NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.32 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20414-il-1000000.txt Download as CSV file: xf-sc20414-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2655 0.09714 0.09353 -0.0314 1.0000 0.0229
-19.500 -1.2842 0.09055 0.08682 -0.0346 1.0000 0.0231
-19.250 -1.2994 0.08455 0.08071 -0.0376 1.0000 0.0233
-19.000 -1.3118 0.07906 0.07513 -0.0402 1.0000 0.0234
-18.750 -1.3219 0.07404 0.07001 -0.0425 1.0000 0.0236
-18.500 -1.3289 0.06955 0.06544 -0.0445 1.0000 0.0238
-18.250 -1.3334 0.06550 0.06130 -0.0462 1.0000 0.0240
-18.000 -1.3359 0.06186 0.05758 -0.0476 1.0000 0.0242
-17.750 -1.3363 0.05857 0.05422 -0.0488 1.0000 0.0244
-17.500 -1.3351 0.05555 0.05113 -0.0498 1.0000 0.0246
-17.250 -1.3329 0.05275 0.04826 -0.0506 1.0000 0.0248
-17.000 -1.3299 0.05014 0.04556 -0.0513 1.0000 0.0251
-16.750 -1.3261 0.04766 0.04301 -0.0518 1.0000 0.0253
-16.500 -1.3208 0.04542 0.04069 -0.0522 1.0000 0.0256
-16.250 -1.3149 0.04331 0.03851 -0.0524 1.0000 0.0258
-16.000 -1.3081 0.04134 0.03647 -0.0526 1.0000 0.0260
-15.750 -1.2994 0.03961 0.03466 -0.0526 1.0000 0.0263
-15.500 -1.2905 0.03796 0.03294 -0.0526 1.0000 0.0264
-15.250 -1.2833 0.03623 0.03114 -0.0524 1.0000 0.0267
-15.000 -1.2813 0.03407 0.02892 -0.0520 1.0000 0.0271
-14.750 -1.2745 0.03238 0.02718 -0.0517 1.0000 0.0275
-14.500 -1.2642 0.03099 0.02576 -0.0513 1.0000 0.0279
-14.250 -1.2526 0.02974 0.02448 -0.0510 1.0000 0.0283
-14.000 -1.2395 0.02863 0.02333 -0.0506 1.0000 0.0287
-13.750 -1.2262 0.02755 0.02221 -0.0502 1.0000 0.0291
-13.500 -1.2122 0.02655 0.02117 -0.0497 1.0000 0.0295
-13.250 -1.1977 0.02560 0.02018 -0.0492 1.0000 0.0300
-13.000 -1.1823 0.02477 0.01930 -0.0486 1.0000 0.0304
-12.750 -1.1664 0.02401 0.01849 -0.0480 1.0000 0.0307
-12.500 -1.1596 0.02271 0.01717 -0.0466 1.0000 0.0315
-12.250 -1.1501 0.02184 0.01629 -0.0450 1.0000 0.0321
-12.000 -1.1450 0.02112 0.01556 -0.0423 1.0000 0.0325
-11.750 -1.1368 0.02046 0.01488 -0.0401 1.0000 0.0330
-11.500 -1.1252 0.01983 0.01423 -0.0384 1.0000 0.0336
-11.250 -1.1120 0.01924 0.01361 -0.0370 1.0000 0.0342
-11.000 -1.0971 0.01869 0.01304 -0.0358 1.0000 0.0348
-10.750 -1.0804 0.01820 0.01251 -0.0348 1.0000 0.0352
-10.500 -1.0649 0.01732 0.01163 -0.0342 1.0000 0.0364
-10.250 -1.0325 0.01672 0.01103 -0.0362 0.9991 0.0375
-10.000 -0.9988 0.01624 0.01054 -0.0383 0.9979 0.0388
-9.750 -0.9645 0.01584 0.01011 -0.0403 0.9967 0.0399
-9.500 -0.9299 0.01516 0.00944 -0.0428 0.9954 0.0416
-9.250 -0.8950 0.01468 0.00898 -0.0450 0.9943 0.0432
-9.000 -0.8601 0.01431 0.00860 -0.0471 0.9934 0.0448
-8.750 -0.8253 0.01389 0.00816 -0.0491 0.9926 0.0464
-8.500 -0.7930 0.01342 0.00772 -0.0507 0.9905 0.0486
-8.250 -0.7592 0.01309 0.00740 -0.0524 0.9887 0.0506
-8.000 -0.7244 0.01275 0.00705 -0.0543 0.9870 0.0525
-7.750 -0.6889 0.01231 0.00665 -0.0564 0.9856 0.0553
-7.500 -0.6531 0.01200 0.00634 -0.0585 0.9844 0.0576
-7.250 -0.6169 0.01164 0.00599 -0.0606 0.9835 0.0604
-7.000 -0.5807 0.01128 0.00567 -0.0628 0.9826 0.0639
-6.750 -0.5448 0.01100 0.00539 -0.0648 0.9814 0.0670
-6.500 -0.5117 0.01064 0.00509 -0.0663 0.9786 0.0717
-6.250 -0.4789 0.01039 0.00484 -0.0676 0.9748 0.0757
-6.000 -0.4450 0.01005 0.00457 -0.0691 0.9716 0.0823
-5.750 -0.4111 0.00976 0.00432 -0.0707 0.9687 0.0898
-5.500 -0.3799 0.00950 0.00410 -0.0716 0.9636 0.0984
-5.250 -0.3485 0.00922 0.00387 -0.0725 0.9584 0.1092
-5.000 -0.3159 0.00888 0.00364 -0.0738 0.9540 0.1264
-4.750 -0.2850 0.00860 0.00344 -0.0746 0.9475 0.1456
-4.500 -0.2531 0.00826 0.00322 -0.0758 0.9416 0.1732
-4.250 -0.2203 0.00787 0.00300 -0.0772 0.9359 0.2157
-4.000 -0.1864 0.00736 0.00275 -0.0791 0.9292 0.2754
-3.750 -0.1507 0.00675 0.00245 -0.0814 0.9232 0.3600
-3.500 -0.1123 0.00600 0.00214 -0.0844 0.9171 0.4723
-3.250 -0.0785 0.00570 0.00206 -0.0859 0.9099 0.5444
-3.000 -0.0477 0.00565 0.00204 -0.0864 0.9021 0.5698
-2.750 -0.0175 0.00564 0.00203 -0.0867 0.8917 0.5853
-2.500 0.0123 0.00565 0.00202 -0.0868 0.8798 0.5967
-2.250 0.0419 0.00569 0.00201 -0.0869 0.8680 0.6057
-2.000 0.0720 0.00571 0.00200 -0.0872 0.8564 0.6128
-1.750 0.1017 0.00575 0.00202 -0.0873 0.8442 0.6188
-1.500 0.1314 0.00583 0.00202 -0.0874 0.8304 0.6250
-1.250 0.1611 0.00588 0.00204 -0.0876 0.8164 0.6313
-1.000 0.1909 0.00596 0.00210 -0.0877 0.8041 0.6368
-0.750 0.2206 0.00605 0.00213 -0.0879 0.7895 0.6418
-0.500 0.2505 0.00614 0.00216 -0.0880 0.7763 0.6466
-0.250 0.2798 0.00622 0.00224 -0.0881 0.7609 0.6518
0.000 0.3091 0.00633 0.00231 -0.0881 0.7436 0.6559
0.250 0.3385 0.00645 0.00235 -0.0882 0.7227 0.6592
0.500 0.3677 0.00660 0.00238 -0.0883 0.6908 0.6616
0.750 0.3962 0.00682 0.00242 -0.0883 0.6451 0.6640
1.000 0.4227 0.00723 0.00250 -0.0879 0.5575 0.6670
1.250 0.4477 0.00797 0.00273 -0.0875 0.4335 0.6692
1.500 0.4740 0.00854 0.00294 -0.0873 0.3453 0.6710
1.750 0.5013 0.00898 0.00311 -0.0873 0.2816 0.6728
2.000 0.5287 0.00940 0.00328 -0.0872 0.2250 0.6745
2.250 0.5565 0.00974 0.00344 -0.0873 0.1863 0.6762
2.500 0.5847 0.01005 0.00360 -0.0873 0.1571 0.6778
2.750 0.6131 0.01030 0.00374 -0.0874 0.1359 0.6793
3.000 0.6416 0.01055 0.00389 -0.0874 0.1198 0.6806
3.250 0.6702 0.01076 0.00404 -0.0875 0.1082 0.6819
3.500 0.6985 0.01095 0.00418 -0.0876 0.0983 0.6840
3.750 0.7268 0.01116 0.00435 -0.0876 0.0913 0.6858
4.000 0.7550 0.01135 0.00453 -0.0876 0.0856 0.6874
4.250 0.7830 0.01159 0.00473 -0.0875 0.0805 0.6890
4.500 0.8112 0.01180 0.00493 -0.0875 0.0762 0.6907
4.750 0.8392 0.01201 0.00513 -0.0874 0.0720 0.6925
5.000 0.8670 0.01226 0.00535 -0.0873 0.0680 0.6943
5.250 0.8950 0.01247 0.00555 -0.0872 0.0648 0.6962
5.500 0.9222 0.01278 0.00581 -0.0870 0.0611 0.6979
5.750 0.9502 0.01298 0.00602 -0.0870 0.0590 0.6994
6.000 0.9776 0.01322 0.00624 -0.0868 0.0564 0.7010
6.250 1.0045 0.01351 0.00653 -0.0866 0.0537 0.7033
6.500 1.0319 0.01372 0.00676 -0.0864 0.0519 0.7051
6.750 1.0587 0.01399 0.00703 -0.0862 0.0499 0.7069
7.000 1.0844 0.01440 0.00743 -0.0857 0.0477 0.7086
7.250 1.1114 0.01463 0.00769 -0.0855 0.0464 0.7104
7.500 1.1379 0.01491 0.00799 -0.0852 0.0449 0.7124
7.750 1.1636 0.01527 0.00833 -0.0848 0.0432 0.7145
8.000 1.1888 0.01569 0.00876 -0.0842 0.0417 0.7163
8.250 1.2150 0.01597 0.00906 -0.0839 0.0406 0.7178
8.500 1.2407 0.01630 0.00940 -0.0834 0.0394 0.7191
8.750 1.2657 0.01666 0.00977 -0.0829 0.0382 0.7215
9.000 1.2886 0.01724 0.01036 -0.0821 0.0368 0.7236
9.250 1.3137 0.01754 0.01072 -0.0815 0.0362 0.7255
9.500 1.3382 0.01790 0.01111 -0.0809 0.0354 0.7274
9.750 1.3624 0.01827 0.01152 -0.0802 0.0345 0.7293
10.000 1.3859 0.01868 0.01194 -0.0795 0.0337 0.7313
10.250 1.4075 0.01927 0.01253 -0.0785 0.0327 0.7333
10.500 1.4287 0.01986 0.01317 -0.0773 0.0320 0.7352
10.750 1.4514 0.02028 0.01364 -0.0765 0.0315 0.7370
11.000 1.4733 0.02074 0.01414 -0.0755 0.0310 0.7389
11.250 1.4946 0.02120 0.01466 -0.0744 0.0304 0.7415
11.500 1.5151 0.02170 0.01520 -0.0732 0.0299 0.7437
11.750 1.5344 0.02225 0.01579 -0.0718 0.0294 0.7458
12.000 1.5516 0.02290 0.01648 -0.0701 0.0288 0.7479
12.250 1.5641 0.02379 0.01741 -0.0678 0.0283 0.7501
12.500 1.5738 0.02463 0.01832 -0.0649 0.0279 0.7523
12.750 1.5870 0.02525 0.01901 -0.0625 0.0276 0.7543
13.000 1.6010 0.02595 0.01978 -0.0605 0.0273 0.7561
13.250 1.6145 0.02670 0.02060 -0.0585 0.0270 0.7588
13.500 1.6275 0.02749 0.02148 -0.0565 0.0267 0.7612
13.750 1.6398 0.02835 0.02241 -0.0546 0.0263 0.7636
14.000 1.6518 0.02926 0.02338 -0.0527 0.0259 0.7660
14.250 1.6625 0.03029 0.02447 -0.0508 0.0256 0.7684
14.500 1.6719 0.03144 0.02569 -0.0489 0.0253 0.7708
14.750 1.6798 0.03276 0.02706 -0.0470 0.0251 0.7729
15.000 1.6847 0.03434 0.02872 -0.0450 0.0248 0.7758
15.250 1.6855 0.03635 0.03082 -0.0430 0.0245 0.7784
15.500 1.6806 0.03894 0.03354 -0.0408 0.0241 0.7810
15.750 1.6849 0.04083 0.03554 -0.0395 0.0240 0.7837
16.000 1.6899 0.04274 0.03755 -0.0384 0.0239 0.7864
16.250 1.6929 0.04491 0.03982 -0.0375 0.0237 0.7888
16.500 1.6946 0.04729 0.04231 -0.0367 0.0236 0.7912
16.750 1.6946 0.04995 0.04509 -0.0361 0.0234 0.7939
17.000 1.6928 0.05291 0.04818 -0.0358 0.0233 0.7964
17.250 1.6891 0.05621 0.05160 -0.0358 0.0231 0.7989
17.500 1.6835 0.05994 0.05546 -0.0361 0.0230 0.8013
17.750 1.6764 0.06410 0.05974 -0.0370 0.0228 0.8037
18.000 1.6670 0.06880 0.06456 -0.0383 0.0227 0.8058
18.250 1.6554 0.07408 0.06998 -0.0401 0.0226 0.8078
18.500 1.6403 0.08019 0.07625 -0.0427 0.0225 0.8101
18.750 1.6230 0.08696 0.08317 -0.0459 0.0224 0.8121
19.000 1.6016 0.09459 0.09096 -0.0498 0.0223 0.8138
19.250 1.5761 0.10317 0.09971 -0.0544 0.0223 0.8154
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0414 AIRFOIL (sc20414-il)