FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 100,000 Max Cl/Cd: 60.41 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w108-il-100000-n5.txt Download as CSV file: xf-fx83w108-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-108
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3862 0.09814 0.09307 -0.0472 1.0000 0.0367
-9.250 -0.3966 0.09567 0.09068 -0.0457 1.0000 0.0365
-9.000 -0.4079 0.09305 0.08815 -0.0445 0.9996 0.0363
-8.750 -0.4003 0.08714 0.08225 -0.0505 0.9938 0.0362
-8.500 -0.3977 0.08039 0.07551 -0.0574 0.9865 0.0364
-8.250 -0.4013 0.07260 0.06774 -0.0655 0.9762 0.0365
-8.000 -0.4091 0.05745 0.05240 -0.0853 0.9610 0.0361
-7.750 -0.4061 0.04796 0.04237 -0.0971 0.9499 0.0361
-7.500 -0.3897 0.04116 0.03484 -0.1041 0.9431 0.0368
-7.250 -0.3722 0.03704 0.03012 -0.1065 0.9359 0.0372
-7.000 -0.3473 0.03352 0.02591 -0.1089 0.9310 0.0379
-6.750 -0.3176 0.03104 0.02320 -0.1110 0.9281 0.0390
-6.500 -0.2941 0.02956 0.02151 -0.1114 0.9224 0.0403
-6.250 -0.2665 0.02827 0.02000 -0.1123 0.9177 0.0430
-6.000 -0.2345 0.02670 0.01804 -0.1137 0.9147 0.0458
-5.750 -0.2012 0.02507 0.01617 -0.1153 0.9125 0.0479
-5.500 -0.1795 0.02422 0.01528 -0.1147 0.9061 0.0506
-5.250 -0.1498 0.02337 0.01430 -0.1154 0.9020 0.0547
-5.000 -0.1169 0.02236 0.01312 -0.1166 0.8992 0.0586
-4.750 -0.0833 0.02146 0.01222 -0.1181 0.8969 0.0640
-4.500 -0.0625 0.02102 0.01167 -0.1170 0.8901 0.0696
-4.250 -0.0335 0.02030 0.01095 -0.1175 0.8861 0.0761
-4.000 -0.0009 0.01965 0.01024 -0.1187 0.8831 0.0874
-3.750 0.0302 0.01904 0.00963 -0.1196 0.8800 0.1022
-3.500 0.0515 0.01863 0.00929 -0.1187 0.8734 0.1265
-3.250 0.0813 0.01795 0.00889 -0.1195 0.8697 0.1876
-3.000 0.1138 0.01747 0.00869 -0.1207 0.8669 0.2712
-2.750 0.1377 0.01743 0.00875 -0.1200 0.8615 0.3248
-2.500 0.1638 0.01743 0.00876 -0.1197 0.8565 0.3651
-2.250 0.1950 0.01736 0.00868 -0.1203 0.8531 0.4009
-2.000 0.2284 0.01727 0.00859 -0.1213 0.8506 0.4374
-1.750 0.2475 0.01740 0.00876 -0.1196 0.8437 0.4611
-1.500 0.2758 0.01736 0.00870 -0.1196 0.8395 0.4845
-1.250 0.3076 0.01724 0.00858 -0.1203 0.8365 0.5050
-1.000 0.3336 0.01724 0.00860 -0.1198 0.8319 0.5233
-0.750 0.3564 0.01730 0.00868 -0.1189 0.8260 0.5415
-0.500 0.3871 0.01722 0.00862 -0.1193 0.8225 0.5633
-0.250 0.4206 0.01708 0.00852 -0.1202 0.8198 0.5876
0.000 0.4398 0.01725 0.00876 -0.1186 0.8130 0.6125
0.250 0.4674 0.01720 0.00881 -0.1184 0.8085 0.6439
0.500 0.4987 0.01702 0.00876 -0.1188 0.8053 0.6860
0.750 0.5210 0.01700 0.00894 -0.1175 0.7998 0.7436
1.000 0.5499 0.01678 0.00903 -0.1173 0.7946 0.8613
1.250 0.5909 0.01669 0.00893 -0.1200 0.7910 1.0000
1.500 0.6245 0.01672 0.00889 -0.1210 0.7877 1.0000
1.750 0.6417 0.01714 0.00929 -0.1192 0.7797 1.0000
2.000 0.6723 0.01723 0.00934 -0.1197 0.7755 1.0000
2.250 0.7024 0.01733 0.00943 -0.1200 0.7712 1.0000
2.500 0.7220 0.01769 0.00980 -0.1186 0.7637 1.0000
2.750 0.7541 0.01770 0.00981 -0.1192 0.7592 1.0000
3.000 0.7764 0.01797 0.01013 -0.1182 0.7520 1.0000
3.250 0.8040 0.01807 0.01025 -0.1180 0.7456 1.0000
3.500 0.8331 0.01809 0.01030 -0.1179 0.7390 1.0000
3.750 0.8582 0.01813 0.01039 -0.1171 0.7297 1.0000
4.000 0.8827 0.01815 0.01047 -0.1161 0.7194 1.0000
4.250 0.9134 0.01790 0.01025 -0.1159 0.7088 1.0000
4.500 0.9412 0.01766 0.01004 -0.1152 0.6950 1.0000
4.750 0.9621 0.01760 0.01003 -0.1133 0.6779 1.0000
5.000 0.9823 0.01758 0.01007 -0.1114 0.6595 1.0000
5.250 1.0040 0.01757 0.01011 -0.1098 0.6403 1.0000
5.500 1.0280 0.01751 0.01006 -0.1085 0.6193 1.0000
5.750 1.0458 0.01762 0.01021 -0.1062 0.5917 1.0000
6.000 1.0656 0.01771 0.01025 -0.1041 0.5565 1.0000
6.250 1.0837 0.01794 0.01032 -0.1018 0.5094 1.0000
6.500 1.0963 0.01850 0.01050 -0.0987 0.4411 1.0000
6.750 1.0999 0.01949 0.01104 -0.0943 0.3661 1.0000
7.000 1.0999 0.02072 0.01182 -0.0897 0.3009 1.0000
7.250 1.1021 0.02201 0.01276 -0.0858 0.2461 1.0000
7.500 1.1070 0.02327 0.01375 -0.0825 0.2023 1.0000
7.750 1.1141 0.02448 0.01476 -0.0796 0.1684 1.0000
8.000 1.1222 0.02569 0.01581 -0.0770 0.1418 1.0000
8.250 1.1311 0.02689 0.01693 -0.0746 0.1227 1.0000
8.500 1.1404 0.02810 0.01809 -0.0723 0.1084 1.0000
8.750 1.1502 0.02931 0.01929 -0.0702 0.0974 1.0000
9.000 1.1590 0.03062 0.02058 -0.0680 0.0884 1.0000
9.250 1.1688 0.03191 0.02188 -0.0661 0.0809 1.0000
9.500 1.1782 0.03327 0.02330 -0.0641 0.0750 1.0000
9.750 1.1886 0.03459 0.02467 -0.0623 0.0695 1.0000
10.000 1.1971 0.03611 0.02618 -0.0605 0.0652 1.0000
10.250 1.2088 0.03745 0.02765 -0.0589 0.0610 1.0000
10.500 1.2193 0.03887 0.02912 -0.0574 0.0575 1.0000
10.750 1.2279 0.04058 0.03080 -0.0558 0.0548 1.0000
11.000 1.2412 0.04199 0.03241 -0.0545 0.0519 1.0000
11.250 1.2540 0.04355 0.03409 -0.0531 0.0494 1.0000
11.500 1.2659 0.04515 0.03578 -0.0519 0.0474 1.0000
11.750 1.2768 0.04685 0.03751 -0.0507 0.0455 1.0000
12.000 1.2894 0.04869 0.03945 -0.0495 0.0436 1.0000
12.250 1.3014 0.05052 0.04152 -0.0484 0.0419 1.0000
12.500 1.3117 0.05250 0.04372 -0.0472 0.0402 1.0000
12.750 1.3217 0.05458 0.04597 -0.0461 0.0390 1.0000
13.000 1.3297 0.05677 0.04830 -0.0450 0.0379 1.0000
13.250 1.3371 0.05906 0.05072 -0.0440 0.0371 1.0000
13.500 1.3442 0.06152 0.05326 -0.0430 0.0362 1.0000
13.750 1.3461 0.06457 0.05653 -0.0420 0.0354 1.0000
14.000 1.3414 0.06797 0.06028 -0.0410 0.0347 1.0000
14.250 1.3340 0.07173 0.06436 -0.0402 0.0341 1.0000
14.500 1.3246 0.07574 0.06867 -0.0398 0.0335 1.0000
14.750 1.3125 0.08023 0.07344 -0.0397 0.0330 1.0000
15.000 1.2981 0.08511 0.07860 -0.0402 0.0326 1.0000
15.250 1.2814 0.09060 0.08437 -0.0413 0.0324 1.0000
15.500 1.2613 0.09692 0.09095 -0.0432 0.0322 1.0000
15.750 1.2380 0.10419 0.09849 -0.0462 0.0322 1.0000
16.000 1.2105 0.11288 0.10745 -0.0507 0.0323 1.0000
16.250 1.1753 0.12423 0.11906 -0.0577 0.0326 1.0000
16.500 1.1245 0.14163 0.13671 -0.0694 0.0334 1.0000
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Polar data table (+)
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