FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-150 (fx84w150-il) Reynolds number: 200,000 Max Cl/Cd: 77.34 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w150-il-200000.txt Download as CSV file: xf-fx84w150-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-150
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1975 0.10660 0.10309 -0.0782 0.9734 0.0653
-11.000 -0.2095 0.09966 0.09617 -0.0909 0.9662 0.0690
-10.750 -0.1997 0.09373 0.09024 -0.0946 0.9614 0.0700
-10.500 -0.1655 0.09228 0.08873 -0.0933 0.9584 0.0722
-10.250 -0.1513 0.08922 0.08565 -0.0955 0.9506 0.0748
-10.000 -0.1485 0.08452 0.08093 -0.1009 0.9426 0.0787
-9.750 -0.2082 0.07465 0.07106 -0.1161 0.9216 0.0808
-9.500 -0.1939 0.07089 0.06734 -0.1138 0.9165 0.0820
-9.250 -0.3361 0.04755 0.04322 -0.1198 0.8944 0.0496
-9.000 -0.3427 0.04412 0.03959 -0.1182 0.8859 0.0490
-8.750 -0.3495 0.04041 0.03553 -0.1162 0.8789 0.0486
-8.500 -0.3519 0.03681 0.03151 -0.1143 0.8709 0.0485
-8.250 -0.3480 0.03371 0.02790 -0.1121 0.8658 0.0490
-8.000 -0.3386 0.03191 0.02555 -0.1103 0.8583 0.0502
-7.750 -0.3230 0.02941 0.02292 -0.1094 0.8531 0.0518
-7.500 -0.3022 0.02822 0.02161 -0.1085 0.8494 0.0534
-7.250 -0.2827 0.02699 0.02018 -0.1077 0.8429 0.0551
-7.000 -0.2618 0.02574 0.01862 -0.1067 0.8376 0.0574
-6.750 -0.2398 0.02433 0.01689 -0.1058 0.8339 0.0600
-6.500 -0.2166 0.02348 0.01604 -0.1054 0.8290 0.0627
-6.250 -0.1930 0.02276 0.01521 -0.1048 0.8233 0.0656
-6.000 -0.1678 0.02218 0.01438 -0.1041 0.8191 0.0691
-5.750 -0.1429 0.02095 0.01314 -0.1037 0.8160 0.0730
-5.500 -0.1193 0.02052 0.01269 -0.1033 0.8096 0.0770
-5.250 -0.0939 0.01991 0.01194 -0.1027 0.8049 0.0818
-5.000 -0.0684 0.01915 0.01122 -0.1023 0.8014 0.0873
-4.750 -0.0428 0.01884 0.01079 -0.1019 0.7969 0.0935
-4.500 -0.0197 0.01822 0.01028 -0.1013 0.7910 0.1009
-4.250 0.0060 0.01769 0.00970 -0.1008 0.7869 0.1101
-4.000 0.0327 0.01724 0.00922 -0.1005 0.7837 0.1219
-3.750 0.0555 0.01691 0.00898 -0.0999 0.7775 0.1361
-3.500 0.0803 0.01647 0.00862 -0.0995 0.7726 0.1560
-3.250 0.1063 0.01597 0.00821 -0.0992 0.7691 0.1853
-3.000 0.1310 0.01548 0.00793 -0.0989 0.7653 0.2306
-2.750 0.1525 0.01501 0.00786 -0.0983 0.7589 0.3103
-2.500 0.1740 0.01418 0.00768 -0.0974 0.7547 0.4705
-2.250 0.1963 0.01365 0.00768 -0.0959 0.7516 0.6275
-2.000 0.2172 0.01371 0.00798 -0.0942 0.7460 0.7048
-1.750 0.2401 0.01378 0.00811 -0.0927 0.7409 0.7531
-1.500 0.2650 0.01378 0.00810 -0.0914 0.7372 0.7887
-1.250 0.2905 0.01381 0.00806 -0.0901 0.7344 0.8172
-1.000 0.3086 0.01409 0.00840 -0.0880 0.7276 0.8403
-0.750 0.3312 0.01414 0.00840 -0.0863 0.7232 0.8621
-0.500 0.3550 0.01412 0.00830 -0.0847 0.7199 0.8814
-0.250 0.3746 0.01427 0.00845 -0.0826 0.7147 0.8991
0.000 0.3963 0.01436 0.00852 -0.0809 0.7094 0.9165
0.250 0.4259 0.01430 0.00840 -0.0806 0.7056 0.9328
0.500 0.4656 0.01425 0.00822 -0.0823 0.7027 0.9475
0.750 0.5157 0.01446 0.00843 -0.0867 0.6965 0.9627
1.000 0.5703 0.01443 0.00833 -0.0920 0.6919 0.9723
1.250 0.6195 0.01428 0.00807 -0.0963 0.6882 0.9779
1.500 0.6616 0.01431 0.00807 -0.0996 0.6832 0.9849
1.750 0.7041 0.01431 0.00806 -0.1030 0.6775 0.9914
2.000 0.7475 0.01419 0.00787 -0.1065 0.6733 0.9971
2.250 0.7792 0.01418 0.00780 -0.1077 0.6690 1.0000
2.500 0.7927 0.01438 0.00804 -0.1057 0.6625 1.0000
2.750 0.8120 0.01440 0.00804 -0.1044 0.6580 1.0000
3.000 0.8347 0.01440 0.00796 -0.1036 0.6544 1.0000
3.250 0.8435 0.01470 0.00834 -0.1007 0.6473 1.0000
3.500 0.8625 0.01474 0.00835 -0.0993 0.6425 1.0000
3.750 0.8878 0.01474 0.00827 -0.0988 0.6389 1.0000
4.000 0.8975 0.01508 0.00868 -0.0960 0.6316 1.0000
4.250 0.9215 0.01512 0.00870 -0.0954 0.6265 1.0000
4.500 0.9498 0.01517 0.00869 -0.0955 0.6223 1.0000
4.750 0.9678 0.01547 0.00908 -0.0942 0.6150 1.0000
5.000 0.9958 0.01552 0.00909 -0.0943 0.6100 1.0000
5.250 1.0222 0.01568 0.00926 -0.0942 0.6048 1.0000
5.500 1.0441 0.01593 0.00957 -0.0934 0.5980 1.0000
5.750 1.0739 0.01596 0.00957 -0.0938 0.5931 1.0000
6.000 1.0962 0.01621 0.00989 -0.0931 0.5861 1.0000
6.250 1.1224 0.01626 0.00995 -0.0929 0.5792 1.0000
6.500 1.1487 0.01637 0.01007 -0.0927 0.5726 1.0000
6.750 1.1715 0.01656 0.01033 -0.0920 0.5651 1.0000
7.000 1.2029 0.01659 0.01031 -0.0927 0.5597 1.0000
7.250 1.2202 0.01690 0.01076 -0.0911 0.5511 1.0000
7.500 1.2507 0.01692 0.01074 -0.0916 0.5447 1.0000
7.750 1.2675 0.01710 0.01103 -0.0899 0.5340 1.0000
8.000 1.2872 0.01707 0.01101 -0.0884 0.5213 1.0000
8.250 1.3063 0.01708 0.01101 -0.0869 0.5083 1.0000
8.500 1.3271 0.01716 0.01108 -0.0857 0.4966 1.0000
8.750 1.3396 0.01742 0.01142 -0.0833 0.4841 1.0000
9.000 1.3520 0.01771 0.01176 -0.0808 0.4712 1.0000
9.250 1.3625 0.01801 0.01209 -0.0781 0.4585 1.0000
9.500 1.3713 0.01840 0.01250 -0.0751 0.4456 1.0000
9.750 1.3789 0.01889 0.01299 -0.0722 0.4317 1.0000
10.000 1.3849 0.01951 0.01362 -0.0692 0.4169 1.0000
10.250 1.3892 0.02027 0.01440 -0.0662 0.4008 1.0000
10.500 1.3919 0.02119 0.01532 -0.0631 0.3829 1.0000
10.750 1.3930 0.02230 0.01640 -0.0602 0.3630 1.0000
11.000 1.3920 0.02363 0.01767 -0.0572 0.3420 1.0000
11.250 1.3897 0.02519 0.01919 -0.0543 0.3177 1.0000
11.500 1.3835 0.02711 0.02101 -0.0514 0.2911 1.0000
11.750 1.3747 0.02939 0.02315 -0.0486 0.2637 1.0000
12.000 1.3640 0.03199 0.02561 -0.0459 0.2344 1.0000
12.250 1.3507 0.03498 0.02843 -0.0435 0.2047 1.0000
12.500 1.3372 0.03826 0.03155 -0.0415 0.1753 1.0000
12.750 1.3231 0.04183 0.03494 -0.0397 0.1463 1.0000
13.000 1.3096 0.04557 0.03852 -0.0383 0.1228 1.0000
13.250 1.2992 0.04919 0.04203 -0.0372 0.1054 1.0000
13.500 1.2910 0.05274 0.04552 -0.0364 0.0935 1.0000
13.750 1.2834 0.05636 0.04908 -0.0358 0.0846 1.0000
14.000 1.2821 0.05937 0.05214 -0.0354 0.0773 1.0000
14.250 1.2766 0.06289 0.05560 -0.0350 0.0721 1.0000
14.500 1.2794 0.06558 0.05838 -0.0349 0.0672 1.0000
14.750 1.2778 0.06877 0.06153 -0.0347 0.0632 1.0000
15.000 1.2813 0.07137 0.06420 -0.0345 0.0598 1.0000
15.250 1.2855 0.07397 0.06686 -0.0345 0.0567 1.0000
15.500 1.2889 0.07657 0.06944 -0.0343 0.0539 1.0000
15.750 1.2958 0.07873 0.07165 -0.0340 0.0514 1.0000
16.000 1.3018 0.08119 0.07421 -0.0341 0.0490 1.0000
16.250 1.3089 0.08343 0.07649 -0.0341 0.0471 1.0000
16.500 1.3214 0.08464 0.07759 -0.0334 0.0447 1.0000
16.750 1.3287 0.08701 0.08011 -0.0334 0.0433 1.0000
17.000 1.3342 0.08961 0.08286 -0.0337 0.0416 1.0000
17.250 1.3413 0.09197 0.08529 -0.0340 0.0401 1.0000
17.500 1.3509 0.09388 0.08721 -0.0340 0.0387 1.0000
17.750 1.3687 0.09461 0.08792 -0.0330 0.0371 1.0000
18.000 1.3701 0.09792 0.09145 -0.0337 0.0363 1.0000
18.250 1.3714 0.10124 0.09497 -0.0345 0.0354 1.0000
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