FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 100,000 Max Cl/Cd: 67.04 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63100-il-100000.txt Download as CSV file: xf-fx63100-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3679 0.09733 0.09271 -0.0366 1.0000 0.1030
-7.750 -0.3950 0.09674 0.09229 -0.0360 1.0000 0.1034
-7.500 -0.4165 0.09471 0.09039 -0.0401 1.0000 0.1037
-7.250 -0.3739 0.08921 0.08480 -0.0294 1.0000 0.1080
-7.000 -0.3836 0.08783 0.08350 -0.0263 1.0000 0.1099
-6.750 -0.3952 0.08629 0.08205 -0.0242 1.0000 0.1124
-6.500 -0.4087 0.08445 0.08030 -0.0240 1.0000 0.1153
-6.250 -0.4272 0.07832 0.07420 -0.0429 1.0000 0.1196
-6.000 -0.4256 0.07701 0.07300 -0.0331 1.0000 0.1211
-5.750 -0.4233 0.07568 0.07172 -0.0276 1.0000 0.1238
-5.500 -0.4104 0.06816 0.06403 -0.0454 1.0000 0.1357
-5.250 -0.4100 0.06748 0.06350 -0.0373 1.0000 0.1381
-5.000 -0.3902 0.06292 0.05885 -0.0443 0.9990 0.1527
-4.750 -0.3556 0.05909 0.05496 -0.0498 0.9938 0.1692
-4.500 -0.2314 0.03713 0.03048 -0.0865 0.9956 0.0891
-4.250 -0.1827 0.03320 0.02602 -0.0920 0.9926 0.0881
-4.000 -0.1336 0.03014 0.02229 -0.0971 0.9890 0.0888
-3.750 -0.0896 0.02737 0.01938 -0.1014 0.9858 0.0943
-3.500 -0.0457 0.02595 0.01757 -0.1047 0.9810 0.1003
-3.250 -0.0030 0.02450 0.01583 -0.1078 0.9761 0.1064
-3.000 0.0406 0.02361 0.01483 -0.1109 0.9716 0.1170
-2.750 0.0779 0.02253 0.01384 -0.1130 0.9650 0.1270
-2.500 0.1233 0.02168 0.01307 -0.1165 0.9604 0.1487
-2.250 0.1636 0.02064 0.01235 -0.1194 0.9535 0.1931
-2.000 0.2108 0.01948 0.01272 -0.1233 0.9487 0.5403
-1.750 0.2431 0.01984 0.01312 -0.1236 0.9396 0.6136
-1.500 0.2813 0.02007 0.01336 -0.1247 0.9329 0.6640
-1.250 0.3063 0.02026 0.01361 -0.1234 0.9229 0.7004
-1.000 0.3424 0.02028 0.01363 -0.1241 0.9167 0.7394
-0.750 0.3676 0.02030 0.01366 -0.1231 0.9068 0.7703
-0.500 0.3960 0.02019 0.01357 -0.1224 0.8990 0.8027
-0.250 0.4230 0.01998 0.01338 -0.1215 0.8908 0.8345
0.000 0.4471 0.01982 0.01323 -0.1202 0.8818 0.8645
0.250 0.4775 0.01942 0.01283 -0.1199 0.8748 0.8959
0.500 0.4993 0.01917 0.01261 -0.1184 0.8649 0.9394
0.750 0.5534 0.01878 0.01217 -0.1234 0.8591 1.0000
1.000 0.5972 0.01883 0.01215 -0.1270 0.8501 1.0000
1.250 0.6467 0.01862 0.01188 -0.1311 0.8436 1.0000
1.500 0.6857 0.01869 0.01192 -0.1334 0.8335 1.0000
1.750 0.7323 0.01841 0.01160 -0.1365 0.8267 1.0000
2.000 0.7658 0.01854 0.01172 -0.1376 0.8148 1.0000
2.250 0.8021 0.01853 0.01170 -0.1388 0.8043 1.0000
2.500 0.8423 0.01826 0.01141 -0.1404 0.7952 1.0000
2.750 0.8742 0.01818 0.01132 -0.1405 0.7810 1.0000
3.000 0.9063 0.01801 0.01116 -0.1405 0.7661 1.0000
3.250 0.9372 0.01790 0.01105 -0.1403 0.7511 1.0000
3.500 0.9671 0.01789 0.01105 -0.1400 0.7364 1.0000
3.750 0.9966 0.01790 0.01109 -0.1397 0.7214 1.0000
4.000 1.0256 0.01793 0.01114 -0.1393 0.7059 1.0000
4.250 1.0543 0.01797 0.01119 -0.1388 0.6900 1.0000
4.500 1.0831 0.01794 0.01117 -0.1383 0.6728 1.0000
4.750 1.1088 0.01795 0.01122 -0.1372 0.6514 1.0000
5.000 1.1352 0.01786 0.01111 -0.1360 0.6282 1.0000
5.250 1.1597 0.01790 0.01116 -0.1347 0.6030 1.0000
5.500 1.1845 0.01797 0.01121 -0.1335 0.5773 1.0000
5.750 1.2073 0.01810 0.01132 -0.1319 0.5470 1.0000
6.000 1.2281 0.01832 0.01150 -0.1302 0.5111 1.0000
6.250 1.2480 0.01868 0.01172 -0.1283 0.4720 1.0000
6.500 1.2664 0.01925 0.01217 -0.1264 0.4296 1.0000
6.750 1.2831 0.01999 0.01276 -0.1243 0.3832 1.0000
7.000 1.2973 0.02092 0.01350 -0.1220 0.3274 1.0000
7.250 1.3064 0.02236 0.01451 -0.1191 0.2620 1.0000
7.500 1.3113 0.02443 0.01606 -0.1158 0.2002 1.0000
7.750 1.3170 0.02660 0.01781 -0.1128 0.1588 1.0000
8.000 1.3277 0.02842 0.01946 -0.1103 0.1337 1.0000
8.250 1.3413 0.03020 0.02112 -0.1083 0.1196 1.0000
8.500 1.3593 0.03198 0.02287 -0.1069 0.1097 1.0000
8.750 1.3803 0.03391 0.02470 -0.1060 0.1017 1.0000
9.000 1.4030 0.03563 0.02652 -0.1053 0.0952 1.0000
9.250 1.4321 0.03810 0.02889 -0.1057 0.0894 1.0000
9.500 1.4525 0.03992 0.03100 -0.1046 0.0845 1.0000
9.750 1.4776 0.04221 0.03329 -0.1045 0.0799 1.0000
10.000 1.4997 0.04524 0.03657 -0.1039 0.0759 1.0000
10.250 1.5143 0.04774 0.03948 -0.1022 0.0728 1.0000
10.500 1.5296 0.05023 0.04219 -0.1008 0.0694 1.0000
10.750 1.5514 0.05498 0.04690 -0.1013 0.0656 1.0000
11.000 1.5501 0.05768 0.05016 -0.0978 0.0645 1.0000
11.250 1.5455 0.06095 0.05394 -0.0943 0.0634 1.0000
11.500 1.5356 0.06438 0.05780 -0.0906 0.0624 1.0000
11.750 1.5207 0.06778 0.06156 -0.0867 0.0616 1.0000
12.000 1.5032 0.07146 0.06557 -0.0834 0.0609 1.0000
12.250 1.4833 0.07566 0.07009 -0.0809 0.0605 1.0000
12.500 1.4605 0.08046 0.07520 -0.0794 0.0604 1.0000
12.750 1.4341 0.08612 0.08116 -0.0789 0.0607 1.0000
13.000 1.4049 0.09263 0.08794 -0.0798 0.0611 1.0000
13.250 1.3743 0.10002 0.09560 -0.0821 0.0618 1.0000
13.500 1.3434 0.10840 0.10419 -0.0859 0.0627 1.0000
13.750 1.3142 0.11749 0.11346 -0.0908 0.0637 1.0000
14.000 1.2880 0.12721 0.12330 -0.0965 0.0646 1.0000
14.250 1.2689 0.13689 0.13304 -0.1018 0.0654 1.0000
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