NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 200,000 Max Cl/Cd: 43 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20412-il-200000-n5.txt Download as CSV file: xf-sc20412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 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 -0.9592 0.07907 0.07413 -0.0382 1.0000 0.0270
-14.500 -0.9924 0.06977 0.06454 -0.0440 1.0000 0.0270
-14.250 -1.0140 0.06338 0.05790 -0.0473 1.0000 0.0272
-14.000 -1.0298 0.05828 0.05257 -0.0493 1.0000 0.0274
-13.750 -1.0418 0.05397 0.04802 -0.0506 1.0000 0.0277
-13.500 -1.0509 0.05020 0.04400 -0.0513 1.0000 0.0281
-13.250 -1.0571 0.04687 0.04041 -0.0515 1.0000 0.0285
-13.000 -1.0605 0.04392 0.03717 -0.0513 1.0000 0.0289
-12.750 -1.0558 0.04191 0.03508 -0.0509 1.0000 0.0293
-12.500 -1.0489 0.04024 0.03336 -0.0504 1.0000 0.0297
-12.250 -1.0417 0.03865 0.03169 -0.0498 1.0000 0.0301
-12.000 -1.0343 0.03712 0.03007 -0.0489 1.0000 0.0306
-11.750 -1.0268 0.03565 0.02849 -0.0479 1.0000 0.0311
-11.500 -1.0190 0.03423 0.02695 -0.0466 1.0000 0.0317
-11.250 -1.0083 0.03281 0.02538 -0.0457 1.0000 0.0325
-11.000 -0.9952 0.03142 0.02379 -0.0449 1.0000 0.0333
-10.750 -0.9806 0.03018 0.02243 -0.0441 1.0000 0.0341
-10.500 -0.9648 0.02921 0.02146 -0.0435 1.0000 0.0349
-10.250 -0.9480 0.02834 0.02054 -0.0429 1.0000 0.0359
-10.000 -0.9306 0.02745 0.01957 -0.0422 1.0000 0.0371
-9.750 -0.9126 0.02653 0.01853 -0.0413 1.0000 0.0384
-9.500 -0.8943 0.02561 0.01750 -0.0404 1.0000 0.0396
-9.250 -0.8759 0.02477 0.01668 -0.0397 1.0000 0.0406
-9.000 -0.8564 0.02408 0.01596 -0.0390 1.0000 0.0419
-8.750 -0.8363 0.02339 0.01522 -0.0383 1.0000 0.0436
-8.500 -0.8158 0.02273 0.01445 -0.0376 1.0000 0.0454
-8.250 -0.7958 0.02197 0.01372 -0.0369 1.0000 0.0469
-8.000 -0.7748 0.02136 0.01310 -0.0363 1.0000 0.0486
-7.750 -0.7533 0.02079 0.01249 -0.0358 1.0000 0.0508
-7.500 -0.7313 0.02026 0.01189 -0.0352 1.0000 0.0529
-7.250 -0.7097 0.01957 0.01124 -0.0348 1.0000 0.0550
-7.000 -0.6872 0.01904 0.01072 -0.0344 1.0000 0.0575
-6.750 -0.6641 0.01857 0.01020 -0.0341 1.0000 0.0604
-6.500 -0.6407 0.01799 0.00966 -0.0339 1.0000 0.0633
-6.250 -0.6167 0.01753 0.00920 -0.0338 1.0000 0.0665
-6.000 -0.5922 0.01713 0.00878 -0.0337 1.0000 0.0702
-5.750 -0.5609 0.01661 0.00832 -0.0352 0.9985 0.0751
-5.500 -0.5262 0.01620 0.00788 -0.0371 0.9961 0.0811
-5.250 -0.4910 0.01571 0.00745 -0.0393 0.9940 0.0887
-5.000 -0.4564 0.01528 0.00705 -0.0412 0.9915 0.0980
-4.750 -0.4217 0.01484 0.00666 -0.0432 0.9886 0.1106
-4.500 -0.3857 0.01435 0.00630 -0.0455 0.9860 0.1307
-4.250 -0.3486 0.01382 0.00595 -0.0482 0.9838 0.1647
-4.000 -0.3106 0.01320 0.00560 -0.0511 0.9819 0.2203
-3.750 -0.2731 0.01231 0.00519 -0.0544 0.9792 0.3156
-3.500 -0.2329 0.01128 0.00494 -0.0582 0.9774 0.4713
-3.250 -0.1991 0.01124 0.00533 -0.0592 0.9738 0.5689
-3.000 -0.1629 0.01132 0.00545 -0.0607 0.9710 0.6026
-2.750 -0.1285 0.01141 0.00552 -0.0620 0.9673 0.6238
-2.500 -0.0960 0.01153 0.00564 -0.0627 0.9627 0.6384
-2.250 -0.0619 0.01169 0.00580 -0.0637 0.9593 0.6525
-2.000 -0.0275 0.01191 0.00605 -0.0646 0.9563 0.6666
-1.750 0.0027 0.01212 0.00626 -0.0648 0.9500 0.6790
-1.500 0.0336 0.01234 0.00653 -0.0648 0.9449 0.6870
-1.250 0.0709 0.01233 0.00648 -0.0667 0.9416 0.6952
-1.000 0.0985 0.01244 0.00664 -0.0662 0.9339 0.6988
-0.750 0.1322 0.01242 0.00664 -0.0669 0.9273 0.7026
-0.500 0.1639 0.01235 0.00657 -0.0674 0.9165 0.7064
-0.250 0.1984 0.01218 0.00638 -0.0685 0.9042 0.7103
0.000 0.2316 0.01197 0.00611 -0.0692 0.8835 0.7132
0.250 0.2607 0.01185 0.00594 -0.0687 0.8591 0.7148
0.500 0.2886 0.01181 0.00589 -0.0681 0.8372 0.7165
0.750 0.3168 0.01179 0.00583 -0.0677 0.8129 0.7183
1.000 0.3449 0.01179 0.00575 -0.0673 0.7809 0.7202
1.250 0.3729 0.01183 0.00568 -0.0669 0.7428 0.7222
1.500 0.4003 0.01196 0.00560 -0.0665 0.6890 0.7244
1.750 0.4251 0.01235 0.00552 -0.0655 0.5813 0.7267
2.000 0.4469 0.01325 0.00565 -0.0646 0.4295 0.7293
2.250 0.4713 0.01400 0.00589 -0.0643 0.3262 0.7316
2.500 0.4954 0.01460 0.00616 -0.0637 0.2497 0.7332
2.750 0.5204 0.01513 0.00644 -0.0633 0.1947 0.7350
3.000 0.5463 0.01559 0.00672 -0.0631 0.1598 0.7370
3.250 0.5732 0.01595 0.00699 -0.0629 0.1386 0.7391
3.500 0.6005 0.01629 0.00728 -0.0629 0.1221 0.7412
3.750 0.6281 0.01664 0.00756 -0.0630 0.1094 0.7433
4.000 0.6558 0.01702 0.00786 -0.0632 0.0994 0.7456
4.250 0.6843 0.01734 0.00817 -0.0634 0.0914 0.7480
4.500 0.7109 0.01773 0.00854 -0.0633 0.0849 0.7497
4.750 0.7370 0.01808 0.00892 -0.0629 0.0794 0.7512
5.000 0.7624 0.01855 0.00935 -0.0625 0.0747 0.7529
5.250 0.7886 0.01893 0.00980 -0.0622 0.0705 0.7549
5.500 0.8143 0.01938 0.01025 -0.0619 0.0667 0.7573
5.750 0.8402 0.01989 0.01077 -0.0617 0.0634 0.7597
6.000 0.8667 0.02034 0.01128 -0.0615 0.0601 0.7622
6.250 0.8929 0.02086 0.01177 -0.0615 0.0572 0.7647
6.500 0.9181 0.02141 0.01238 -0.0611 0.0545 0.7667
6.750 0.9425 0.02193 0.01298 -0.0604 0.0520 0.7686
7.000 0.9666 0.02248 0.01355 -0.0599 0.0497 0.7708
7.250 0.9906 0.02313 0.01426 -0.0593 0.0476 0.7731
7.500 1.0151 0.02374 0.01497 -0.0588 0.0453 0.7754
7.750 1.0395 0.02437 0.01564 -0.0584 0.0436 0.7779
8.000 1.0630 0.02515 0.01638 -0.0580 0.0421 0.7805
8.250 1.0872 0.02589 0.01729 -0.0575 0.0403 0.7829
8.500 1.1095 0.02659 0.01811 -0.0566 0.0386 0.7850
8.750 1.1314 0.02728 0.01886 -0.0558 0.0373 0.7873
9.000 1.1525 0.02814 0.01974 -0.0549 0.0364 0.7898
9.250 1.1739 0.02917 0.02098 -0.0540 0.0352 0.7925
9.500 1.1950 0.03024 0.02221 -0.0532 0.0341 0.7952
9.750 1.2157 0.03125 0.02334 -0.0524 0.0331 0.7980
10.000 1.2349 0.03215 0.02433 -0.0513 0.0323 0.8003
10.250 1.2529 0.03305 0.02530 -0.0501 0.0316 0.8026
10.500 1.2694 0.03427 0.02665 -0.0487 0.0308 0.8052
10.750 1.2846 0.03573 0.02840 -0.0472 0.0300 0.8081
11.000 1.2985 0.03721 0.03009 -0.0457 0.0292 0.8112
11.250 1.3111 0.03872 0.03178 -0.0440 0.0286 0.8146
11.500 1.3210 0.04017 0.03342 -0.0420 0.0281 0.8174
11.750 1.3279 0.04160 0.03502 -0.0396 0.0277 0.8205
12.000 1.3310 0.04301 0.03656 -0.0368 0.0274 0.8240
12.250 1.3350 0.04463 0.03830 -0.0345 0.0271 0.8277
12.750 1.3372 0.04868 0.04260 -0.0304 0.0266 0.8342
13.000 1.3277 0.05190 0.04617 -0.0283 0.0264 0.8374
13.250 1.3148 0.05570 0.05030 -0.0269 0.0262 0.8408
13.500 1.2979 0.06029 0.05521 -0.0266 0.0260 0.8444
13.750 1.2767 0.06589 0.06112 -0.0275 0.0259 0.8476
14.000 1.2501 0.07285 0.06840 -0.0301 0.0259 0.8502
14.250 1.2160 0.08230 0.07817 -0.0357 0.0259 0.8526
14.500 1.1660 0.09743 0.09366 -0.0467 0.0261 0.8539
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