FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.42 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63100-il-1000000-n5.txt Download as CSV file: xf-fx63100-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4008 0.13598 0.13419 -0.0263 1.0000 0.0048
-12.500 -0.3988 0.13200 0.13021 -0.0274 1.0000 0.0049
-12.000 -0.7726 0.03034 0.02778 -0.1061 0.9920 0.0053
-11.750 -0.7446 0.02648 0.02362 -0.1136 0.9893 0.0054
-11.500 -0.7137 0.02413 0.02106 -0.1183 0.9876 0.0055
-11.250 -0.6812 0.02226 0.01899 -0.1221 0.9864 0.0056
-11.000 -0.6553 0.02040 0.01693 -0.1244 0.9828 0.0057
-10.750 -0.6244 0.01859 0.01493 -0.1273 0.9803 0.0060
-10.500 -0.5919 0.01739 0.01358 -0.1297 0.9785 0.0062
-10.000 -0.5330 0.01559 0.01158 -0.1322 0.9713 0.0066
-9.500 -0.4730 0.01413 0.00992 -0.1344 0.9623 0.0070
-9.250 -0.4417 0.01344 0.00912 -0.1356 0.9568 0.0073
-9.000 -0.4080 0.01280 0.00840 -0.1373 0.9515 0.0075
-8.750 -0.3714 0.01222 0.00772 -0.1395 0.9456 0.0078
-8.500 -0.3308 0.01156 0.00695 -0.1426 0.9403 0.0081
-8.250 -0.2905 0.01093 0.00624 -0.1456 0.9314 0.0088
-8.000 -0.2517 0.01047 0.00568 -0.1482 0.9199 0.0094
-7.750 -0.2172 0.01012 0.00522 -0.1498 0.9055 0.0101
-7.500 -0.1865 0.00985 0.00484 -0.1505 0.8917 0.0107
-7.250 -0.1572 0.00954 0.00443 -0.1509 0.8798 0.0116
-7.000 -0.1285 0.00928 0.00411 -0.1512 0.8688 0.0128
-6.750 -0.0998 0.00906 0.00382 -0.1514 0.8588 0.0139
-6.500 -0.0713 0.00886 0.00355 -0.1516 0.8494 0.0153
-6.250 -0.0427 0.00868 0.00336 -0.1517 0.8404 0.0174
-6.000 -0.0142 0.00855 0.00317 -0.1518 0.8321 0.0192
-5.750 0.0144 0.00838 0.00298 -0.1520 0.8233 0.0215
-5.500 0.0430 0.00827 0.00283 -0.1521 0.8154 0.0235
-5.250 0.0716 0.00816 0.00267 -0.1522 0.8071 0.0249
-5.000 0.1000 0.00809 0.00255 -0.1523 0.7982 0.0259
-4.750 0.1286 0.00793 0.00231 -0.1524 0.7870 0.0280
-4.250 0.1854 0.00774 0.00201 -0.1525 0.7621 0.0319
-4.000 0.2140 0.00766 0.00188 -0.1526 0.7528 0.0335
-3.750 0.2426 0.00760 0.00176 -0.1527 0.7444 0.0345
-3.500 0.2716 0.00750 0.00162 -0.1529 0.7362 0.0363
-3.000 0.3294 0.00733 0.00140 -0.1532 0.7199 0.0448
-2.750 0.3581 0.00727 0.00132 -0.1533 0.7118 0.0527
-2.500 0.3872 0.00718 0.00126 -0.1535 0.7035 0.0669
-2.250 0.4160 0.00712 0.00121 -0.1536 0.6954 0.0833
-2.000 0.4449 0.00707 0.00117 -0.1538 0.6871 0.0957
-1.750 0.4736 0.00704 0.00113 -0.1539 0.6792 0.1082
-1.500 0.5025 0.00697 0.00109 -0.1541 0.6703 0.1287
-1.250 0.5327 0.00673 0.00104 -0.1548 0.6624 0.2128
-1.000 0.5627 0.00650 0.00105 -0.1554 0.6536 0.3155
-0.750 0.5918 0.00644 0.00107 -0.1557 0.6449 0.3575
-0.500 0.6204 0.00642 0.00110 -0.1558 0.6359 0.3910
-0.250 0.6493 0.00639 0.00112 -0.1560 0.6264 0.4189
0.000 0.6776 0.00643 0.00115 -0.1560 0.6142 0.4395
0.250 0.7057 0.00646 0.00120 -0.1560 0.5964 0.4743
0.500 0.7334 0.00654 0.00129 -0.1560 0.5745 0.5203
0.750 0.7609 0.00666 0.00137 -0.1559 0.5522 0.5428
1.000 0.7878 0.00684 0.00147 -0.1556 0.5255 0.5607
1.250 0.8136 0.00714 0.00160 -0.1552 0.4833 0.5794
1.500 0.8399 0.00741 0.00174 -0.1549 0.4502 0.5918
1.750 0.8667 0.00761 0.00187 -0.1547 0.4280 0.5998
2.000 0.8933 0.00785 0.00201 -0.1544 0.4040 0.6075
2.250 0.9203 0.00804 0.00214 -0.1542 0.3858 0.6140
2.500 0.9474 0.00822 0.00227 -0.1540 0.3688 0.6209
2.750 0.9741 0.00844 0.00242 -0.1538 0.3496 0.6272
3.000 1.0002 0.00872 0.00260 -0.1535 0.3222 0.6345
3.500 1.0488 0.00970 0.00317 -0.1524 0.2315 0.6494
3.750 1.0734 0.01015 0.00346 -0.1519 0.1978 0.6567
4.000 1.0989 0.01049 0.00372 -0.1515 0.1745 0.6649
4.250 1.1242 0.01085 0.00399 -0.1511 0.1525 0.6754
4.500 1.1494 0.01122 0.00429 -0.1507 0.1303 0.6882
4.750 1.1739 0.01166 0.00462 -0.1501 0.1038 0.7006
5.000 1.1986 0.01206 0.00496 -0.1496 0.0857 0.7134
5.250 1.2239 0.01239 0.00528 -0.1492 0.0747 0.7277
5.500 1.2493 0.01269 0.00558 -0.1488 0.0669 0.7441
5.750 1.2747 0.01298 0.00589 -0.1484 0.0595 0.7630
6.000 1.2991 0.01336 0.00626 -0.1479 0.0480 0.7849
6.250 1.3233 0.01371 0.00665 -0.1473 0.0400 0.8130
6.500 1.3473 0.01397 0.00700 -0.1466 0.0373 0.8564
6.750 1.3646 0.01407 0.00726 -0.1444 0.0353 1.0000
7.000 1.3892 0.01443 0.00763 -0.1439 0.0335 1.0000
7.250 1.4137 0.01477 0.00800 -0.1434 0.0326 1.0000
7.500 1.4381 0.01511 0.00837 -0.1428 0.0321 1.0000
7.750 1.4621 0.01548 0.00876 -0.1423 0.0310 1.0000
8.000 1.4855 0.01589 0.00918 -0.1416 0.0295 1.0000
8.250 1.5083 0.01635 0.00965 -0.1408 0.0281 1.0000
8.500 1.5305 0.01684 0.01017 -0.1400 0.0267 1.0000
8.750 1.5525 0.01733 0.01069 -0.1391 0.0257 1.0000
9.000 1.5755 0.01768 0.01108 -0.1384 0.0253 1.0000
9.250 1.5979 0.01807 0.01151 -0.1376 0.0246 1.0000
9.500 1.6197 0.01850 0.01198 -0.1367 0.0237 1.0000
9.750 1.6408 0.01896 0.01247 -0.1358 0.0224 1.0000
10.000 1.6607 0.01948 0.01301 -0.1346 0.0208 1.0000
10.250 1.6798 0.02005 0.01360 -0.1333 0.0193 1.0000
10.500 1.6988 0.02057 0.01415 -0.1320 0.0180 1.0000
10.750 1.7150 0.02117 0.01476 -0.1303 0.0155 1.0000
11.000 1.7280 0.02186 0.01545 -0.1280 0.0133 1.0000
11.250 1.7392 0.02267 0.01627 -0.1255 0.0112 1.0000
11.500 1.7504 0.02350 0.01714 -0.1231 0.0099 1.0000
11.750 1.7603 0.02445 0.01814 -0.1206 0.0088 1.0000
12.000 1.7698 0.02547 0.01922 -0.1182 0.0079 1.0000
12.250 1.7795 0.02651 0.02033 -0.1160 0.0073 1.0000
12.500 1.7878 0.02769 0.02157 -0.1137 0.0067 1.0000
12.750 1.7951 0.02901 0.02295 -0.1115 0.0062 1.0000
13.000 1.8017 0.03044 0.02446 -0.1094 0.0058 1.0000
13.250 1.8094 0.03184 0.02595 -0.1075 0.0056 1.0000
13.500 1.8162 0.03339 0.02758 -0.1058 0.0053 1.0000
13.750 1.8220 0.03509 0.02937 -0.1041 0.0051 1.0000
14.000 1.8267 0.03697 0.03133 -0.1026 0.0049 1.0000
14.250 1.8306 0.03901 0.03346 -0.1011 0.0047 1.0000
14.500 1.8328 0.04130 0.03583 -0.0998 0.0045 1.0000
14.750 1.8342 0.04378 0.03842 -0.0987 0.0043 1.0000
15.000 1.8338 0.04657 0.04131 -0.0977 0.0041 1.0000
15.250 1.8351 0.04925 0.04411 -0.0970 0.0040 1.0000
15.500 1.8354 0.05215 0.04712 -0.0964 0.0039 1.0000
15.750 1.8347 0.05529 0.05037 -0.0961 0.0038 1.0000
16.000 1.8328 0.05872 0.05392 -0.0959 0.0038 1.0000
16.250 1.8301 0.06237 0.05768 -0.0961 0.0037 1.0000
16.500 1.8260 0.06638 0.06181 -0.0964 0.0036 1.0000
16.750 1.8208 0.07070 0.06625 -0.0971 0.0035 1.0000
17.000 1.8146 0.07536 0.07103 -0.0981 0.0034 1.0000
17.250 1.8065 0.08044 0.07625 -0.0994 0.0034 1.0000
17.500 1.7975 0.08590 0.08183 -0.1010 0.0033 1.0000
17.750 1.7864 0.09191 0.08798 -0.1031 0.0032 1.0000
18.000 1.7751 0.09811 0.09430 -0.1055 0.0031 1.0000
18.250 1.7612 0.10498 0.10132 -0.1084 0.0031 1.0000
18.500 1.7468 0.11211 0.10860 -0.1117 0.0031 1.0000
18.750 1.7314 0.11963 0.11627 -0.1154 0.0030 1.0000
19.000 1.7134 0.12779 0.12457 -0.1196 0.0030 1.0000
19.250 1.6961 0.13599 0.13292 -0.1242 0.0030 1.0000
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