FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 500,000 Max Cl/Cd: 112.74 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100sm-il-500000.txt Download as CSV file: xf-fx60100sm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX60-100 10.0% smoothed
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2921 0.09078 0.08861 -0.0408 1.0000 0.0194
-9.750 -0.2944 0.08665 0.08452 -0.0416 1.0000 0.0194
-9.500 -0.3080 0.08023 0.07814 -0.0422 1.0000 0.0199
-9.250 -0.3083 0.07816 0.07611 -0.0407 1.0000 0.0203
-9.000 -0.3142 0.07564 0.07362 -0.0393 1.0000 0.0205
-8.750 -0.3235 0.07362 0.07165 -0.0370 1.0000 0.0207
-8.500 -0.3246 0.07022 0.06827 -0.0376 0.9992 0.0210
-8.250 -0.3174 0.06498 0.06304 -0.0416 0.9970 0.0214
-8.000 -0.3108 0.05917 0.05723 -0.0465 0.9944 0.0218
-7.750 -0.3079 0.05279 0.05086 -0.0521 0.9901 0.0222
-7.500 -0.3081 0.04336 0.04144 -0.0621 0.9846 0.0225
-7.250 -0.3062 0.02778 0.02547 -0.0896 0.9757 0.0222
-7.000 -0.2807 0.02200 0.01935 -0.0984 0.9725 0.0234
-6.750 -0.2439 0.01981 0.01668 -0.1039 0.9703 0.0262
-5.750 -0.1512 0.01808 0.01311 -0.1164 0.9607 0.0178
-5.500 -0.1165 0.01545 0.01014 -0.1179 0.9578 0.0164
-5.250 -0.0823 0.01408 0.00862 -0.1193 0.9551 0.0167
-5.000 -0.0555 0.01316 0.00761 -0.1190 0.9483 0.0172
-4.750 -0.0248 0.01230 0.00667 -0.1195 0.9435 0.0179
-4.500 0.0047 0.01189 0.00619 -0.1197 0.9384 0.0191
-4.250 0.0325 0.01093 0.00516 -0.1198 0.9314 0.0202
-4.000 0.0624 0.01015 0.00431 -0.1202 0.9263 0.0218
-3.750 0.0900 0.00971 0.00382 -0.1201 0.9186 0.0242
-3.500 0.1191 0.00929 0.00328 -0.1201 0.9125 0.0276
-3.250 0.1474 0.00884 0.00281 -0.1201 0.9049 0.0406
-3.000 0.1769 0.00744 0.00233 -0.1214 0.8984 0.2995
-2.750 0.2046 0.00722 0.00228 -0.1214 0.8905 0.3675
-2.500 0.2327 0.00713 0.00220 -0.1212 0.8833 0.4007
-2.250 0.2604 0.00708 0.00217 -0.1210 0.8746 0.4277
-2.000 0.2884 0.00705 0.00213 -0.1207 0.8670 0.4527
-1.750 0.3162 0.00701 0.00208 -0.1205 0.8576 0.4665
-1.500 0.3442 0.00699 0.00201 -0.1203 0.8488 0.4789
-1.250 0.3722 0.00698 0.00196 -0.1201 0.8397 0.4919
-1.000 0.4000 0.00695 0.00193 -0.1199 0.8293 0.5040
-0.750 0.4279 0.00693 0.00190 -0.1197 0.8192 0.5158
-0.500 0.4558 0.00692 0.00187 -0.1195 0.8087 0.5276
-0.250 0.4836 0.00692 0.00185 -0.1193 0.7970 0.5393
0.000 0.5114 0.00693 0.00184 -0.1191 0.7845 0.5514
0.250 0.5391 0.00694 0.00184 -0.1189 0.7716 0.5634
0.500 0.5667 0.00696 0.00185 -0.1186 0.7581 0.5757
0.750 0.5942 0.00699 0.00187 -0.1184 0.7440 0.5885
1.000 0.6217 0.00703 0.00190 -0.1181 0.7291 0.6020
1.250 0.6490 0.00708 0.00194 -0.1179 0.7126 0.6160
1.500 0.6761 0.00715 0.00200 -0.1176 0.6952 0.6309
1.750 0.7031 0.00723 0.00206 -0.1173 0.6768 0.6468
2.000 0.7299 0.00732 0.00213 -0.1169 0.6555 0.6639
2.250 0.7562 0.00745 0.00221 -0.1165 0.6306 0.6827
2.500 0.7822 0.00758 0.00233 -0.1160 0.6048 0.7028
3.000 0.8340 0.00785 0.00258 -0.1150 0.5545 0.7548
3.250 0.8590 0.00797 0.00273 -0.1144 0.5299 0.7915
3.500 0.8810 0.00797 0.00287 -0.1130 0.5075 0.8617
3.750 0.9042 0.00802 0.00296 -0.1119 0.4834 1.0000
4.000 0.9303 0.00832 0.00313 -0.1116 0.4555 1.0000
4.250 0.9562 0.00864 0.00333 -0.1113 0.4284 1.0000
4.500 0.9820 0.00897 0.00356 -0.1109 0.4009 1.0000
4.750 1.0074 0.00933 0.00380 -0.1106 0.3711 1.0000
5.000 1.0322 0.00975 0.00407 -0.1101 0.3364 1.0000
5.250 1.0565 0.01023 0.00439 -0.1096 0.3002 1.0000
5.500 1.0807 0.01073 0.00473 -0.1091 0.2639 1.0000
5.750 1.1041 0.01131 0.00512 -0.1085 0.2264 1.0000
6.000 1.1269 0.01197 0.00557 -0.1079 0.1873 1.0000
6.250 1.1498 0.01261 0.00605 -0.1072 0.1545 1.0000
6.500 1.1727 0.01323 0.00654 -0.1065 0.1308 1.0000
6.750 1.1960 0.01379 0.00703 -0.1059 0.1149 1.0000
7.000 1.2191 0.01435 0.00755 -0.1052 0.1031 1.0000
7.250 1.2420 0.01491 0.00807 -0.1045 0.0941 1.0000
7.500 1.2656 0.01538 0.00859 -0.1039 0.0875 1.0000
7.750 1.2872 0.01604 0.00920 -0.1030 0.0798 1.0000
8.000 1.3112 0.01640 0.00964 -0.1024 0.0750 1.0000
8.250 1.3330 0.01698 0.01019 -0.1016 0.0690 1.0000
8.500 1.3554 0.01748 0.01074 -0.1008 0.0645 1.0000
8.750 1.3781 0.01791 0.01121 -0.1001 0.0594 1.0000
9.000 1.3986 0.01855 0.01186 -0.0991 0.0542 1.0000
9.250 1.4215 0.01892 0.01229 -0.0985 0.0496 1.0000
9.500 1.4407 0.01962 0.01297 -0.0973 0.0440 1.0000
9.750 1.4627 0.02002 0.01342 -0.0966 0.0393 1.0000
10.000 1.4811 0.02072 0.01412 -0.0953 0.0335 1.0000
10.250 1.4974 0.02159 0.01496 -0.0938 0.0265 1.0000
10.500 1.5123 0.02251 0.01590 -0.0920 0.0209 1.0000
10.750 1.5231 0.02356 0.01700 -0.0896 0.0170 1.0000
11.000 1.5274 0.02499 0.01848 -0.0863 0.0143 1.0000
11.250 1.5367 0.02605 0.01965 -0.0838 0.0129 1.0000
11.500 1.5434 0.02733 0.02101 -0.0813 0.0117 1.0000
11.750 1.5419 0.02929 0.02307 -0.0780 0.0106 1.0000
12.000 1.5455 0.03093 0.02485 -0.0756 0.0101 1.0000
12.250 1.5513 0.03247 0.02652 -0.0736 0.0095 1.0000
12.500 1.5551 0.03424 0.02841 -0.0717 0.0090 1.0000
12.750 1.5575 0.03623 0.03052 -0.0700 0.0086 1.0000
13.000 1.5577 0.03853 0.03294 -0.0684 0.0083 1.0000
13.250 1.5556 0.04119 0.03573 -0.0670 0.0080 1.0000
13.500 1.5501 0.04437 0.03905 -0.0659 0.0078 1.0000
13.750 1.5411 0.04819 0.04301 -0.0652 0.0076 1.0000
14.000 1.5292 0.05264 0.04763 -0.0650 0.0075 1.0000
14.250 1.5152 0.05768 0.05284 -0.0653 0.0073 1.0000
14.500 1.5099 0.06180 0.05711 -0.0660 0.0073 1.0000
14.750 1.5038 0.06626 0.06174 -0.0671 0.0072 1.0000
15.000 1.4958 0.07123 0.06688 -0.0686 0.0071 1.0000
15.250 1.4869 0.07660 0.07241 -0.0705 0.0071 1.0000
15.500 1.4769 0.08241 0.07839 -0.0728 0.0070 1.0000
15.750 1.4657 0.08866 0.08480 -0.0755 0.0070 1.0000
16.000 1.4534 0.09534 0.09165 -0.0787 0.0069 1.0000
16.250 1.4411 0.10230 0.09877 -0.0821 0.0069 1.0000
16.500 1.4275 0.10968 0.10631 -0.0860 0.0069 1.0000
16.750 1.4142 0.11726 0.11405 -0.0901 0.0068 1.0000
17.000 1.4006 0.12510 0.12205 -0.0946 0.0068 1.0000
17.250 1.3871 0.13311 0.13020 -0.0993 0.0068 1.0000
17.500 1.3730 0.14141 0.13865 -0.1043 0.0068 1.0000
17.750 1.3592 0.14990 0.14729 -0.1096 0.0069 1.0000
18.000 1.3462 0.15849 0.15602 -0.1152 0.0068 1.0000
18.250 1.3324 0.16748 0.16515 -0.1211 0.0069 1.0000
18.500 1.3184 0.17676 0.17457 -0.1272 0.0069 1.0000
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Polar data table (+)
Polar graphs
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