FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 100,000 Max Cl/Cd: 39.76 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61184-il-100000.txt Download as CSV file: xf-fx61184-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-184 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2236 0.11231 0.10820 -0.0668 0.9719 0.1787
-11.250 -0.3477 0.07872 0.07463 -0.0837 0.9729 0.0843
-11.000 -0.4123 0.06731 0.06306 -0.0898 0.9679 0.0809
-10.750 -0.5229 0.06112 0.05627 -0.0944 0.9585 0.0766
-10.500 -0.5899 0.06839 0.06343 -0.0888 0.9660 0.0746
-10.250 -0.5932 0.06353 0.05838 -0.0912 0.9599 0.0726
-10.000 -0.6070 0.06018 0.05478 -0.0910 0.9505 0.0716
-9.750 -0.6073 0.05518 0.04932 -0.0931 0.9448 0.0689
-9.500 -0.6292 0.05213 0.04567 -0.0897 0.9349 0.0662
-9.250 -0.6148 0.04961 0.04242 -0.0906 0.9302 0.0642
-9.000 -0.6115 0.04789 0.04042 -0.0880 0.9231 0.0639
-8.750 -0.5936 0.04514 0.03733 -0.0880 0.9184 0.0640
-8.500 -0.5647 0.04127 0.03334 -0.0897 0.9158 0.0664
-8.250 -0.5393 0.03947 0.03143 -0.0901 0.9121 0.0687
-8.000 -0.5291 0.03834 0.03014 -0.0877 0.9056 0.0697
-7.750 -0.4979 0.03667 0.02828 -0.0882 0.9021 0.0716
-7.500 -0.4602 0.03536 0.02668 -0.0900 0.8995 0.0759
-7.250 -0.4425 0.03419 0.02564 -0.0879 0.8948 0.0795
-7.000 -0.4275 0.03358 0.02509 -0.0857 0.8892 0.0830
-6.750 -0.3954 0.03275 0.02418 -0.0859 0.8857 0.0896
-6.500 -0.3613 0.03162 0.02329 -0.0867 0.8832 0.1019
-6.250 -0.3759 0.03177 0.02347 -0.0806 0.8747 0.1059
-6.000 -0.3583 0.03078 0.02266 -0.0800 0.8700 0.1231
-5.750 -0.3378 0.02750 0.02048 -0.0833 0.8667 0.2454
-5.500 -0.3569 0.02829 0.02288 -0.0750 0.8580 0.4880
-5.250 -0.3248 0.03113 0.02547 -0.0728 0.8534 0.5579
-5.000 -0.2875 0.03445 0.02868 -0.0689 0.8506 0.5783
-4.750 -0.3015 0.03530 0.02948 -0.0629 0.8416 0.5899
-4.500 -0.2748 0.03748 0.03155 -0.0592 0.8372 0.6055
-4.250 -0.2344 0.04123 0.03524 -0.0534 0.8349 0.6240
-4.000 -0.2590 0.04158 0.03558 -0.0470 0.8255 0.6369
-3.750 -0.2255 0.04445 0.03841 -0.0409 0.8217 0.6556
-3.500 -0.1847 0.04467 0.03843 -0.0421 0.8189 0.6701
-3.000 -0.1850 0.04502 0.03867 -0.0343 0.8051 0.6874
-2.750 -0.1428 0.04476 0.03823 -0.0365 0.8023 0.6970
-2.500 -0.1731 0.04511 0.03861 -0.0290 0.7926 0.7041
-2.250 -0.1436 0.04484 0.03820 -0.0299 0.7883 0.7129
-2.000 -0.1270 0.04475 0.03803 -0.0287 0.7831 0.7200
-1.750 -0.1316 0.04494 0.03819 -0.0251 0.7755 0.7266
-1.500 -0.0977 0.04446 0.03756 -0.0273 0.7714 0.7340
-1.250 -0.0972 0.04476 0.03784 -0.0238 0.7643 0.7392
-1.000 -0.0800 0.04467 0.03766 -0.0244 0.7584 0.7456
-0.750 -0.0439 0.04433 0.03720 -0.0260 0.7547 0.7507
-0.500 -0.0478 0.04476 0.03762 -0.0227 0.7464 0.7551
-0.250 -0.0210 0.04470 0.03747 -0.0242 0.7411 0.7604
0.000 0.0232 0.04433 0.03698 -0.0276 0.7378 0.7649
0.250 0.0136 0.04499 0.03765 -0.0238 0.7285 0.7685
0.500 0.0448 0.04492 0.03752 -0.0251 0.7238 0.7724
0.750 0.0932 0.04461 0.03709 -0.0288 0.7209 0.7765
1.000 0.0907 0.04552 0.03799 -0.0279 0.7104 0.7801
1.250 0.1223 0.04536 0.03780 -0.0285 0.7066 0.7829
1.500 0.1300 0.04606 0.03849 -0.0274 0.6986 0.7860
1.750 0.1575 0.04625 0.03864 -0.0286 0.6927 0.7893
2.000 0.2041 0.04603 0.03836 -0.0320 0.6895 0.7922
2.250 0.2106 0.04728 0.03960 -0.0326 0.6795 0.7951
2.500 0.2425 0.04709 0.03940 -0.0331 0.6751 0.7977
2.750 0.2865 0.04672 0.03901 -0.0351 0.6727 0.8003
3.000 0.2800 0.04827 0.04060 -0.0336 0.6611 0.8027
3.250 0.3247 0.04796 0.04027 -0.0361 0.6579 0.8059
3.500 0.3296 0.04943 0.04175 -0.0361 0.6472 0.8085
3.750 0.3755 0.04926 0.04158 -0.0394 0.6433 0.8108
4.000 0.3788 0.05053 0.04289 -0.0382 0.6338 0.8130
4.250 0.4105 0.05048 0.04287 -0.0389 0.6288 0.8158
4.500 0.4559 0.04992 0.04233 -0.0408 0.6262 0.8187
4.750 0.4547 0.05185 0.04431 -0.0403 0.6143 0.8210
5.000 0.5025 0.05129 0.04377 -0.0429 0.6114 0.8235
5.250 0.5082 0.05313 0.04566 -0.0432 0.5996 0.8261
5.500 0.5504 0.05228 0.04487 -0.0442 0.5963 0.8290
5.750 0.5516 0.05402 0.04667 -0.0433 0.5847 0.8315
6.000 0.5949 0.05324 0.04595 -0.0447 0.5812 0.8342
6.250 0.6465 0.05197 0.04474 -0.0467 0.5793 0.8371
6.500 0.6459 0.05425 0.04708 -0.0464 0.5661 0.8397
6.750 0.6994 0.05259 0.04551 -0.0483 0.5641 0.8432
7.000 0.6970 0.05459 0.04759 -0.0470 0.5508 0.8460
7.250 0.7502 0.05239 0.04548 -0.0481 0.5489 0.8497
7.500 0.7523 0.05447 0.04766 -0.0477 0.5355 0.8525
7.750 0.7924 0.05363 0.04691 -0.0489 0.5307 0.8558
8.000 0.8615 0.04977 0.04319 -0.0505 0.5326 0.8598
8.250 0.8362 0.05416 0.04765 -0.0486 0.5138 0.8628
8.500 0.9071 0.04969 0.04333 -0.0499 0.5161 0.8682
8.750 0.9763 0.04550 0.03930 -0.0516 0.5165 0.8730
9.000 1.0520 0.04050 0.03446 -0.0532 0.5167 0.8777
9.250 1.0252 0.04446 0.03850 -0.0504 0.4986 0.8817
9.500 1.1298 0.03762 0.03185 -0.0543 0.4989 0.8878
9.750 1.1702 0.03579 0.03015 -0.0544 0.4889 0.8936
10.000 1.1955 0.03527 0.02974 -0.0538 0.4764 0.9003
10.250 1.2354 0.03365 0.02820 -0.0541 0.4629 0.9070
10.500 1.2618 0.03287 0.02747 -0.0534 0.4470 0.9148
10.750 1.2783 0.03267 0.02733 -0.0519 0.4303 0.9235
11.000 1.2913 0.03266 0.02734 -0.0501 0.4124 0.9353
11.250 1.3028 0.03277 0.02745 -0.0483 0.3938 0.9543
11.500 1.3082 0.03380 0.02851 -0.0473 0.3734 1.0000
11.750 1.3141 0.03549 0.03020 -0.0472 0.3517 1.0000
12.000 1.3276 0.03675 0.03134 -0.0474 0.3297 1.0000
12.250 1.3282 0.03910 0.03372 -0.0471 0.3089 1.0000
12.500 1.3317 0.04130 0.03586 -0.0471 0.2881 1.0000
12.750 1.3364 0.04346 0.03787 -0.0470 0.2677 1.0000
13.000 1.3340 0.04632 0.04074 -0.0468 0.2481 1.0000
13.250 1.3320 0.04922 0.04358 -0.0467 0.2289 1.0000
13.500 1.3300 0.05220 0.04645 -0.0467 0.2102 1.0000
13.750 1.3270 0.05537 0.04948 -0.0466 0.1918 1.0000
14.000 1.3217 0.05896 0.05303 -0.0467 0.1740 1.0000
14.250 1.3170 0.06257 0.05658 -0.0468 0.1571 1.0000
14.500 1.3138 0.06614 0.06008 -0.0470 0.1420 1.0000
14.750 1.3129 0.06955 0.06341 -0.0472 0.1287 1.0000
15.000 1.3157 0.07258 0.06634 -0.0474 0.1175 1.0000
15.250 1.3253 0.07480 0.06835 -0.0473 0.1074 1.0000
15.500 1.3275 0.07813 0.07188 -0.0477 0.1003 1.0000
15.750 1.3428 0.07986 0.07348 -0.0474 0.0932 1.0000
16.000 1.3454 0.08317 0.07699 -0.0479 0.0883 1.0000
16.250 1.3733 0.08371 0.07727 -0.0472 0.0820 1.0000
16.500 1.3719 0.08755 0.08147 -0.0478 0.0795 1.0000
16.750 1.3728 0.09118 0.08532 -0.0484 0.0765 1.0000
17.000 1.3808 0.09384 0.08802 -0.0488 0.0731 1.0000
17.250 1.3976 0.09606 0.09024 -0.0487 0.0696 1.0000
17.500 1.3853 0.10123 0.09574 -0.0501 0.0683 1.0000
17.750 1.3724 0.10662 0.10143 -0.0519 0.0667 1.0000
18.000 1.3614 0.11182 0.10685 -0.0540 0.0648 1.0000
18.250 1.3833 0.11231 0.10703 -0.0539 0.0592 1.0000
18.500 1.3618 0.11896 0.11401 -0.0571 0.0586 1.0000
18.750 1.3392 0.12623 0.12161 -0.0608 0.0580 1.0000
19.000 1.3150 0.13421 0.12989 -0.0653 0.0575 1.0000
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