FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 200,000 Max Cl/Cd: 77.46 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k153-il-200000.txt Download as CSV file: xf-fx62k153-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 62-K-153/20 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1632 0.09673 0.09316 -0.1093 0.9614 0.0443
-10.250 -0.1590 0.09217 0.08861 -0.1133 0.9566 0.0462
-10.000 -0.1611 0.08466 0.08111 -0.1237 0.9517 0.0486
-9.750 -0.1686 0.07593 0.07229 -0.1367 0.9476 0.0491
-9.500 -0.1837 0.07197 0.06823 -0.1404 0.9392 0.0492
-9.250 -0.1941 0.06799 0.06408 -0.1455 0.9334 0.0493
-9.000 -0.2095 0.06596 0.06192 -0.1455 0.9248 0.0494
-8.750 -0.2065 0.05820 0.05426 -0.1473 0.9222 0.0510
-8.500 -0.1903 0.05512 0.05119 -0.1488 0.9200 0.0526
-8.250 -0.1953 0.05328 0.04929 -0.1474 0.9134 0.0537
-8.000 -0.1939 0.05089 0.04675 -0.1474 0.9086 0.0557
-7.500 -0.2069 0.04672 0.04186 -0.1450 0.8961 0.0640
-7.250 -0.1863 0.04420 0.03951 -0.1455 0.8941 0.0680
-7.000 -0.1681 0.03427 0.02828 -0.1453 0.8912 0.0354
-6.750 -0.1738 0.03299 0.02677 -0.1402 0.8841 0.0344
-6.500 -0.1548 0.03039 0.02377 -0.1394 0.8808 0.0341
-6.250 -0.1225 0.02921 0.02218 -0.1406 0.8790 0.0375
-6.000 -0.0906 0.02645 0.01908 -0.1416 0.8777 0.0393
-5.750 -0.0579 0.02520 0.01783 -0.1431 0.8765 0.0435
-5.500 -0.0627 0.02546 0.01805 -0.1376 0.8695 0.0444
-5.250 -0.0390 0.02464 0.01712 -0.1369 0.8664 0.0464
-5.000 -0.0072 0.02403 0.01638 -0.1377 0.8646 0.0494
-4.750 0.0241 0.02263 0.01507 -0.1388 0.8633 0.0547
-4.500 0.0609 0.02183 0.01422 -0.1409 0.8622 0.0614
-4.250 0.1023 0.02065 0.01311 -0.1446 0.8612 0.0805
-4.000 0.1644 0.01771 0.01240 -0.1551 0.8611 0.5747
-3.750 0.1648 0.01900 0.01373 -0.1503 0.8530 0.6166
-3.500 0.1864 0.01982 0.01449 -0.1480 0.8501 0.6484
-3.250 0.2090 0.02058 0.01520 -0.1456 0.8481 0.6672
-3.000 0.2339 0.02121 0.01576 -0.1435 0.8466 0.6814
-2.750 0.2277 0.02254 0.01710 -0.1379 0.8372 0.6916
-2.500 0.2446 0.02329 0.01782 -0.1342 0.8345 0.7062
-2.250 0.2598 0.02402 0.01856 -0.1293 0.8326 0.7215
-2.000 0.2442 0.02532 0.01991 -0.1214 0.8225 0.7293
-1.750 0.2706 0.02544 0.01994 -0.1206 0.8202 0.7382
-1.500 0.3064 0.02526 0.01967 -0.1219 0.8188 0.7430
-1.250 0.3522 0.02495 0.01921 -0.1261 0.8179 0.7495
-1.000 0.3422 0.02593 0.02023 -0.1198 0.8077 0.7530
-0.750 0.3755 0.02577 0.02001 -0.1209 0.8056 0.7572
-0.500 0.4214 0.02548 0.01962 -0.1249 0.8045 0.7626
-0.250 0.4576 0.02515 0.01923 -0.1263 0.8033 0.7657
0.000 0.4538 0.02611 0.02022 -0.1215 0.7931 0.7694
0.250 0.4906 0.02588 0.01995 -0.1234 0.7911 0.7732
0.500 0.5376 0.02552 0.01952 -0.1276 0.7899 0.7776
0.750 0.5742 0.02507 0.01905 -0.1290 0.7887 0.7802
1.000 0.6119 0.02460 0.01856 -0.1304 0.7877 0.7829
1.250 0.6146 0.02548 0.01948 -0.1270 0.7766 0.7869
1.500 0.6576 0.02504 0.01901 -0.1301 0.7753 0.7904
1.750 0.7000 0.02461 0.01857 -0.1330 0.7741 0.7936
2.000 0.7352 0.02420 0.01817 -0.1341 0.7729 0.7959
2.250 0.7369 0.02516 0.01920 -0.1305 0.7620 0.7990
2.500 0.7763 0.02472 0.01878 -0.1326 0.7605 0.8021
2.750 0.8197 0.02427 0.01834 -0.1357 0.7593 0.8054
3.000 0.8617 0.02385 0.01794 -0.1385 0.7581 0.8080
3.250 0.8629 0.02473 0.01891 -0.1346 0.7474 0.8106
3.500 0.9007 0.02419 0.01843 -0.1361 0.7457 0.8133
3.750 0.9437 0.02343 0.01770 -0.1386 0.7442 0.8161
4.000 0.9639 0.02354 0.01789 -0.1378 0.7348 0.8192
4.250 1.0148 0.02233 0.01672 -0.1415 0.7319 0.8219
4.500 1.0561 0.02133 0.01576 -0.1433 0.7295 0.8241
4.750 1.0684 0.02163 0.01618 -0.1409 0.7204 0.8270
5.000 1.1071 0.02098 0.01561 -0.1427 0.7169 0.8295
5.250 1.1409 0.02048 0.01519 -0.1437 0.7109 0.8323
5.500 1.1763 0.01977 0.01456 -0.1450 0.7027 0.8354
5.750 1.2023 0.01921 0.01409 -0.1443 0.6925 0.8381
6.000 1.2328 0.01841 0.01336 -0.1443 0.6821 0.8405
6.250 1.2612 0.01782 0.01283 -0.1440 0.6702 0.8431
6.500 1.2855 0.01754 0.01264 -0.1433 0.6565 0.8461
6.750 1.3073 0.01747 0.01265 -0.1423 0.6406 0.8495
7.000 1.3264 0.01744 0.01270 -0.1408 0.6234 0.8523
7.250 1.3430 0.01741 0.01270 -0.1386 0.6032 0.8549
7.500 1.3586 0.01754 0.01280 -0.1363 0.5766 0.8578
7.750 1.3727 0.01792 0.01309 -0.1340 0.5430 0.8611
8.000 1.3822 0.01864 0.01366 -0.1312 0.5035 0.8646
8.250 1.3844 0.01959 0.01444 -0.1272 0.4641 0.8677
8.500 1.3832 0.02082 0.01551 -0.1231 0.4235 0.8708
8.750 1.3801 0.02239 0.01688 -0.1191 0.3808 0.8741
9.000 1.3752 0.02430 0.01858 -0.1154 0.3328 0.8774
9.500 1.3620 0.02860 0.02244 -0.1081 0.2485 0.8840
9.750 1.3570 0.03085 0.02449 -0.1049 0.2093 0.8874
10.000 1.3533 0.03320 0.02662 -0.1022 0.1707 0.8907
10.250 1.3507 0.03561 0.02886 -0.0998 0.1423 0.8938
10.500 1.3497 0.03771 0.03087 -0.0974 0.1215 0.8970
10.750 1.3495 0.03984 0.03293 -0.0951 0.1061 0.9009
11.000 1.3515 0.04193 0.03500 -0.0933 0.0930 0.9051
11.250 1.3557 0.04391 0.03699 -0.0917 0.0818 0.9092
11.500 1.3581 0.04589 0.03902 -0.0898 0.0733 0.9136
11.750 1.3580 0.04825 0.04135 -0.0880 0.0665 0.9182
12.000 1.3654 0.05001 0.04324 -0.0868 0.0605 0.9234
12.250 1.3660 0.05219 0.04543 -0.0850 0.0556 0.9297
12.500 1.3714 0.05399 0.04736 -0.0837 0.0507 0.9380
12.750 1.3747 0.05574 0.04922 -0.0822 0.0460 0.9520
13.000 1.3714 0.05803 0.05156 -0.0803 0.0426 0.9999
13.250 1.3837 0.06004 0.05371 -0.0806 0.0370 0.9999
13.500 1.3846 0.06314 0.05685 -0.0802 0.0325 0.9999
13.750 1.3871 0.06622 0.05999 -0.0801 0.0264 0.9999
14.000 1.3842 0.06984 0.06372 -0.0794 0.0220 0.9999
14.250 1.3815 0.07348 0.06740 -0.0791 0.0196 0.9999
14.500 1.3776 0.07717 0.07119 -0.0783 0.0179 0.9999
14.750 1.3796 0.08033 0.07451 -0.0780 0.0165 0.9999
15.000 1.3809 0.08352 0.07781 -0.0778 0.0156 0.9999
15.250 1.3819 0.08677 0.08115 -0.0778 0.0148 0.9999
15.500 1.3819 0.09008 0.08452 -0.0776 0.0142 0.9999
15.750 1.3813 0.09323 0.08779 -0.0766 0.0135 0.9999
16.000 1.3807 0.09700 0.09180 -0.0773 0.0130 0.9999
16.250 1.3793 0.10086 0.09586 -0.0779 0.0125 0.9999
16.500 1.3765 0.10493 0.10013 -0.0787 0.0120 0.9999
16.750 1.3736 0.10909 0.10446 -0.0798 0.0117 0.9999
17.000 1.3692 0.11356 0.10911 -0.0813 0.0113 0.9999
17.250 1.3639 0.11828 0.11400 -0.0830 0.0110 0.9999
17.500 1.3571 0.12332 0.11924 -0.0849 0.0109 0.9999
17.750 1.3491 0.12871 0.12482 -0.0873 0.0108 0.9999
18.000 1.3396 0.13459 0.13090 -0.0902 0.0107 0.9999
18.250 1.3287 0.14097 0.13750 -0.0937 0.0107 0.9999
18.500 1.3162 0.14800 0.14473 -0.0979 0.0107 0.9999
18.750 1.2994 0.15644 0.15343 -0.1033 0.0108 0.9999
19.000 1.2817 0.16563 0.16286 -0.1097 0.0109 0.9999
19.250 1.2509 0.17960 0.17717 -0.1198 0.0114 0.9999
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