NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 100,000 Max Cl/Cd: 30.52 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20414-il-100000-n5.txt Download as CSV file: xf-sc20414-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0414 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8357 0.08888 0.08211 -0.0455 1.0000 0.0512
-14.000 -0.8858 0.07766 0.07059 -0.0522 1.0000 0.0510
-13.750 -0.9215 0.07006 0.06268 -0.0558 1.0000 0.0511
-13.500 -0.9495 0.06415 0.05645 -0.0577 1.0000 0.0514
-13.250 -0.9731 0.05922 0.05117 -0.0586 1.0000 0.0518
-13.000 -0.9699 0.05702 0.04895 -0.0584 1.0000 0.0524
-12.750 -0.9676 0.05489 0.04674 -0.0582 1.0000 0.0531
-12.500 -0.9671 0.05265 0.04441 -0.0577 1.0000 0.0539
-12.250 -0.9677 0.05036 0.04198 -0.0570 1.0000 0.0547
-12.000 -0.9687 0.04810 0.03954 -0.0560 1.0000 0.0555
-11.750 -0.9691 0.04593 0.03717 -0.0547 1.0000 0.0564
-11.500 -0.9689 0.04386 0.03487 -0.0530 1.0000 0.0574
-11.250 -0.9664 0.04182 0.03254 -0.0515 1.0000 0.0585
-11.000 -0.9542 0.04044 0.03113 -0.0505 1.0000 0.0596
-10.750 -0.9418 0.03929 0.02997 -0.0494 1.0000 0.0608
-10.500 -0.9297 0.03809 0.02871 -0.0483 1.0000 0.0623
-10.250 -0.9172 0.03679 0.02728 -0.0471 1.0000 0.0640
-10.000 -0.9038 0.03545 0.02571 -0.0457 1.0000 0.0658
-9.750 -0.8879 0.03431 0.02455 -0.0445 1.0000 0.0673
-9.500 -0.8724 0.03338 0.02366 -0.0432 1.0000 0.0689
-9.250 -0.8570 0.03247 0.02271 -0.0420 1.0000 0.0711
-9.000 -0.8411 0.03153 0.02165 -0.0406 1.0000 0.0736
-8.750 -0.8248 0.03061 0.02067 -0.0392 1.0000 0.0758
-8.500 -0.8087 0.02980 0.01993 -0.0379 1.0000 0.0779
-8.250 -0.7924 0.02904 0.01916 -0.0366 1.0000 0.0807
-8.000 -0.7755 0.02831 0.01832 -0.0352 1.0000 0.0839
-7.750 -0.7592 0.02754 0.01760 -0.0338 1.0000 0.0866
-7.500 -0.7424 0.02685 0.01696 -0.0326 1.0000 0.0898
-7.250 -0.7249 0.02621 0.01628 -0.0313 1.0000 0.0938
-7.000 -0.7075 0.02552 0.01562 -0.0302 1.0000 0.0976
-6.750 -0.6895 0.02489 0.01504 -0.0292 1.0000 0.1020
-6.500 -0.6704 0.02435 0.01445 -0.0283 1.0000 0.1073
-6.250 -0.6513 0.02368 0.01390 -0.0276 1.0000 0.1127
-6.000 -0.6309 0.02316 0.01338 -0.0270 1.0000 0.1196
-5.750 -0.6099 0.02258 0.01289 -0.0267 1.0000 0.1274
-5.500 -0.5874 0.02208 0.01243 -0.0265 0.9999 0.1376
-5.250 -0.5531 0.02146 0.01191 -0.0287 0.9965 0.1528
-5.000 -0.5180 0.02081 0.01144 -0.0312 0.9934 0.1755
-4.750 -0.4834 0.02008 0.01095 -0.0336 0.9898 0.2116
-4.500 -0.4473 0.01910 0.01039 -0.0369 0.9866 0.2779
-4.250 -0.4097 0.01794 0.01004 -0.0405 0.9842 0.4055
-4.000 -0.3844 0.01850 0.01130 -0.0386 0.9799 0.5130
-3.750 -0.3545 0.01896 0.01182 -0.0384 0.9743 0.5627
-3.500 -0.3177 0.01923 0.01201 -0.0402 0.9703 0.5943
-3.250 -0.2840 0.01968 0.01240 -0.0410 0.9663 0.6148
-3.000 -0.2535 0.02006 0.01271 -0.0413 0.9605 0.6306
-2.750 -0.2181 0.02040 0.01298 -0.0427 0.9564 0.6458
-2.500 -0.1911 0.02109 0.01368 -0.0412 0.9517 0.6546
-2.250 -0.1641 0.02157 0.01414 -0.0405 0.9455 0.6670
-2.000 -0.1318 0.02211 0.01466 -0.0408 0.9412 0.6820
-1.750 -0.1089 0.02283 0.01543 -0.0381 0.9363 0.6888
-1.500 -0.0777 0.02288 0.01543 -0.0392 0.9303 0.6993
-1.250 -0.0460 0.02294 0.01549 -0.0397 0.9260 0.7029
-1.000 -0.0120 0.02302 0.01556 -0.0405 0.9229 0.7066
-0.750 0.0132 0.02306 0.01561 -0.0400 0.9151 0.7115
-0.500 0.0523 0.02284 0.01537 -0.0428 0.9103 0.7171
-0.250 0.0926 0.02260 0.01512 -0.0456 0.9067 0.7205
0.000 0.1191 0.02255 0.01511 -0.0451 0.8980 0.7227
0.250 0.1552 0.02231 0.01490 -0.0463 0.8908 0.7251
0.500 0.1879 0.02207 0.01468 -0.0469 0.8806 0.7280
0.750 0.2300 0.02156 0.01419 -0.0489 0.8702 0.7313
1.000 0.2667 0.02102 0.01365 -0.0502 0.8531 0.7349
1.250 0.3065 0.02040 0.01301 -0.0521 0.8335 0.7381
1.500 0.3352 0.02007 0.01270 -0.0514 0.8131 0.7396
1.750 0.3623 0.01983 0.01248 -0.0506 0.7902 0.7415
2.000 0.3900 0.01961 0.01227 -0.0499 0.7646 0.7438
2.250 0.4194 0.01939 0.01205 -0.0496 0.7361 0.7463
2.500 0.4486 0.01923 0.01185 -0.0495 0.6986 0.7487
2.750 0.4790 0.01911 0.01155 -0.0495 0.6367 0.7512
3.000 0.5070 0.01936 0.01121 -0.0491 0.5155 0.7539
3.250 0.5282 0.02019 0.01131 -0.0482 0.3894 0.7565
3.500 0.5467 0.02097 0.01164 -0.0466 0.3066 0.7584
3.750 0.5676 0.02163 0.01198 -0.0455 0.2469 0.7606
4.000 0.5905 0.02223 0.01233 -0.0449 0.2072 0.7629
4.250 0.6154 0.02274 0.01269 -0.0447 0.1803 0.7653
4.500 0.6412 0.02326 0.01309 -0.0447 0.1613 0.7681
4.750 0.6687 0.02377 0.01353 -0.0452 0.1468 0.7711
5.000 0.6956 0.02430 0.01400 -0.0454 0.1356 0.7737
5.250 0.7183 0.02483 0.01447 -0.0447 0.1268 0.7754
5.500 0.7423 0.02533 0.01501 -0.0441 0.1192 0.7773
5.750 0.7657 0.02593 0.01556 -0.0436 0.1127 0.7793
6.000 0.7908 0.02650 0.01617 -0.0433 0.1065 0.7816
6.250 0.8158 0.02712 0.01679 -0.0431 0.1013 0.7843
6.500 0.8421 0.02784 0.01752 -0.0433 0.0965 0.7873
6.750 0.8697 0.02854 0.01824 -0.0437 0.0917 0.7902
7.000 0.8915 0.02929 0.01894 -0.0429 0.0884 0.7921
7.250 0.9155 0.03002 0.01981 -0.0423 0.0846 0.7940
7.500 0.9393 0.03078 0.02061 -0.0419 0.0811 0.7962
7.750 0.9631 0.03165 0.02143 -0.0417 0.0785 0.7986
8.000 0.9883 0.03261 0.02256 -0.0415 0.0754 0.8011
8.250 1.0133 0.03356 0.02362 -0.0415 0.0724 0.8039
8.500 1.0390 0.03454 0.02460 -0.0418 0.0702 0.8070
8.750 1.0601 0.03562 0.02576 -0.0409 0.0683 0.8092
9.000 1.0807 0.03681 0.02721 -0.0400 0.0659 0.8117
9.250 1.1013 0.03789 0.02842 -0.0392 0.0638 0.8144
9.500 1.1223 0.03890 0.02947 -0.0387 0.0622 0.8170
9.750 1.1437 0.04024 0.03088 -0.0384 0.0608 0.8198
10.000 1.1622 0.04214 0.03313 -0.0377 0.0592 0.8226
10.250 1.1777 0.04385 0.03511 -0.0365 0.0576 0.8250
10.500 1.1913 0.04528 0.03673 -0.0350 0.0563 0.8274
10.750 1.2054 0.04654 0.03809 -0.0337 0.0552 0.8303
11.000 1.2206 0.04781 0.03937 -0.0327 0.0542 0.8335
11.250 1.2229 0.05040 0.04238 -0.0304 0.0531 0.8368
11.500 1.2198 0.05310 0.04547 -0.0278 0.0522 0.8401
11.750 1.2126 0.05582 0.04852 -0.0247 0.0516 0.8428
12.000 1.2036 0.05885 0.05186 -0.0223 0.0510 0.8457
12.250 1.1922 0.06221 0.05553 -0.0204 0.0505 0.8487
12.500 1.1781 0.06601 0.05961 -0.0193 0.0501 0.8517
12.750 1.1599 0.07058 0.06445 -0.0191 0.0498 0.8547
13.000 1.1343 0.07641 0.07059 -0.0203 0.0496 0.8571
13.250 1.0745 0.08808 0.08272 -0.0259 0.0498 0.8582
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