FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 200,000 Max Cl/Cd: 90.01 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63100-il-200000-n5.txt Download as CSV file: xf-fx63100-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3464 0.09319 0.08964 -0.0394 1.0000 0.0178
-8.750 -0.3513 0.08989 0.08640 -0.0395 1.0000 0.0179
-8.500 -0.3583 0.08692 0.08349 -0.0389 1.0000 0.0178
-8.250 -0.3608 0.08293 0.07957 -0.0407 0.9984 0.0178
-8.000 -0.3502 0.07680 0.07345 -0.0478 0.9918 0.0177
-7.750 -0.3410 0.06970 0.06638 -0.0565 0.9816 0.0177
-7.500 -0.3268 0.05817 0.05485 -0.0733 0.9687 0.0177
-7.250 -0.2925 0.02852 0.02358 -0.1155 0.9529 0.0182
-7.000 -0.2579 0.02449 0.01889 -0.1204 0.9469 0.0200
-6.750 -0.2228 0.02346 0.01773 -0.1229 0.9432 0.0212
-6.500 -0.1883 0.02166 0.01560 -0.1254 0.9385 0.0228
-6.250 -0.1535 0.01979 0.01334 -0.1277 0.9333 0.0247
-6.000 -0.1165 0.01843 0.01174 -0.1302 0.9298 0.0273
-5.750 -0.0795 0.01774 0.01097 -0.1325 0.9262 0.0299
-5.500 -0.0457 0.01682 0.00987 -0.1339 0.9199 0.0327
-5.250 -0.0087 0.01586 0.00874 -0.1360 0.9156 0.0362
-5.000 0.0291 0.01509 0.00790 -0.1383 0.9118 0.0398
-4.750 0.0626 0.01460 0.00732 -0.1396 0.9049 0.0439
-4.500 0.0993 0.01403 0.00662 -0.1414 0.8997 0.0470
-4.000 0.1696 0.01289 0.00540 -0.1447 0.8865 0.0554
-3.750 0.2051 0.01249 0.00490 -0.1463 0.8802 0.0600
-3.500 0.2375 0.01214 0.00454 -0.1474 0.8718 0.0674
-3.250 0.2713 0.01183 0.00419 -0.1486 0.8647 0.0778
-3.000 0.3024 0.01158 0.00392 -0.1493 0.8555 0.0930
-2.750 0.3340 0.01133 0.00365 -0.1500 0.8457 0.1140
-2.500 0.3659 0.01098 0.00339 -0.1510 0.8356 0.1583
-2.250 0.3974 0.01040 0.00333 -0.1523 0.8249 0.3221
-2.000 0.4275 0.01023 0.00329 -0.1527 0.8160 0.3928
-1.750 0.4569 0.01008 0.00331 -0.1530 0.8071 0.4533
-1.500 0.4854 0.01003 0.00340 -0.1530 0.7983 0.5076
-1.250 0.5141 0.01005 0.00341 -0.1529 0.7900 0.5422
-1.000 0.5421 0.01009 0.00346 -0.1527 0.7808 0.5711
-0.750 0.5707 0.01014 0.00346 -0.1526 0.7727 0.5942
-0.500 0.5982 0.01018 0.00351 -0.1524 0.7633 0.6148
-0.250 0.6259 0.01023 0.00356 -0.1521 0.7548 0.6350
0.000 0.6535 0.01028 0.00360 -0.1518 0.7457 0.6526
0.250 0.6810 0.01033 0.00366 -0.1516 0.7365 0.6657
0.750 0.7361 0.01047 0.00377 -0.1511 0.7177 0.6898
1.000 0.7635 0.01054 0.00384 -0.1508 0.7084 0.7020
1.250 0.7907 0.01061 0.00391 -0.1504 0.6984 0.7135
1.500 0.8177 0.01069 0.00401 -0.1501 0.6877 0.7249
1.750 0.8446 0.01077 0.00410 -0.1497 0.6759 0.7371
2.000 0.8708 0.01087 0.00417 -0.1492 0.6600 0.7500
2.250 0.8964 0.01097 0.00426 -0.1485 0.6417 0.7629
2.500 0.9220 0.01108 0.00436 -0.1478 0.6250 0.7766
2.750 0.9477 0.01119 0.00449 -0.1472 0.6103 0.7917
3.000 0.9728 0.01131 0.00464 -0.1465 0.5952 0.8088
3.250 0.9965 0.01142 0.00478 -0.1454 0.5791 0.8307
3.500 1.0175 0.01151 0.00489 -0.1437 0.5597 0.8643
3.750 1.0351 0.01150 0.00492 -0.1412 0.5353 1.0000
4.000 1.0603 0.01184 0.00512 -0.1407 0.5040 1.0000
4.250 1.0847 0.01225 0.00536 -0.1401 0.4719 1.0000
4.750 1.1318 0.01321 0.00601 -0.1387 0.4070 1.0000
5.000 1.1552 0.01371 0.00638 -0.1380 0.3753 1.0000
5.250 1.1779 0.01427 0.00679 -0.1372 0.3385 1.0000
5.500 1.1997 0.01490 0.00727 -0.1363 0.3000 1.0000
5.750 1.2209 0.01561 0.00779 -0.1354 0.2617 1.0000
6.000 1.2413 0.01639 0.00838 -0.1344 0.2259 1.0000
6.250 1.2622 0.01713 0.00900 -0.1334 0.1977 1.0000
6.750 1.3026 0.01872 0.01035 -0.1313 0.1420 1.0000
7.000 1.3216 0.01960 0.01109 -0.1301 0.1138 1.0000
7.250 1.3403 0.02048 0.01188 -0.1289 0.0941 1.0000
7.500 1.3590 0.02133 0.01270 -0.1276 0.0819 1.0000
7.750 1.3772 0.02219 0.01358 -0.1263 0.0730 1.0000
8.000 1.3949 0.02305 0.01447 -0.1248 0.0660 1.0000
8.250 1.4116 0.02395 0.01543 -0.1233 0.0612 1.0000
8.500 1.4283 0.02480 0.01636 -0.1217 0.0573 1.0000
8.750 1.4420 0.02574 0.01735 -0.1196 0.0540 1.0000
9.000 1.4525 0.02684 0.01849 -0.1172 0.0514 1.0000
9.250 1.4653 0.02779 0.01958 -0.1151 0.0495 1.0000
9.500 1.4769 0.02883 0.02074 -0.1129 0.0477 1.0000
9.750 1.4881 0.02992 0.02192 -0.1109 0.0457 1.0000
10.000 1.4978 0.03115 0.02320 -0.1088 0.0435 1.0000
10.250 1.5034 0.03276 0.02484 -0.1064 0.0415 1.0000
10.500 1.5146 0.03397 0.02621 -0.1047 0.0399 1.0000
10.750 1.5244 0.03534 0.02771 -0.1031 0.0381 1.0000
11.000 1.5330 0.03683 0.02931 -0.1014 0.0363 1.0000
11.250 1.5394 0.03858 0.03117 -0.0998 0.0347 1.0000
11.500 1.5413 0.04088 0.03352 -0.0981 0.0331 1.0000
11.750 1.5494 0.04263 0.03544 -0.0968 0.0318 1.0000
12.000 1.5561 0.04456 0.03754 -0.0956 0.0303 1.0000
12.250 1.5617 0.04664 0.03975 -0.0945 0.0287 1.0000
12.500 1.5654 0.04897 0.04220 -0.0936 0.0273 1.0000
12.750 1.5647 0.05190 0.04520 -0.0927 0.0261 1.0000
13.000 1.5679 0.05452 0.04801 -0.0920 0.0249 1.0000
13.250 1.5713 0.05719 0.05089 -0.0915 0.0234 1.0000
13.500 1.5728 0.06014 0.05400 -0.0912 0.0220 1.0000
13.750 1.5734 0.06326 0.05726 -0.0911 0.0209 1.0000
14.000 1.5715 0.06680 0.06092 -0.0914 0.0200 1.0000
14.250 1.5687 0.07066 0.06497 -0.0917 0.0191 1.0000
14.500 1.5672 0.07448 0.06901 -0.0922 0.0180 1.0000
14.750 1.5634 0.07875 0.07346 -0.0930 0.0172 1.0000
15.000 1.5592 0.08323 0.07810 -0.0941 0.0165 1.0000
15.250 1.5543 0.08800 0.08303 -0.0956 0.0159 1.0000
15.500 1.5481 0.09310 0.08828 -0.0974 0.0154 1.0000
15.750 1.5402 0.09868 0.09400 -0.0997 0.0150 1.0000
16.000 1.5304 0.10479 0.10023 -0.1023 0.0147 1.0000
16.250 1.5213 0.11093 0.10658 -0.1050 0.0143 1.0000
16.500 1.5112 0.11745 0.11331 -0.1081 0.0140 1.0000
16.750 1.5004 0.12427 0.12034 -0.1117 0.0136 1.0000
17.000 1.4896 0.13131 0.12756 -0.1156 0.0133 1.0000
17.250 1.4777 0.13877 0.13521 -0.1200 0.0131 1.0000
17.500 1.4650 0.14665 0.14327 -0.1249 0.0129 1.0000
17.750 1.4520 0.15487 0.15167 -0.1303 0.0127 1.0000
18.000 1.4369 0.16390 0.16088 -0.1363 0.0126 1.0000
18.250 1.4199 0.17393 0.17109 -0.1433 0.0125 1.0000
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