FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 200,000 Max Cl/Cd: 79.86 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k153-il-200000-n5.txt Download as CSV file: xf-fx62k153-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1808 0.08800 0.08399 -0.1129 0.9005 0.0107
-10.750 -0.1837 0.08209 0.07808 -0.1165 0.8949 0.0106
-10.500 -0.1901 0.07499 0.07097 -0.1212 0.8902 0.0105
-10.250 -0.2081 0.06373 0.05969 -0.1299 0.8844 0.0102
-10.000 -0.2354 0.05415 0.04991 -0.1374 0.8781 0.0099
-9.750 -0.2582 0.04761 0.04311 -0.1412 0.8720 0.0097
-9.500 -0.2758 0.04270 0.03792 -0.1427 0.8657 0.0097
-9.250 -0.2827 0.03836 0.03318 -0.1446 0.8612 0.0099
-9.000 -0.2807 0.03474 0.02917 -0.1452 0.8572 0.0103
-8.750 -0.2731 0.03127 0.02518 -0.1454 0.8534 0.0112
-8.500 -0.2589 0.02851 0.02192 -0.1455 0.8503 0.0122
-8.250 -0.2370 0.02761 0.02091 -0.1461 0.8478 0.0130
-8.000 -0.2149 0.02615 0.01919 -0.1464 0.8456 0.0139
-7.750 -0.1951 0.02450 0.01723 -0.1458 0.8427 0.0150
-7.500 -0.1734 0.02314 0.01557 -0.1453 0.8400 0.0163
-7.250 -0.1501 0.02245 0.01488 -0.1455 0.8374 0.0178
-7.000 -0.1253 0.02170 0.01399 -0.1456 0.8351 0.0196
-6.750 -0.0997 0.02089 0.01298 -0.1455 0.8331 0.0213
-6.500 -0.0750 0.01998 0.01205 -0.1456 0.8314 0.0233
-6.250 -0.0526 0.01937 0.01140 -0.1452 0.8288 0.0247
-6.000 -0.0297 0.01876 0.01074 -0.1448 0.8260 0.0263
-5.750 -0.0048 0.01827 0.01016 -0.1448 0.8234 0.0284
-5.500 0.0208 0.01757 0.00945 -0.1453 0.8212 0.0312
-5.250 0.0487 0.01706 0.00888 -0.1460 0.8193 0.0341
-5.000 0.0782 0.01660 0.00830 -0.1470 0.8175 0.0379
-4.750 0.1070 0.01612 0.00781 -0.1480 0.8155 0.0464
-4.500 0.1335 0.01575 0.00748 -0.1486 0.8128 0.0602
-4.250 0.1621 0.01532 0.00714 -0.1496 0.8102 0.0894
-4.000 0.1955 0.01438 0.00671 -0.1525 0.8080 0.2095
-3.750 0.2351 0.01306 0.00669 -0.1571 0.8062 0.5304
-3.500 0.2625 0.01329 0.00700 -0.1567 0.8043 0.5896
-3.250 0.2916 0.01354 0.00718 -0.1567 0.8026 0.6192
-3.000 0.3183 0.01397 0.00755 -0.1562 0.8003 0.6456
-2.750 0.3381 0.01458 0.00819 -0.1539 0.7970 0.6628
-2.500 0.3645 0.01482 0.00836 -0.1536 0.7942 0.6722
-2.250 0.3932 0.01487 0.00832 -0.1540 0.7918 0.6761
-2.000 0.4211 0.01495 0.00832 -0.1541 0.7897 0.6790
-1.750 0.4514 0.01497 0.00826 -0.1547 0.7879 0.6827
-1.500 0.4823 0.01499 0.00819 -0.1558 0.7856 0.6876
-1.250 0.5076 0.01510 0.00829 -0.1557 0.7820 0.6907
-1.000 0.5336 0.01520 0.00836 -0.1555 0.7790 0.6930
-0.750 0.5619 0.01524 0.00837 -0.1557 0.7764 0.6957
-0.500 0.5925 0.01524 0.00832 -0.1565 0.7742 0.6990
-0.250 0.6264 0.01519 0.00819 -0.1582 0.7723 0.7032
0.000 0.6501 0.01534 0.00836 -0.1577 0.7680 0.7057
0.250 0.6755 0.01542 0.00847 -0.1574 0.7643 0.7078
0.500 0.7038 0.01544 0.00849 -0.1577 0.7614 0.7101
0.750 0.7346 0.01542 0.00844 -0.1585 0.7589 0.7127
1.000 0.7641 0.01544 0.00846 -0.1592 0.7558 0.7158
1.250 0.7909 0.01554 0.00858 -0.1595 0.7507 0.7195
1.500 0.8182 0.01551 0.00858 -0.1595 0.7468 0.7211
1.750 0.8485 0.01544 0.00850 -0.1600 0.7438 0.7229
2.000 0.8724 0.01557 0.00871 -0.1596 0.7392 0.7252
2.250 0.8981 0.01566 0.00886 -0.1595 0.7348 0.7278
2.500 0.9280 0.01565 0.00887 -0.1601 0.7314 0.7305
2.750 0.9612 0.01558 0.00882 -0.1615 0.7287 0.7334
3.000 0.9826 0.01579 0.00913 -0.1606 0.7228 0.7355
3.250 1.0083 0.01584 0.00926 -0.1604 0.7185 0.7374
3.500 1.0383 0.01577 0.00923 -0.1609 0.7150 0.7394
3.750 1.0597 0.01586 0.00943 -0.1599 0.7067 0.7417
4.000 1.0897 0.01561 0.00920 -0.1603 0.6989 0.7443
4.250 1.1126 0.01565 0.00931 -0.1596 0.6885 0.7472
4.500 1.1383 0.01568 0.00943 -0.1594 0.6807 0.7496
4.750 1.1635 0.01567 0.00951 -0.1590 0.6728 0.7512
5.000 1.1854 0.01574 0.00967 -0.1580 0.6621 0.7531
5.250 1.2082 0.01572 0.00970 -0.1570 0.6479 0.7554
5.500 1.2316 0.01570 0.00969 -0.1562 0.6302 0.7580
5.750 1.2531 0.01577 0.00973 -0.1550 0.6066 0.7606
6.000 1.2738 0.01595 0.00981 -0.1537 0.5792 0.7631
6.250 1.2890 0.01625 0.01003 -0.1514 0.5513 0.7649
6.500 1.3008 0.01669 0.01041 -0.1485 0.5232 0.7670
6.750 1.3117 0.01730 0.01093 -0.1457 0.4937 0.7694
7.000 1.3211 0.01804 0.01158 -0.1427 0.4642 0.7720
7.250 1.3277 0.01897 0.01240 -0.1395 0.4316 0.7746
7.500 1.3299 0.02018 0.01344 -0.1359 0.3944 0.7772
7.750 1.3292 0.02160 0.01469 -0.1320 0.3522 0.7793
8.000 1.3247 0.02334 0.01621 -0.1279 0.3080 0.7815
8.250 1.3230 0.02509 0.01781 -0.1244 0.2701 0.7839
8.500 1.3228 0.02689 0.01943 -0.1214 0.2334 0.7863
8.750 1.3249 0.02865 0.02104 -0.1188 0.2013 0.7888
9.000 1.3290 0.03034 0.02260 -0.1166 0.1691 0.7911
9.250 1.3324 0.03211 0.02424 -0.1143 0.1441 0.7932
9.500 1.3384 0.03366 0.02576 -0.1123 0.1245 0.7952
9.750 1.3447 0.03522 0.02731 -0.1104 0.1091 0.7975
10.000 1.3516 0.03678 0.02887 -0.1087 0.0959 0.8000
10.250 1.3585 0.03839 0.03050 -0.1070 0.0837 0.8026
10.500 1.3655 0.04003 0.03215 -0.1055 0.0729 0.8050
11.000 1.3788 0.04342 0.03557 -0.1024 0.0562 0.8094
11.250 1.3863 0.04506 0.03729 -0.1010 0.0497 0.8117
11.500 1.3921 0.04689 0.03915 -0.0996 0.0443 0.8143
11.750 1.4000 0.04859 0.04096 -0.0984 0.0402 0.8172
12.000 1.4067 0.05045 0.04289 -0.0972 0.0359 0.8202
12.250 1.4128 0.05238 0.04491 -0.0960 0.0319 0.8229
12.500 1.4187 0.05429 0.04688 -0.0948 0.0275 0.8254
12.750 1.4237 0.05636 0.04902 -0.0937 0.0240 0.8281
13.000 1.4291 0.05843 0.05119 -0.0927 0.0211 0.8311
13.250 1.4321 0.06082 0.05363 -0.0917 0.0184 0.8342
13.500 1.4371 0.06303 0.05599 -0.0908 0.0159 0.8373
13.750 1.4380 0.06567 0.05870 -0.0897 0.0135 0.8405
14.000 1.4406 0.06820 0.06140 -0.0888 0.0115 0.8443
14.250 1.4408 0.07107 0.06436 -0.0880 0.0100 0.8482
14.500 1.4403 0.07410 0.06753 -0.0873 0.0089 0.8521
14.750 1.4394 0.07719 0.07078 -0.0867 0.0079 0.8563
15.000 1.4377 0.08047 0.07423 -0.0862 0.0074 0.8609
15.500 1.4308 0.08762 0.08168 -0.0857 0.0066 0.8714
15.750 1.4266 0.09138 0.08564 -0.0857 0.0064 0.8781
16.000 1.4214 0.09527 0.08972 -0.0857 0.0061 0.8865
16.250 1.4158 0.09917 0.09380 -0.0859 0.0059 0.8993
16.500 1.4065 0.10285 0.09767 -0.0854 0.0056 0.9460
16.750 1.4009 0.10709 0.10207 -0.0864 0.0055 0.9999
17.000 1.3958 0.11166 0.10679 -0.0878 0.0053 0.9999
17.250 1.3897 0.11649 0.11176 -0.0895 0.0051 0.9999
17.500 1.3826 0.12159 0.11700 -0.0914 0.0050 0.9999
17.750 1.3747 0.12696 0.12252 -0.0938 0.0049 0.9999
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