WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 500,000 Max Cl/Cd: 108.18 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601261-il-500000.txt Download as CSV file: xf-fx601261-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3491 0.08618 0.08405 -0.0453 1.0000 0.0206
-9.000 -0.3522 0.08314 0.08106 -0.0454 1.0000 0.0209
-8.750 -0.3609 0.08001 0.07799 -0.0451 1.0000 0.0212
-8.500 -0.3520 0.07339 0.07139 -0.0524 0.9970 0.0218
-8.250 -0.3760 0.04786 0.04556 -0.0889 0.9737 0.0210
-8.000 -0.3544 0.04167 0.03910 -0.1018 0.9603 0.0218
-5.750 -0.0763 0.00536 0.00024 -0.1271 0.8625 0.0351
-5.500 -0.0409 0.01496 0.00902 -0.1312 0.8716 0.0151
-5.250 -0.0160 0.01357 0.00766 -0.1307 0.8628 0.0141
-5.000 0.0118 0.01274 0.00673 -0.1308 0.8549 0.0134
-4.750 0.0386 0.01208 0.00600 -0.1306 0.8459 0.0130
-4.500 0.0671 0.01153 0.00535 -0.1307 0.8385 0.0128
-4.250 0.0950 0.01103 0.00478 -0.1308 0.8305 0.0130
-4.000 0.1239 0.01063 0.00428 -0.1310 0.8235 0.0134
-3.750 0.1522 0.01028 0.00387 -0.1310 0.8156 0.0141
-3.500 0.1811 0.01006 0.00353 -0.1311 0.8086 0.0149
-3.250 0.2093 0.00976 0.00314 -0.1310 0.8000 0.0168
-3.000 0.2379 0.00959 0.00287 -0.1310 0.7922 0.0201
-2.750 0.2666 0.00915 0.00259 -0.1312 0.7835 0.0728
-2.500 0.2959 0.00814 0.00228 -0.1323 0.7756 0.2751
-2.250 0.3243 0.00789 0.00226 -0.1325 0.7674 0.3597
-2.000 0.3525 0.00785 0.00225 -0.1324 0.7590 0.3917
-1.750 0.3807 0.00785 0.00226 -0.1323 0.7504 0.4208
-1.500 0.4087 0.00787 0.00228 -0.1322 0.7410 0.4436
-1.250 0.4367 0.00790 0.00228 -0.1320 0.7319 0.4578
-1.000 0.4646 0.00791 0.00226 -0.1318 0.7216 0.4677
-0.750 0.4926 0.00794 0.00226 -0.1316 0.7115 0.4783
-0.500 0.5204 0.00799 0.00226 -0.1314 0.7020 0.4884
-0.250 0.5482 0.00801 0.00227 -0.1312 0.6914 0.4975
0.250 0.6033 0.00810 0.00229 -0.1307 0.6669 0.5156
0.500 0.6303 0.00816 0.00230 -0.1304 0.6512 0.5243
0.750 0.6572 0.00823 0.00232 -0.1300 0.6347 0.5324
1.000 0.6842 0.00831 0.00234 -0.1297 0.6192 0.5402
1.250 0.7114 0.00839 0.00239 -0.1294 0.6059 0.5482
1.500 0.7386 0.00847 0.00246 -0.1292 0.5929 0.5562
1.750 0.7657 0.00857 0.00253 -0.1289 0.5802 0.5657
2.000 0.7927 0.00867 0.00261 -0.1286 0.5672 0.5752
2.250 0.8195 0.00878 0.00269 -0.1283 0.5544 0.5853
2.500 0.8463 0.00889 0.00280 -0.1280 0.5403 0.5952
2.750 0.8726 0.00902 0.00290 -0.1277 0.5231 0.6049
3.000 0.8989 0.00917 0.00301 -0.1273 0.5044 0.6161
3.500 0.9514 0.00946 0.00329 -0.1266 0.4720 0.6409
3.750 0.9775 0.00961 0.00344 -0.1262 0.4563 0.6547
4.000 1.0035 0.00977 0.00360 -0.1258 0.4405 0.6708
4.250 1.0290 0.00995 0.00380 -0.1253 0.4228 0.6906
4.500 1.0541 0.01014 0.00401 -0.1248 0.4054 0.7154
4.750 1.0790 0.01031 0.00423 -0.1243 0.3875 0.7493
5.000 1.1027 0.01043 0.00446 -0.1234 0.3696 0.8009
5.250 1.1186 0.01034 0.00459 -0.1207 0.3535 1.0000
5.500 1.1437 0.01066 0.00483 -0.1202 0.3354 1.0000
6.000 1.1926 0.01139 0.00539 -0.1192 0.2959 1.0000
6.250 1.2162 0.01181 0.00571 -0.1185 0.2753 1.0000
6.500 1.2395 0.01225 0.00606 -0.1178 0.2537 1.0000
6.750 1.2620 0.01273 0.00643 -0.1170 0.2319 1.0000
7.000 1.2841 0.01324 0.00684 -0.1162 0.2112 1.0000
7.250 1.3055 0.01379 0.00728 -0.1152 0.1884 1.0000
7.500 1.3262 0.01439 0.00777 -0.1142 0.1703 1.0000
7.750 1.3467 0.01496 0.00826 -0.1131 0.1495 1.0000
8.000 1.3658 0.01563 0.00880 -0.1118 0.1320 1.0000
8.250 1.3859 0.01618 0.00931 -0.1107 0.1190 1.0000
8.500 1.4058 0.01672 0.00982 -0.1095 0.1083 1.0000
8.750 1.4245 0.01731 0.01037 -0.1082 0.0986 1.0000
9.000 1.4417 0.01797 0.01097 -0.1066 0.0897 1.0000
9.250 1.4601 0.01846 0.01148 -0.1052 0.0823 1.0000
9.500 1.4746 0.01910 0.01209 -0.1032 0.0734 1.0000
10.000 1.5008 0.02049 0.01342 -0.0988 0.0591 1.0000
10.250 1.5122 0.02129 0.01421 -0.0965 0.0540 1.0000
10.500 1.5270 0.02189 0.01488 -0.0948 0.0506 1.0000
10.750 1.5371 0.02281 0.01577 -0.0925 0.0414 1.0000
11.000 1.5447 0.02393 0.01683 -0.0902 0.0348 1.0000
11.250 1.5530 0.02504 0.01794 -0.0880 0.0314 1.0000
11.500 1.5602 0.02629 0.01920 -0.0859 0.0285 1.0000
11.750 1.5689 0.02749 0.02045 -0.0841 0.0262 1.0000
12.000 1.5806 0.02852 0.02158 -0.0827 0.0246 1.0000
12.250 1.5864 0.03005 0.02314 -0.0810 0.0197 1.0000
12.500 1.5768 0.03298 0.02597 -0.0784 0.0056 1.0000
12.750 1.5765 0.03528 0.02833 -0.0768 0.0041 1.0000
13.000 1.5782 0.03751 0.03066 -0.0754 0.0037 1.0000
13.250 1.5807 0.03974 0.03300 -0.0743 0.0035 1.0000
13.500 1.5823 0.04217 0.03555 -0.0734 0.0033 1.0000
13.750 1.5836 0.04472 0.03822 -0.0727 0.0032 1.0000
14.000 1.5840 0.04746 0.04109 -0.0721 0.0031 1.0000
14.250 1.5832 0.05046 0.04422 -0.0718 0.0030 1.0000
14.500 1.5820 0.05364 0.04754 -0.0716 0.0029 1.0000
14.750 1.5803 0.05700 0.05105 -0.0717 0.0029 1.0000
15.000 1.5770 0.06072 0.05491 -0.0720 0.0028 1.0000
15.250 1.5735 0.06463 0.05896 -0.0726 0.0028 1.0000
15.500 1.5681 0.06897 0.06345 -0.0735 0.0027 1.0000
15.750 1.5620 0.07356 0.06819 -0.0746 0.0027 1.0000
16.000 1.5541 0.07860 0.07338 -0.0761 0.0027 1.0000
16.250 1.5451 0.08401 0.07895 -0.0779 0.0026 1.0000
16.500 1.5356 0.08966 0.08474 -0.0800 0.0026 1.0000
16.750 1.5244 0.09580 0.09104 -0.0825 0.0026 1.0000
17.000 1.5124 0.10224 0.09763 -0.0852 0.0026 1.0000
17.250 1.5002 0.10888 0.10443 -0.0883 0.0026 1.0000
17.500 1.4868 0.11591 0.11161 -0.0917 0.0026 1.0000
17.750 1.4723 0.12331 0.11917 -0.0955 0.0025 1.0000
18.000 1.4602 0.13035 0.12635 -0.0992 0.0026 1.0000
18.250 1.4456 0.13803 0.13417 -0.1035 0.0026 1.0000
18.500 1.4315 0.14574 0.14203 -0.1079 0.0025 1.0000
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Polar data table (+)
Polar graphs
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