NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il) Reynolds number: 50,000 Max Cl/Cd: 22.43 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20714-il-50000-n5.txt Download as CSV file: xf-sc20714-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0714 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5760 0.10645 0.09762 -0.0476 1.0000 0.0854
-12.250 -0.6212 0.09333 0.08449 -0.0546 1.0000 0.0848
-12.000 -0.7088 0.07867 0.06965 -0.0618 1.0000 0.0827
-11.750 -0.7865 0.07065 0.06133 -0.0617 1.0000 0.0811
-11.500 -0.8120 0.06763 0.05822 -0.0592 1.0000 0.0813
-11.250 -0.8237 0.06492 0.05544 -0.0575 1.0000 0.0820
-11.000 -0.8309 0.06221 0.05263 -0.0562 1.0000 0.0828
-10.750 -0.8365 0.05940 0.04966 -0.0551 1.0000 0.0837
-10.500 -0.8388 0.05657 0.04663 -0.0540 1.0000 0.0847
-10.250 -0.8373 0.05382 0.04364 -0.0531 1.0000 0.0861
-10.000 -0.8329 0.05115 0.04066 -0.0524 1.0000 0.0881
-9.750 -0.8259 0.04838 0.03743 -0.0520 1.0000 0.0904
-9.500 -0.8118 0.04644 0.03539 -0.0512 1.0000 0.0926
-9.250 -0.7958 0.04487 0.03377 -0.0503 1.0000 0.0949
-9.000 -0.7792 0.04320 0.03194 -0.0495 1.0000 0.0977
-8.750 -0.7619 0.04152 0.02998 -0.0488 1.0000 0.1013
-8.500 -0.7434 0.04007 0.02842 -0.0479 1.0000 0.1046
-8.250 -0.7246 0.03896 0.02733 -0.0467 1.0000 0.1080
-8.000 -0.7052 0.03787 0.02614 -0.0455 1.0000 0.1123
-7.750 -0.6854 0.03684 0.02496 -0.0441 1.0000 0.1171
-7.500 -0.6666 0.03605 0.02427 -0.0424 1.0000 0.1216
-7.250 -0.6471 0.03533 0.02347 -0.0407 1.0000 0.1273
-7.000 -0.6281 0.03465 0.02280 -0.0389 1.0000 0.1335
-6.750 -0.6094 0.03399 0.02217 -0.0373 1.0000 0.1407
-6.500 -0.5906 0.03332 0.02151 -0.0357 1.0000 0.1487
-6.250 -0.5716 0.03262 0.02086 -0.0345 1.0000 0.1589
-6.000 -0.5521 0.03183 0.02021 -0.0337 1.0000 0.1710
-5.750 -0.5314 0.03097 0.01949 -0.0333 1.0000 0.1877
-5.500 -0.5088 0.02998 0.01871 -0.0337 1.0000 0.2120
-5.250 -0.4832 0.02866 0.01784 -0.0353 1.0000 0.2547
-5.000 -0.4573 0.02735 0.01747 -0.0367 1.0000 0.3515
-4.750 -0.4539 0.02836 0.01929 -0.0290 1.0000 0.4425
-4.500 -0.4487 0.03008 0.02126 -0.0211 1.0000 0.5013
-4.250 -0.4184 0.03045 0.02142 -0.0226 1.0000 0.5656
-4.000 -0.3928 0.03114 0.02194 -0.0224 1.0000 0.6020
-3.750 -0.3745 0.03197 0.02266 -0.0198 1.0000 0.6240
-3.500 -0.3567 0.03273 0.02333 -0.0171 1.0000 0.6441
-3.250 -0.3405 0.03343 0.02397 -0.0140 1.0000 0.6623
-3.000 -0.3259 0.03411 0.02460 -0.0105 1.0000 0.6801
-2.750 -0.3128 0.03474 0.02520 -0.0067 1.0000 0.6984
-2.500 -0.2995 0.03521 0.02564 -0.0030 1.0000 0.7161
-2.250 -0.2840 0.03550 0.02589 -0.0003 1.0000 0.7326
-2.000 -0.2643 0.03562 0.02595 0.0009 1.0000 0.7465
-1.750 -0.2475 0.03547 0.02576 0.0028 1.0000 0.7534
-1.500 -0.2245 0.03538 0.02562 0.0027 1.0000 0.7612
-1.250 -0.1935 0.03536 0.02554 0.0010 0.9968 0.7677
-1.000 -0.1602 0.03540 0.02553 -0.0006 0.9912 0.7733
-0.750 -0.1236 0.03547 0.02556 -0.0035 0.9851 0.7791
-0.500 -0.0848 0.03561 0.02565 -0.0068 0.9796 0.7839
-0.250 -0.0530 0.03557 0.02562 -0.0083 0.9720 0.7880
0.000 -0.0164 0.03566 0.02570 -0.0108 0.9650 0.7922
0.250 0.0226 0.03576 0.02582 -0.0141 0.9565 0.7964
0.500 0.0614 0.03585 0.02593 -0.0173 0.9472 0.8002
0.750 0.1000 0.03583 0.02597 -0.0197 0.9384 0.8034
1.000 0.1312 0.03575 0.02596 -0.0210 0.9270 0.8069
1.250 0.1688 0.03574 0.02603 -0.0235 0.9166 0.8103
1.500 0.2127 0.03570 0.02608 -0.0271 0.9061 0.8130
1.750 0.2523 0.03553 0.02601 -0.0298 0.8911 0.8154
2.000 0.2915 0.03507 0.02569 -0.0317 0.8743 0.8176
2.250 0.3356 0.03419 0.02494 -0.0336 0.8540 0.8198
2.500 0.3692 0.03329 0.02417 -0.0337 0.8268 0.8219
2.750 0.4095 0.03203 0.02307 -0.0343 0.7971 0.8236
3.000 0.4438 0.03095 0.02214 -0.0340 0.7649 0.8258
3.250 0.4718 0.03021 0.02154 -0.0331 0.7223 0.8283
3.500 0.5103 0.02914 0.02052 -0.0331 0.6600 0.8306
3.750 0.5807 0.02794 0.01835 -0.0367 0.4814 0.8320
4.000 0.5976 0.02895 0.01857 -0.0348 0.3604 0.8335
4.250 0.6120 0.03011 0.01915 -0.0331 0.2818 0.8352
4.500 0.6309 0.03117 0.01984 -0.0322 0.2331 0.8371
4.750 0.6535 0.03213 0.02056 -0.0320 0.2017 0.8394
5.000 0.6792 0.03307 0.02136 -0.0322 0.1805 0.8417
5.250 0.7087 0.03401 0.02221 -0.0330 0.1642 0.8440
5.500 0.7418 0.03496 0.02314 -0.0344 0.1513 0.8460
5.750 0.7771 0.03599 0.02411 -0.0361 0.1410 0.8477
6.000 0.8103 0.03691 0.02509 -0.0372 0.1325 0.8493
6.250 0.8432 0.03799 0.02617 -0.0383 0.1253 0.8511
6.500 0.8749 0.03910 0.02741 -0.0391 0.1188 0.8532
6.750 0.9068 0.04042 0.02862 -0.0403 0.1138 0.8556
7.000 0.9360 0.04182 0.03034 -0.0408 0.1082 0.8581
7.250 0.9649 0.04326 0.03188 -0.0416 0.1038 0.8606
7.500 0.9937 0.04497 0.03365 -0.0425 0.1000 0.8628
7.750 1.0148 0.04671 0.03577 -0.0419 0.0961 0.8648
8.000 1.0367 0.04846 0.03774 -0.0416 0.0929 0.8668
8.250 1.0597 0.05012 0.03943 -0.0417 0.0901 0.8688
8.500 1.0750 0.05248 0.04218 -0.0406 0.0875 0.8711
8.750 1.0864 0.05510 0.04526 -0.0392 0.0850 0.8735
9.000 1.0974 0.05783 0.04836 -0.0381 0.0832 0.8759
9.250 1.1074 0.06029 0.05108 -0.0368 0.0815 0.8784
9.500 1.1184 0.06238 0.05330 -0.0356 0.0799 0.8810
9.750 1.1235 0.06502 0.05613 -0.0340 0.0785 0.8835
10.000 1.1076 0.06872 0.06035 -0.0305 0.0775 0.8856
10.250 1.0878 0.07258 0.06462 -0.0274 0.0769 0.8877
10.500 1.0649 0.07717 0.06959 -0.0254 0.0764 0.8894
10.750 1.0374 0.08257 0.07534 -0.0246 0.0762 0.8908
11.000 1.0045 0.08919 0.08227 -0.0256 0.0763 0.8919
11.250 0.9643 0.09785 0.09121 -0.0292 0.0766 0.8927
11.500 0.9179 0.11013 0.10370 -0.0372 0.0773 0.8929
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Polar data table (+)
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