FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.5 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63100-il-1000000.txt Download as CSV file: xf-fx63100-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-100 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2830 0.10443 0.10288 -0.0344 1.0000 0.0142
-10.500 -0.2827 0.10133 0.09979 -0.0345 1.0000 0.0145
-10.250 -0.6389 0.02909 0.02666 -0.1010 0.9928 0.0098
-10.000 -0.6066 0.02454 0.02166 -0.1088 0.9898 0.0100
-9.750 -0.5721 0.02206 0.01888 -0.1134 0.9879 0.0101
-9.500 -0.5364 0.01788 0.01417 -0.1196 0.9865 0.0107
-9.250 -0.5008 0.01694 0.01314 -0.1222 0.9855 0.0111
-9.000 -0.4649 0.01631 0.01245 -0.1245 0.9846 0.0116
-8.750 -0.4340 0.01552 0.01155 -0.1257 0.9813 0.0121
-8.500 -0.4008 0.01470 0.01060 -0.1274 0.9785 0.0126
-8.250 -0.3659 0.01391 0.00968 -0.1293 0.9764 0.0130
-8.000 -0.3297 0.01266 0.00825 -0.1319 0.9748 0.0136
-7.750 -0.2933 0.01194 0.00747 -0.1341 0.9733 0.0143
-7.500 -0.2634 0.01151 0.00702 -0.1346 0.9680 0.0151
-7.250 -0.2305 0.01107 0.00651 -0.1358 0.9637 0.0159
-7.000 -0.1954 0.01068 0.00606 -0.1374 0.9606 0.0166
-6.750 -0.1632 0.00995 0.00529 -0.1386 0.9531 0.0181
-6.500 -0.1261 0.00972 0.00505 -0.1406 0.9483 0.0195
-6.250 -0.0891 0.00951 0.00479 -0.1425 0.9414 0.0208
-6.000 -0.0497 0.00891 0.00415 -0.1452 0.9336 0.0230
-5.750 -0.0129 0.00870 0.00388 -0.1471 0.9224 0.0248
-5.500 0.0207 0.00860 0.00371 -0.1482 0.9094 0.0261
-5.250 0.0524 0.00817 0.00321 -0.1491 0.8965 0.0291
-5.000 0.0819 0.00807 0.00303 -0.1494 0.8839 0.0311
-4.750 0.1105 0.00802 0.00289 -0.1494 0.8710 0.0324
-4.500 0.1396 0.00768 0.00246 -0.1497 0.8578 0.0356
-4.250 0.1680 0.00756 0.00230 -0.1498 0.8457 0.0380
-4.000 0.1965 0.00747 0.00215 -0.1498 0.8357 0.0400
-3.750 0.2255 0.00729 0.00189 -0.1500 0.8263 0.0435
-3.500 0.2544 0.00716 0.00175 -0.1502 0.8172 0.0478
-3.250 0.2833 0.00704 0.00159 -0.1503 0.8085 0.0543
-3.000 0.3124 0.00689 0.00148 -0.1505 0.7996 0.0709
-2.750 0.3413 0.00677 0.00139 -0.1507 0.7912 0.0940
-2.500 0.3702 0.00667 0.00131 -0.1508 0.7823 0.1133
-2.250 0.3996 0.00649 0.00122 -0.1512 0.7740 0.1521
-2.000 0.4304 0.00603 0.00114 -0.1522 0.7654 0.3007
-1.750 0.4595 0.00593 0.00113 -0.1525 0.7569 0.3498
-1.500 0.4881 0.00590 0.00112 -0.1525 0.7484 0.3799
-1.250 0.5170 0.00584 0.00111 -0.1527 0.7398 0.4051
-1.000 0.5458 0.00578 0.00112 -0.1528 0.7312 0.4452
-0.750 0.5751 0.00566 0.00117 -0.1531 0.7223 0.5138
-0.500 0.6036 0.00567 0.00122 -0.1532 0.7137 0.5527
-0.250 0.6318 0.00571 0.00126 -0.1531 0.7042 0.5732
0.000 0.6600 0.00576 0.00129 -0.1530 0.6934 0.5877
0.250 0.6878 0.00582 0.00133 -0.1529 0.6798 0.6034
0.500 0.7155 0.00591 0.00137 -0.1527 0.6653 0.6164
0.750 0.7432 0.00598 0.00142 -0.1525 0.6520 0.6258
1.000 0.7709 0.00606 0.00148 -0.1524 0.6400 0.6374
1.250 0.7986 0.00615 0.00154 -0.1522 0.6264 0.6491
1.750 0.8536 0.00635 0.00169 -0.1519 0.5958 0.6654
2.000 0.8809 0.00647 0.00177 -0.1517 0.5782 0.6739
2.250 0.9077 0.00665 0.00186 -0.1514 0.5520 0.6818
2.500 0.9339 0.00687 0.00199 -0.1510 0.5209 0.6904
2.750 0.9600 0.00712 0.00213 -0.1506 0.4906 0.6989
3.000 0.9864 0.00735 0.00228 -0.1503 0.4647 0.7087
3.250 1.0125 0.00761 0.00245 -0.1499 0.4386 0.7192
3.500 1.0386 0.00786 0.00264 -0.1496 0.4140 0.7304
3.750 1.0649 0.00810 0.00282 -0.1493 0.3916 0.7424
4.000 1.0907 0.00839 0.00303 -0.1489 0.3644 0.7555
4.250 1.1158 0.00874 0.00327 -0.1484 0.3285 0.7712
4.500 1.1398 0.00921 0.00357 -0.1478 0.2841 0.7896
4.750 1.1631 0.00974 0.00393 -0.1471 0.2391 0.8109
5.000 1.1866 0.01017 0.00427 -0.1463 0.2059 0.8402
5.250 1.2073 0.01044 0.00458 -0.1449 0.1810 0.9041
5.500 1.2270 0.01076 0.00485 -0.1432 0.1563 1.0000
5.750 1.2508 0.01132 0.00523 -0.1426 0.1241 1.0000
6.000 1.2731 0.01204 0.00572 -0.1418 0.0891 1.0000
6.250 1.2969 0.01257 0.00615 -0.1412 0.0712 1.0000
6.500 1.3202 0.01314 0.00661 -0.1405 0.0541 1.0000
6.750 1.3439 0.01364 0.00705 -0.1398 0.0438 1.0000
7.000 1.3681 0.01407 0.00746 -0.1393 0.0402 1.0000
7.250 1.3916 0.01457 0.00795 -0.1385 0.0367 1.0000
7.500 1.4156 0.01499 0.00840 -0.1379 0.0351 1.0000
7.750 1.4396 0.01538 0.00883 -0.1373 0.0339 1.0000
8.000 1.4629 0.01583 0.00931 -0.1366 0.0325 1.0000
8.250 1.4853 0.01636 0.00984 -0.1358 0.0309 1.0000
8.500 1.5060 0.01704 0.01057 -0.1346 0.0291 1.0000
8.750 1.5275 0.01761 0.01119 -0.1337 0.0281 1.0000
9.000 1.5504 0.01799 0.01161 -0.1329 0.0273 1.0000
9.250 1.5722 0.01846 0.01212 -0.1320 0.0263 1.0000
9.500 1.5933 0.01896 0.01265 -0.1311 0.0252 1.0000
9.750 1.6130 0.01957 0.01328 -0.1299 0.0239 1.0000
10.000 1.6273 0.02060 0.01438 -0.1278 0.0222 1.0000
10.250 1.6496 0.02089 0.01470 -0.1270 0.0216 1.0000
10.500 1.6699 0.02131 0.01516 -0.1260 0.0205 1.0000
10.750 1.6882 0.02179 0.01567 -0.1246 0.0194 1.0000
11.000 1.7018 0.02246 0.01634 -0.1224 0.0183 1.0000
11.250 1.7118 0.02334 0.01728 -0.1196 0.0172 1.0000
11.500 1.7268 0.02391 0.01791 -0.1178 0.0164 1.0000
11.750 1.7409 0.02455 0.01859 -0.1159 0.0154 1.0000
12.000 1.7528 0.02538 0.01943 -0.1138 0.0144 1.0000
12.250 1.7594 0.02663 0.02074 -0.1111 0.0134 1.0000
12.500 1.7710 0.02754 0.02172 -0.1092 0.0128 1.0000
12.750 1.7810 0.02861 0.02285 -0.1072 0.0121 1.0000
13.000 1.7892 0.02988 0.02417 -0.1052 0.0115 1.0000
13.250 1.7938 0.03150 0.02584 -0.1030 0.0109 1.0000
13.500 1.7941 0.03361 0.02806 -0.1007 0.0103 1.0000
13.750 1.8010 0.03520 0.02975 -0.0991 0.0101 1.0000
14.000 1.8062 0.03702 0.03167 -0.0976 0.0097 1.0000
14.250 1.8106 0.03900 0.03374 -0.0962 0.0094 1.0000
14.500 1.8135 0.04121 0.03605 -0.0950 0.0091 1.0000
14.750 1.8151 0.04366 0.03859 -0.0939 0.0089 1.0000
15.000 1.8149 0.04642 0.04144 -0.0930 0.0086 1.0000
15.250 1.8113 0.04972 0.04484 -0.0923 0.0083 1.0000
15.500 1.8008 0.05404 0.04930 -0.0918 0.0080 1.0000
15.750 1.7907 0.05858 0.05399 -0.0918 0.0078 1.0000
16.000 1.7892 0.06214 0.05767 -0.0920 0.0077 1.0000
16.250 1.7886 0.06565 0.06130 -0.0924 0.0076 1.0000
16.500 1.7822 0.07020 0.06598 -0.0932 0.0074 1.0000
16.750 1.7758 0.07494 0.07086 -0.0943 0.0073 1.0000
17.000 1.7678 0.08011 0.07616 -0.0958 0.0072 1.0000
17.250 1.7590 0.08561 0.08179 -0.0976 0.0071 1.0000
17.500 1.7493 0.09147 0.08778 -0.0997 0.0069 1.0000
17.750 1.7373 0.09795 0.09439 -0.1023 0.0068 1.0000
18.000 1.7246 0.10471 0.10129 -0.1053 0.0068 1.0000
18.250 1.7104 0.11193 0.10865 -0.1087 0.0067 1.0000
18.500 1.6937 0.11982 0.11669 -0.1127 0.0067 1.0000
18.750 1.6791 0.12741 0.12442 -0.1167 0.0066 1.0000
19.000 1.6612 0.13583 0.13299 -0.1215 0.0065 1.0000
19.250 1.6458 0.14390 0.14119 -0.1262 0.0065 1.0000
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