FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.14 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601001-il-1000000.txt Download as CSV file: xf-fx601001-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 (126) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4076 0.10786 0.10618 -0.0298 1.0000 0.0109
-10.500 -0.4059 0.10381 0.10214 -0.0314 1.0000 0.0114
-8.750 -0.5295 0.02770 0.02509 -0.0939 0.9881 0.0078
-8.500 -0.4979 0.02236 0.01918 -0.1006 0.9854 0.0078
-8.250 -0.4640 0.02006 0.01658 -0.1040 0.9840 0.0081
-8.000 -0.4296 0.01763 0.01382 -0.1071 0.9829 0.0082
-7.750 -0.4003 0.01590 0.01184 -0.1085 0.9793 0.0084
-7.500 -0.3685 0.01464 0.01041 -0.1100 0.9762 0.0086
-7.250 -0.3357 0.01390 0.00955 -0.1113 0.9734 0.0089
-7.000 -0.3033 0.01225 0.00770 -0.1131 0.9705 0.0094
-6.750 -0.2744 0.01123 0.00658 -0.1139 0.9653 0.0100
-6.500 -0.2455 0.01063 0.00591 -0.1143 0.9596 0.0105
-6.250 -0.2151 0.01010 0.00531 -0.1150 0.9551 0.0110
-6.000 -0.1881 0.00964 0.00479 -0.1149 0.9476 0.0116
-5.750 -0.1595 0.00925 0.00433 -0.1150 0.9415 0.0123
-5.500 -0.1317 0.00882 0.00381 -0.1151 0.9335 0.0133
-5.250 -0.1033 0.00834 0.00324 -0.1152 0.9261 0.0152
-5.000 -0.0754 0.00805 0.00289 -0.1151 0.9168 0.0169
-4.750 -0.0470 0.00772 0.00253 -0.1152 0.9082 0.0223
-4.500 -0.0189 0.00743 0.00232 -0.1152 0.8989 0.0434
-4.250 0.0093 0.00727 0.00215 -0.1153 0.8890 0.0539
-4.000 0.0375 0.00715 0.00198 -0.1152 0.8791 0.0602
-3.750 0.0656 0.00702 0.00181 -0.1152 0.8688 0.0676
-3.500 0.0939 0.00686 0.00164 -0.1152 0.8580 0.0802
-3.250 0.1227 0.00641 0.00142 -0.1157 0.8480 0.1545
-3.000 0.1512 0.00599 0.00125 -0.1161 0.8380 0.2466
-2.750 0.1797 0.00560 0.00110 -0.1164 0.8274 0.3340
-2.500 0.2081 0.00542 0.00106 -0.1166 0.8169 0.4049
-2.250 0.2363 0.00543 0.00107 -0.1165 0.8052 0.4325
-2.000 0.2643 0.00549 0.00108 -0.1163 0.7915 0.4494
-1.750 0.2923 0.00556 0.00109 -0.1162 0.7762 0.4614
-1.500 0.3203 0.00565 0.00108 -0.1160 0.7601 0.4696
-1.250 0.3482 0.00572 0.00110 -0.1158 0.7439 0.4756
-1.000 0.3762 0.00583 0.00111 -0.1157 0.7283 0.4820
-0.500 0.4316 0.00604 0.00117 -0.1154 0.6893 0.4945
-0.250 0.4592 0.00615 0.00119 -0.1152 0.6688 0.5002
0.000 0.4868 0.00625 0.00122 -0.1150 0.6500 0.5033
0.250 0.5146 0.00635 0.00125 -0.1149 0.6327 0.5064
0.500 0.5425 0.00645 0.00128 -0.1148 0.6174 0.5093
0.750 0.5704 0.00654 0.00132 -0.1148 0.6050 0.5120
1.000 0.5983 0.00659 0.00135 -0.1147 0.5928 0.5147
1.500 0.6542 0.00675 0.00146 -0.1146 0.5701 0.5200
1.750 0.6822 0.00683 0.00152 -0.1146 0.5602 0.5226
2.000 0.7100 0.00694 0.00159 -0.1145 0.5502 0.5251
2.250 0.7380 0.00698 0.00164 -0.1144 0.5398 0.5281
2.500 0.7659 0.00705 0.00171 -0.1144 0.5293 0.5303
2.750 0.7936 0.00714 0.00180 -0.1143 0.5182 0.5322
3.000 0.8213 0.00724 0.00189 -0.1142 0.5058 0.5342
3.250 0.8488 0.00736 0.00198 -0.1141 0.4896 0.5364
3.500 0.8757 0.00754 0.00210 -0.1139 0.4627 0.5384
3.750 0.9021 0.00778 0.00222 -0.1137 0.4269 0.5403
4.000 0.9273 0.00816 0.00242 -0.1133 0.3802 0.5427
4.250 0.9520 0.00862 0.00268 -0.1129 0.3329 0.5449
4.500 0.9767 0.00909 0.00296 -0.1124 0.2875 0.5474
4.750 1.0017 0.00953 0.00323 -0.1120 0.2490 0.5501
5.000 1.0274 0.00988 0.00347 -0.1117 0.2223 0.5527
5.250 1.0529 0.01023 0.00373 -0.1114 0.1969 0.5554
5.500 1.0779 0.01062 0.00404 -0.1110 0.1712 0.5585
5.750 1.1031 0.01101 0.00435 -0.1106 0.1503 0.5620
6.000 1.1277 0.01145 0.00468 -0.1102 0.1229 0.5658
6.250 1.1484 0.01239 0.00530 -0.1093 0.0665 0.5701
6.500 1.1675 0.01355 0.00616 -0.1080 0.0189 0.5755
6.750 1.1917 0.01403 0.00669 -0.1074 0.0142 0.5822
7.000 1.2157 0.01450 0.00722 -0.1068 0.0124 0.5918
7.250 1.2383 0.01517 0.00802 -0.1060 0.0107 0.6067
7.500 1.2626 0.01556 0.00855 -0.1054 0.0103 0.6384
7.750 1.2863 0.01598 0.00919 -0.1049 0.0097 0.7062
8.000 1.3079 0.01623 0.00986 -0.1039 0.0091 0.8548
8.250 1.3263 0.01662 0.01043 -0.1021 0.0085 1.0000
8.500 1.3459 0.01753 0.01140 -0.1009 0.0078 1.0000
8.750 1.3612 0.01886 0.01286 -0.0991 0.0073 1.0000
9.000 1.3824 0.01946 0.01352 -0.0981 0.0071 1.0000
9.250 1.4016 0.02023 0.01435 -0.0969 0.0068 1.0000
9.500 1.4195 0.02109 0.01528 -0.0955 0.0066 1.0000
9.750 1.4362 0.02200 0.01628 -0.0939 0.0063 1.0000
10.000 1.4515 0.02297 0.01733 -0.0922 0.0061 1.0000
10.250 1.4657 0.02395 0.01838 -0.0903 0.0059 1.0000
10.500 1.4767 0.02494 0.01944 -0.0880 0.0057 1.0000
10.750 1.4846 0.02597 0.02055 -0.0852 0.0056 1.0000
11.000 1.4909 0.02714 0.02178 -0.0824 0.0054 1.0000
11.250 1.4944 0.02861 0.02334 -0.0795 0.0053 1.0000
11.500 1.4937 0.03057 0.02541 -0.0765 0.0051 1.0000
11.750 1.4865 0.03347 0.02847 -0.0732 0.0050 1.0000
12.000 1.4773 0.03711 0.03231 -0.0703 0.0048 1.0000
12.250 1.4833 0.03864 0.03395 -0.0689 0.0048 1.0000
12.500 1.4873 0.04056 0.03600 -0.0676 0.0047 1.0000
12.750 1.4902 0.04270 0.03826 -0.0666 0.0046 1.0000
13.000 1.4908 0.04525 0.04094 -0.0657 0.0045 1.0000
13.250 1.4899 0.04811 0.04393 -0.0651 0.0044 1.0000
13.500 1.4878 0.05127 0.04723 -0.0648 0.0043 1.0000
13.750 1.4833 0.05493 0.05104 -0.0648 0.0043 1.0000
14.000 1.4769 0.05905 0.05531 -0.0653 0.0042 1.0000
14.250 1.4684 0.06371 0.06013 -0.0662 0.0042 1.0000
14.500 1.4584 0.06884 0.06542 -0.0676 0.0041 1.0000
14.750 1.4472 0.07444 0.07118 -0.0696 0.0041 1.0000
15.000 1.4343 0.08067 0.07758 -0.0721 0.0041 1.0000
15.250 1.4197 0.08750 0.08458 -0.0751 0.0041 1.0000
15.500 1.4047 0.09480 0.09205 -0.0788 0.0041 1.0000
15.750 1.3879 0.10287 0.10029 -0.0831 0.0041 1.0000
16.000 1.3693 0.11176 0.10935 -0.0881 0.0041 1.0000
16.250 1.3523 0.12069 0.11845 -0.0934 0.0041 1.0000
16.500 1.3311 0.13109 0.12902 -0.0998 0.0041 1.0000
16.750 1.3114 0.14149 0.13958 -0.1065 0.0041 1.0000
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