FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 500,000 Max Cl/Cd: 106.21 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63100-il-500000-n5.txt Download as CSV file: xf-fx63100-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2756 0.10397 0.10177 -0.0372 1.0000 0.0087
-10.750 -0.2715 0.09892 0.09673 -0.0398 0.9991 0.0088
-10.250 -0.6007 0.03371 0.03083 -0.1003 0.9871 0.0079
-10.000 -0.5732 0.02662 0.02314 -0.1128 0.9808 0.0082
-9.750 -0.5401 0.02390 0.02014 -0.1178 0.9780 0.0084
-9.500 -0.5104 0.02217 0.01821 -0.1205 0.9736 0.0087
-9.250 -0.4790 0.02058 0.01640 -0.1231 0.9694 0.0090
-8.750 -0.4172 0.01790 0.01332 -0.1270 0.9596 0.0098
-8.250 -0.3542 0.01588 0.01092 -0.1300 0.9488 0.0108
-8.000 -0.3197 0.01484 0.00975 -0.1322 0.9442 0.0116
-7.750 -0.2844 0.01418 0.00900 -0.1342 0.9398 0.0123
-7.500 -0.2485 0.01352 0.00823 -0.1362 0.9341 0.0131
-7.250 -0.2098 0.01283 0.00742 -0.1388 0.9295 0.0141
-7.000 -0.1715 0.01217 0.00665 -0.1414 0.9238 0.0153
-6.750 -0.1337 0.01179 0.00624 -0.1436 0.9167 0.0169
-6.500 -0.0966 0.01144 0.00579 -0.1457 0.9087 0.0188
-6.250 -0.0614 0.01101 0.00530 -0.1474 0.8996 0.0207
-6.000 -0.0291 0.01078 0.00500 -0.1484 0.8898 0.0228
-5.750 0.0024 0.01058 0.00470 -0.1491 0.8801 0.0249
-5.500 0.0324 0.01032 0.00436 -0.1496 0.8701 0.0269
-5.250 0.0623 0.01004 0.00403 -0.1501 0.8612 0.0293
-5.000 0.0916 0.00988 0.00379 -0.1504 0.8520 0.0315
-4.750 0.1206 0.00972 0.00356 -0.1507 0.8432 0.0336
-4.250 0.1792 0.00927 0.00296 -0.1513 0.8262 0.0383
-4.000 0.2083 0.00910 0.00274 -0.1515 0.8165 0.0413
-3.750 0.2369 0.00897 0.00253 -0.1516 0.8048 0.0440
-3.500 0.2654 0.00886 0.00233 -0.1516 0.7928 0.0466
-3.250 0.2944 0.00873 0.00216 -0.1518 0.7830 0.0524
-3.000 0.3232 0.00863 0.00203 -0.1519 0.7744 0.0619
-2.750 0.3523 0.00849 0.00192 -0.1522 0.7660 0.0784
-2.500 0.3810 0.00841 0.00183 -0.1523 0.7578 0.0939
-2.250 0.4100 0.00832 0.00174 -0.1525 0.7493 0.1095
-2.000 0.4390 0.00821 0.00165 -0.1528 0.7412 0.1332
-1.750 0.4696 0.00784 0.00157 -0.1536 0.7327 0.2381
-1.500 0.4991 0.00765 0.00157 -0.1541 0.7245 0.3226
-1.250 0.5283 0.00753 0.00158 -0.1545 0.7158 0.3844
-0.750 0.5861 0.00740 0.00161 -0.1548 0.6988 0.4624
-0.500 0.6147 0.00738 0.00166 -0.1549 0.6901 0.4974
-0.250 0.6430 0.00742 0.00172 -0.1549 0.6815 0.5316
0.000 0.6713 0.00745 0.00178 -0.1549 0.6721 0.5602
0.250 0.6993 0.00751 0.00183 -0.1548 0.6628 0.5769
0.500 0.7272 0.00758 0.00189 -0.1547 0.6530 0.5936
0.750 0.7548 0.00766 0.00196 -0.1545 0.6405 0.6107
1.000 0.7819 0.00777 0.00203 -0.1542 0.6237 0.6222
1.250 0.8087 0.00791 0.00210 -0.1539 0.6039 0.6308
1.500 0.8357 0.00804 0.00218 -0.1536 0.5856 0.6396
1.750 0.8628 0.00817 0.00228 -0.1534 0.5696 0.6476
2.000 0.8890 0.00837 0.00239 -0.1530 0.5451 0.6566
2.250 0.9145 0.00862 0.00253 -0.1525 0.5121 0.6656
2.500 0.9394 0.00895 0.00270 -0.1519 0.4746 0.6746
2.750 0.9649 0.00924 0.00290 -0.1514 0.4467 0.6836
3.000 0.9909 0.00949 0.00309 -0.1510 0.4259 0.6926
3.250 1.0170 0.00973 0.00328 -0.1507 0.4082 0.7031
3.500 1.0429 0.00999 0.00351 -0.1503 0.3856 0.7142
3.750 1.0679 0.01034 0.00376 -0.1498 0.3560 0.7268
4.000 1.0919 0.01078 0.00405 -0.1492 0.3170 0.7414
4.250 1.1150 0.01132 0.00440 -0.1485 0.2716 0.7571
4.500 1.1384 0.01182 0.00478 -0.1478 0.2351 0.7738
4.750 1.1620 0.01226 0.00515 -0.1471 0.2077 0.7929
5.000 1.1851 0.01269 0.00552 -0.1463 0.1832 0.8174
5.250 1.2065 0.01305 0.00589 -0.1450 0.1600 0.8580
5.500 1.2222 0.01329 0.00616 -0.1425 0.1380 1.0000
5.750 1.2455 0.01388 0.00660 -0.1419 0.1115 1.0000
6.000 1.2684 0.01447 0.00707 -0.1412 0.0903 1.0000
6.250 1.2921 0.01497 0.00751 -0.1406 0.0785 1.0000
6.500 1.3159 0.01543 0.00796 -0.1400 0.0696 1.0000
6.750 1.3392 0.01593 0.00843 -0.1393 0.0612 1.0000
7.000 1.3621 0.01645 0.00892 -0.1386 0.0524 1.0000
7.250 1.3851 0.01694 0.00941 -0.1379 0.0470 1.0000
7.500 1.4073 0.01748 0.00995 -0.1370 0.0428 1.0000
7.750 1.4297 0.01799 0.01049 -0.1362 0.0404 1.0000
8.000 1.4516 0.01850 0.01104 -0.1353 0.0388 1.0000
8.250 1.4729 0.01906 0.01163 -0.1343 0.0374 1.0000
8.500 1.4932 0.01968 0.01227 -0.1332 0.0354 1.0000
8.750 1.5117 0.02042 0.01305 -0.1318 0.0329 1.0000
9.000 1.5321 0.02094 0.01364 -0.1308 0.0320 1.0000
9.250 1.5513 0.02153 0.01430 -0.1295 0.0308 1.0000
9.500 1.5692 0.02216 0.01500 -0.1281 0.0296 1.0000
9.750 1.5844 0.02286 0.01575 -0.1262 0.0284 1.0000
10.000 1.5972 0.02366 0.01659 -0.1239 0.0271 1.0000
10.250 1.6069 0.02467 0.01766 -0.1213 0.0258 1.0000
10.500 1.6225 0.02527 0.01837 -0.1196 0.0251 1.0000
10.750 1.6369 0.02598 0.01916 -0.1178 0.0240 1.0000
11.000 1.6503 0.02678 0.02004 -0.1159 0.0226 1.0000
11.250 1.6627 0.02768 0.02100 -0.1141 0.0212 1.0000
11.500 1.6731 0.02876 0.02212 -0.1121 0.0197 1.0000
11.750 1.6848 0.02977 0.02323 -0.1104 0.0184 1.0000
12.000 1.6956 0.03089 0.02440 -0.1087 0.0164 1.0000
12.250 1.7049 0.03219 0.02572 -0.1070 0.0145 1.0000
12.500 1.7126 0.03366 0.02727 -0.1053 0.0131 1.0000
12.750 1.7191 0.03532 0.02901 -0.1036 0.0118 1.0000
13.000 1.7240 0.03720 0.03095 -0.1020 0.0107 1.0000
13.250 1.7287 0.03917 0.03304 -0.1005 0.0100 1.0000
13.500 1.7322 0.04135 0.03532 -0.0992 0.0094 1.0000
13.750 1.7342 0.04377 0.03784 -0.0980 0.0088 1.0000
14.000 1.7346 0.04648 0.04066 -0.0970 0.0083 1.0000
14.250 1.7345 0.04935 0.04364 -0.0962 0.0080 1.0000
14.500 1.7346 0.05227 0.04670 -0.0956 0.0077 1.0000
14.750 1.7338 0.05542 0.04998 -0.0952 0.0074 1.0000
15.000 1.7316 0.05887 0.05358 -0.0950 0.0071 1.0000
15.250 1.7283 0.06262 0.05745 -0.0951 0.0068 1.0000
15.500 1.7238 0.06667 0.06164 -0.0954 0.0066 1.0000
15.750 1.7176 0.07116 0.06626 -0.0961 0.0063 1.0000
16.000 1.7102 0.07602 0.07127 -0.0971 0.0062 1.0000
16.250 1.7008 0.08138 0.07677 -0.0986 0.0060 1.0000
16.500 1.6891 0.08741 0.08295 -0.1005 0.0059 1.0000
16.750 1.6797 0.09322 0.08892 -0.1026 0.0058 1.0000
17.000 1.6688 0.09947 0.09536 -0.1051 0.0057 1.0000
17.250 1.6570 0.10608 0.10214 -0.1079 0.0056 1.0000
17.500 1.6436 0.11318 0.10940 -0.1112 0.0056 1.0000
17.750 1.6310 0.12027 0.11665 -0.1147 0.0055 1.0000
18.000 1.6160 0.12801 0.12456 -0.1188 0.0054 1.0000
18.250 1.6006 0.13601 0.13272 -0.1233 0.0054 1.0000
18.500 1.5857 0.14408 0.14094 -0.1280 0.0053 1.0000
18.750 1.5704 0.15245 0.14947 -0.1332 0.0054 1.0000
19.000 1.5553 0.16091 0.15808 -0.1386 0.0053 1.0000
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