WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 200,000 Max Cl/Cd: 30.1 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-whitcomb-il-200000.txt Download as CSV file: xf-whitcomb-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7429 0.08477 0.08039 -0.0499 1.0000 0.0558
-11.750 -0.7360 0.08195 0.07759 -0.0490 1.0000 0.0550
-11.500 -0.7532 0.07631 0.07192 -0.0508 1.0000 0.0544
-11.250 -0.7827 0.07013 0.06566 -0.0526 1.0000 0.0536
-11.000 -0.8194 0.06444 0.05984 -0.0529 1.0000 0.0528
-10.750 -0.9536 0.05229 0.04685 -0.0498 1.0000 0.0490
-10.500 -0.9621 0.04835 0.04259 -0.0494 1.0000 0.0489
-10.250 -0.9517 0.04632 0.04054 -0.0486 1.0000 0.0495
-10.000 -0.9400 0.04457 0.03875 -0.0479 1.0000 0.0503
-9.750 -0.9317 0.04181 0.03576 -0.0476 1.0000 0.0508
-9.500 -0.9207 0.03882 0.03245 -0.0477 1.0000 0.0512
-9.250 -0.9058 0.03596 0.02927 -0.0478 1.0000 0.0517
-9.000 -0.8876 0.03351 0.02652 -0.0479 1.0000 0.0524
-8.750 -0.8670 0.03136 0.02407 -0.0480 1.0000 0.0533
-8.500 -0.8446 0.02952 0.02191 -0.0481 1.0000 0.0545
-8.250 -0.8207 0.02795 0.02003 -0.0483 1.0000 0.0558
-8.000 -0.7988 0.02652 0.01868 -0.0478 1.0000 0.0576
-7.750 -0.7746 0.02561 0.01773 -0.0477 1.0000 0.0596
-7.500 -0.7497 0.02463 0.01663 -0.0475 1.0000 0.0618
-7.250 -0.7236 0.02377 0.01556 -0.0475 1.0000 0.0638
-7.000 -0.7009 0.02254 0.01443 -0.0468 1.0000 0.0664
-6.750 -0.6752 0.02191 0.01381 -0.0468 1.0000 0.0697
-6.500 -0.6483 0.02135 0.01312 -0.0469 1.0000 0.0733
-6.250 -0.6239 0.02038 0.01229 -0.0465 1.0000 0.0771
-6.000 -0.5968 0.01984 0.01174 -0.0467 1.0000 0.0819
-5.750 -0.5697 0.01910 0.01105 -0.0470 1.0000 0.0873
-5.500 -0.5412 0.01858 0.01057 -0.0475 1.0000 0.0940
-5.250 -0.5113 0.01789 0.00997 -0.0485 1.0000 0.1025
-5.000 -0.4798 0.01728 0.00943 -0.0498 1.0000 0.1141
-4.750 -0.4460 0.01665 0.00894 -0.0517 1.0000 0.1312
-4.500 -0.4102 0.01602 0.00846 -0.0541 1.0000 0.1580
-4.250 -0.3693 0.01524 0.00801 -0.0579 1.0000 0.2048
-4.000 -0.3152 0.01406 0.00744 -0.0652 1.0000 0.3114
-3.750 -0.2792 0.01362 0.00837 -0.0669 1.0000 0.5311
-3.500 -0.2871 0.01514 0.01018 -0.0569 1.0000 0.5807
-3.250 -0.2573 0.01566 0.01060 -0.0573 1.0000 0.6294
-3.000 -0.2282 0.01628 0.01111 -0.0574 1.0000 0.6555
-2.750 -0.2203 0.01722 0.01208 -0.0518 1.0000 0.6636
-2.500 -0.2035 0.01793 0.01278 -0.0487 1.0000 0.6752
-2.250 -0.1808 0.01848 0.01329 -0.0472 1.0000 0.6880
-2.000 -0.1727 0.01906 0.01391 -0.0419 1.0000 0.6922
-1.750 -0.1464 0.01944 0.01425 -0.0416 1.0000 0.7040
-1.500 -0.1383 0.01985 0.01471 -0.0363 1.0000 0.7081
-1.250 -0.1111 0.02021 0.01504 -0.0363 1.0000 0.7199
-1.000 -0.1068 0.02054 0.01543 -0.0302 1.0000 0.7248
-0.750 -0.0823 0.02088 0.01578 -0.0295 1.0000 0.7368
-0.500 -0.0760 0.02107 0.01602 -0.0241 1.0000 0.7424
-0.250 -0.0482 0.02132 0.01627 -0.0245 1.0000 0.7532
0.000 -0.0428 0.02144 0.01646 -0.0190 1.0000 0.7604
0.250 -0.0207 0.02172 0.01677 -0.0173 0.9978 0.7725
0.500 0.0297 0.02221 0.01729 -0.0206 0.9855 0.7866
0.750 0.0674 0.02220 0.01734 -0.0215 0.9747 0.7949
1.000 0.1318 0.02212 0.01727 -0.0289 0.9620 0.8006
1.250 0.1670 0.02150 0.01672 -0.0293 0.9502 0.8038
1.500 0.2101 0.02087 0.01615 -0.0314 0.9369 0.8071
1.750 0.2619 0.01990 0.01526 -0.0349 0.9198 0.8101
2.000 0.3045 0.01896 0.01439 -0.0369 0.8971 0.8127
2.250 0.3405 0.01819 0.01369 -0.0379 0.8625 0.8149
2.500 0.4428 0.01787 0.01161 -0.0489 0.4658 0.8175
2.750 0.4541 0.01862 0.01167 -0.0460 0.3292 0.8190
3.000 0.4737 0.01930 0.01181 -0.0450 0.2243 0.8200
3.250 0.4956 0.01991 0.01203 -0.0443 0.1638 0.8217
3.500 0.5217 0.02045 0.01234 -0.0444 0.1310 0.8225
3.750 0.5492 0.02101 0.01274 -0.0448 0.1125 0.8228
4.000 0.5767 0.02149 0.01315 -0.0451 0.1007 0.8240
4.250 0.6059 0.02194 0.01358 -0.0457 0.0921 0.8249
4.500 0.6352 0.02267 0.01422 -0.0464 0.0855 0.8251
4.750 0.6659 0.02309 0.01466 -0.0473 0.0796 0.8252
5.000 0.6964 0.02406 0.01552 -0.0483 0.0750 0.8256
5.250 0.7274 0.02462 0.01617 -0.0491 0.0713 0.8265
5.500 0.7581 0.02525 0.01676 -0.0500 0.0675 0.8269
5.750 0.7899 0.02645 0.01795 -0.0512 0.0646 0.8269
6.000 0.8212 0.02733 0.01899 -0.0520 0.0622 0.8269
6.250 0.8520 0.02831 0.02006 -0.0528 0.0601 0.8270
6.500 0.8822 0.02934 0.02109 -0.0537 0.0581 0.8275
6.750 0.9119 0.03114 0.02300 -0.0545 0.0563 0.8281
7.000 0.9390 0.03246 0.02466 -0.0546 0.0548 0.8283
7.250 0.9651 0.03426 0.02677 -0.0545 0.0538 0.8282
7.500 0.9891 0.03637 0.02921 -0.0542 0.0531 0.8282
7.750 1.0101 0.03896 0.03218 -0.0534 0.0527 0.8281
8.000 1.0263 0.04221 0.03589 -0.0521 0.0527 0.8280
8.250 1.0380 0.04593 0.04009 -0.0503 0.0528 0.8283
8.500 1.0428 0.05053 0.04519 -0.0480 0.0534 0.8287
8.750 1.0418 0.05577 0.05088 -0.0455 0.0548 0.8288
9.000 1.0492 0.05994 0.05521 -0.0444 0.0560 0.8287
9.250 0.8888 0.08767 0.08452 -0.0382 0.0845 0.8276
9.500 0.8441 0.09842 0.09544 -0.0472 0.0828 0.8271
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