-10.500 -1.0071 0.03307 0.02572 -0.0444 1.0000 0.0319
-10.250 -0.9932 0.03181 0.02435 -0.0437 1.0000 0.0325
-10.000 -0.9776 0.03060 0.02302 -0.0431 1.0000 0.0332
-9.750 -0.9605 0.02945 0.02172 -0.0426 1.0000 0.0341
-9.500 -0.9420 0.02838 0.02047 -0.0421 1.0000 0.0350
-9.250 -0.9231 0.02736 0.01946 -0.0418 1.0000 0.0358
-9.000 -0.9025 0.02648 0.01857 -0.0416 1.0000 0.0367
-8.750 -0.8811 0.02563 0.01766 -0.0415 1.0000 0.0378
-8.500 -0.8591 0.02479 0.01674 -0.0413 1.0000 0.0389
-8.250 -0.8363 0.02399 0.01583 -0.0411 1.0000 0.0402
-8.000 -0.8130 0.02314 0.01499 -0.0412 1.0000 0.0414
-7.750 -0.7884 0.02245 0.01429 -0.0415 1.0000 0.0429
-7.500 -0.7631 0.02182 0.01362 -0.0418 1.0000 0.0449
-7.250 -0.7373 0.02121 0.01295 -0.0421 1.0000 0.0470
-7.000 -0.7105 0.02056 0.01234 -0.0428 1.0000 0.0492
-6.750 -0.6832 0.02003 0.01178 -0.0434 1.0000 0.0518
-6.500 -0.6553 0.01949 0.01122 -0.0440 1.0000 0.0547
-6.250 -0.6267 0.01899 0.01075 -0.0449 1.0000 0.0581
-6.000 -0.5980 0.01857 0.01029 -0.0456 1.0000 0.0620
-5.750 -0.5680 0.01808 0.00986 -0.0468 1.0000 0.0666
-5.500 -0.5382 0.01769 0.00947 -0.0477 1.0000 0.0720
-5.250 -0.5074 0.01727 0.00909 -0.0489 1.0000 0.0790
-5.000 -0.4761 0.01687 0.00875 -0.0502 1.0000 0.0874
-4.750 -0.4444 0.01651 0.00844 -0.0516 1.0000 0.0980
-4.500 -0.4121 0.01616 0.00817 -0.0531 1.0000 0.1118
-4.250 -0.3791 0.01581 0.00794 -0.0547 1.0000 0.1299
-3.750 -0.3076 0.01513 0.00755 -0.0592 0.9994 0.1872
-3.500 -0.2696 0.01473 0.00736 -0.0621 0.9992 0.2284
-3.250 -0.2280 0.01419 0.00715 -0.0659 0.9995 0.2970
-3.000 -0.1747 0.01326 0.00723 -0.0726 1.0000 0.4833
-2.750 -0.1740 0.01465 0.00921 -0.0644 0.9967 0.5635
-2.500 -0.1499 0.01545 0.01007 -0.0626 0.9945 0.6044
-2.250 -0.1110 0.01553 0.01005 -0.0653 0.9937 0.6292
-2.000 -0.0774 0.01570 0.01016 -0.0667 0.9921 0.6436
-1.750 -0.0441 0.01591 0.01032 -0.0680 0.9907 0.6554
-1.500 -0.0184 0.01643 0.01085 -0.0669 0.9880 0.6631
-1.250 0.0159 0.01678 0.01119 -0.0680 0.9856 0.6721
-1.000 0.0461 0.01717 0.01162 -0.0677 0.9800 0.6772
-0.750 0.0935 0.01739 0.01183 -0.0712 0.9731 0.6871
-0.500 0.1281 0.01755 0.01206 -0.0708 0.9608 0.6918
-0.250 0.1701 0.01728 0.01181 -0.0727 0.9476 0.6985
0.250 0.2363 0.01663 0.01123 -0.0734 0.9218 0.7051
0.500 0.2652 0.01633 0.01098 -0.0729 0.9077 0.7069
0.750 0.2925 0.01602 0.01072 -0.0723 0.8891 0.7087
1.000 0.3225 0.01555 0.01027 -0.0720 0.8528 0.7107
1.250 0.4218 0.01621 0.00893 -0.0845 0.4332 0.7104
1.500 0.4443 0.01685 0.00907 -0.0838 0.3288 0.7125
1.750 0.4717 0.01731 0.00916 -0.0843 0.2526 0.7148
2.000 0.5020 0.01770 0.00923 -0.0854 0.1948 0.7167
2.250 0.5315 0.01802 0.00934 -0.0860 0.1555 0.7183
2.500 0.5567 0.01834 0.00952 -0.0855 0.1278 0.7192
2.750 0.5827 0.01863 0.00971 -0.0852 0.1077 0.7200
3.000 0.6094 0.01892 0.00992 -0.0850 0.0932 0.7207
3.250 0.6364 0.01922 0.01017 -0.0848 0.0824 0.7214
3.500 0.6629 0.01956 0.01045 -0.0846 0.0746 0.7223
3.750 0.6897 0.01987 0.01075 -0.0844 0.0683 0.7235
4.000 0.7167 0.02023 0.01110 -0.0843 0.0634 0.7245
4.250 0.7443 0.02058 0.01144 -0.0843 0.0593 0.7253
4.500 0.7717 0.02101 0.01184 -0.0843 0.0558 0.7262
4.750 0.7995 0.02139 0.01225 -0.0844 0.0526 0.7270
5.000 0.8267 0.02186 0.01270 -0.0845 0.0500 0.7281
5.250 0.8540 0.02237 0.01324 -0.0845 0.0478 0.7293
5.500 0.8819 0.02284 0.01374 -0.0846 0.0454 0.7304
5.750 0.9094 0.02336 0.01424 -0.0848 0.0435 0.7312
6.000 0.9365 0.02403 0.01492 -0.0849 0.0420 0.7320
6.250 0.9640 0.02468 0.01566 -0.0849 0.0405 0.7327
6.500 0.9913 0.02535 0.01637 -0.0850 0.0392 0.7334
6.750 1.0183 0.02600 0.01703 -0.0851 0.0380 0.7342
7.000 1.0423 0.02680 0.01781 -0.0846 0.0369 0.7348
7.250 1.0667 0.02757 0.01876 -0.0839 0.0358 0.7355
7.500 1.0908 0.02838 0.01971 -0.0833 0.0347 0.7361
7.750 1.1146 0.02926 0.02070 -0.0827 0.0338 0.7366
8.000 1.1380 0.03014 0.02167 -0.0820 0.0331 0.7371
8.250 1.1609 0.03105 0.02263 -0.0814 0.0325 0.7376
8.500 1.1832 0.03209 0.02372 -0.0807 0.0320 0.7381
8.750 1.2045 0.03343 0.02525 -0.0798 0.0315 0.7386
9.000 1.2243 0.03494 0.02705 -0.0786 0.0310 0.7391
9.250 1.2424 0.03659 0.02897 -0.0773 0.0304 0.7396
9.500 1.2590 0.03831 0.03097 -0.0758 0.0299 0.7401
9.750 1.2739 0.04004 0.03295 -0.0741 0.0294 0.7407
10.000 1.2874 0.04168 0.03481 -0.0723 0.0290 0.7413
10.250 1.2997 0.04327 0.03659 -0.0705 0.0285 0.7421
10.500 1.3108 0.04481 0.03829 -0.0685 0.0282 0.7429
10.750 1.3207 0.04632 0.03994 -0.0664 0.0279 0.7436
11.000 1.3278 0.04803 0.04180 -0.0642 0.0276 0.7442
11.250 1.3301 0.04990 0.04381 -0.0613 0.0274 0.7447
11.500 1.3220 0.05246 0.04663 -0.0574 0.0273 0.7451
11.750 1.3047 0.05601 0.05054 -0.0533 0.0272 0.7455
12.000 1.2825 0.06015 0.05504 -0.0500 0.0271 0.7459
12.250 1.2554 0.06517 0.06039 -0.0479 0.0270 0.7461
12.500 1.2226 0.07167 0.06723 -0.0483 0.0270 0.7464
12.750 1.1866 0.08040 0.07626 -0.0528 0.0271 0.7465
|
Polar data table (+)
Polar graphs
<< Back to WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)