FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 200,000 Max Cl/Cd: 70.62 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61140-il-200000-n5.txt Download as CSV file: xf-fx61140-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4289 0.08911 0.08565 -0.0434 1.0000 0.0089
-10.000 -0.4394 0.08177 0.07835 -0.0471 1.0000 0.0087
-9.750 -0.4576 0.07249 0.06906 -0.0531 1.0000 0.0085
-9.500 -0.4798 0.06587 0.06238 -0.0566 1.0000 0.0083
-9.250 -0.5024 0.06103 0.05747 -0.0579 1.0000 0.0081
-9.000 -0.5252 0.05745 0.05384 -0.0571 1.0000 0.0080
-8.750 -0.5520 0.05486 0.05119 -0.0542 1.0000 0.0081
-8.500 -0.5722 0.05195 0.04820 -0.0522 1.0000 0.0080
-8.250 -0.5690 0.04604 0.04192 -0.0563 0.9951 0.0079
-8.000 -0.5536 0.04001 0.03538 -0.0605 0.9875 0.0079
-7.750 -0.5328 0.03526 0.03013 -0.0633 0.9800 0.0080
-7.500 -0.5063 0.03128 0.02564 -0.0658 0.9735 0.0083
-7.250 -0.4810 0.02825 0.02218 -0.0668 0.9651 0.0086
-7.000 -0.4496 0.02603 0.01953 -0.0683 0.9588 0.0098
-6.750 -0.4224 0.02410 0.01737 -0.0691 0.9495 0.0107
-6.500 -0.3932 0.02287 0.01604 -0.0701 0.9403 0.0116
-6.250 -0.3609 0.02133 0.01430 -0.0712 0.9328 0.0124
-6.000 -0.3311 0.01998 0.01283 -0.0718 0.9219 0.0131
-5.750 -0.2980 0.01873 0.01145 -0.0730 0.9117 0.0142
-5.500 -0.2610 0.01741 0.01005 -0.0755 0.9015 0.0162
-5.250 -0.2185 0.01645 0.00904 -0.0791 0.8902 0.0194
-5.000 -0.1733 0.01545 0.00785 -0.0833 0.8762 0.0221
-4.750 -0.1277 0.01448 0.00678 -0.0877 0.8587 0.0297
-4.500 -0.0830 0.01371 0.00590 -0.0918 0.8383 0.0446
-4.250 -0.0411 0.01243 0.00504 -0.0963 0.8162 0.1518
-4.000 0.0019 0.01059 0.00432 -0.1021 0.7931 0.4436
-3.750 0.0324 0.01054 0.00457 -0.1024 0.7710 0.5567
-3.500 0.0597 0.01095 0.00495 -0.1016 0.7503 0.6070
-3.250 0.0863 0.01140 0.00525 -0.1007 0.7311 0.6310
-3.000 0.1147 0.01159 0.00523 -0.1006 0.7129 0.6418
-2.750 0.1417 0.01178 0.00525 -0.1002 0.6963 0.6481
-2.500 0.1706 0.01188 0.00516 -0.1005 0.6809 0.6553
-2.250 0.1971 0.01204 0.00518 -0.1000 0.6667 0.6594
-2.000 0.2256 0.01213 0.00511 -0.1002 0.6534 0.6650
-1.750 0.2540 0.01222 0.00505 -0.1003 0.6409 0.6699
-1.500 0.2807 0.01236 0.00508 -0.1000 0.6295 0.6733
-1.250 0.3087 0.01245 0.00505 -0.1000 0.6184 0.6776
-1.000 0.3389 0.01249 0.00496 -0.1008 0.6076 0.6829
-0.750 0.3653 0.01262 0.00501 -0.1004 0.5977 0.6855
-0.500 0.3924 0.01274 0.00505 -0.1002 0.5884 0.6887
-0.250 0.4210 0.01282 0.00505 -0.1005 0.5788 0.6929
0.000 0.4508 0.01289 0.00502 -0.1011 0.5700 0.6974
0.250 0.4774 0.01300 0.00509 -0.1008 0.5616 0.6997
0.500 0.5047 0.01310 0.00516 -0.1007 0.5533 0.7025
0.750 0.5329 0.01321 0.00520 -0.1009 0.5457 0.7057
1.000 0.5627 0.01327 0.00522 -0.1016 0.5379 0.7097
1.250 0.5908 0.01339 0.00529 -0.1017 0.5311 0.7125
1.500 0.6179 0.01349 0.00540 -0.1016 0.5240 0.7147
1.750 0.6453 0.01361 0.00550 -0.1016 0.5173 0.7173
2.000 0.6737 0.01371 0.00562 -0.1019 0.5104 0.7204
2.250 0.7031 0.01383 0.00569 -0.1025 0.5038 0.7241
2.500 0.7311 0.01394 0.00582 -0.1026 0.4971 0.7267
2.750 0.7578 0.01407 0.00597 -0.1024 0.4903 0.7289
3.000 0.7851 0.01421 0.00614 -0.1024 0.4841 0.7313
3.250 0.8130 0.01434 0.00630 -0.1026 0.4773 0.7342
3.500 0.8417 0.01449 0.00645 -0.1030 0.4713 0.7375
3.750 0.8703 0.01461 0.00665 -0.1034 0.4644 0.7402
4.000 0.8968 0.01478 0.00684 -0.1032 0.4588 0.7421
4.250 0.9238 0.01492 0.00708 -0.1032 0.4524 0.7443
4.500 0.9509 0.01510 0.00730 -0.1032 0.4461 0.7469
4.750 0.9787 0.01526 0.00756 -0.1034 0.4397 0.7497
5.000 1.0070 0.01544 0.00779 -0.1037 0.4330 0.7526
5.250 1.0340 0.01563 0.00805 -0.1037 0.4261 0.7549
5.500 1.0599 0.01581 0.00833 -0.1034 0.4188 0.7569
5.750 1.0862 0.01601 0.00865 -0.1033 0.4121 0.7592
6.000 1.1125 0.01621 0.00895 -0.1032 0.4041 0.7616
6.250 1.1387 0.01641 0.00924 -0.1031 0.3936 0.7645
6.500 1.1647 0.01663 0.00951 -0.1030 0.3803 0.7674
6.750 1.1877 0.01684 0.00977 -0.1022 0.3621 0.7694
7.000 1.2097 0.01713 0.01008 -0.1013 0.3404 0.7716
7.250 1.2310 0.01751 0.01047 -0.1004 0.3151 0.7740
7.500 1.2504 0.01807 0.01093 -0.0993 0.2783 0.7767
7.750 1.2648 0.01909 0.01164 -0.0977 0.2199 0.7793
8.000 1.2739 0.02066 0.01276 -0.0955 0.1495 0.7820
8.250 1.2837 0.02200 0.01390 -0.0932 0.1071 0.7841
8.500 1.2936 0.02328 0.01505 -0.0909 0.0759 0.7864
8.750 1.3009 0.02467 0.01631 -0.0884 0.0498 0.7889
9.000 1.3077 0.02587 0.01748 -0.0857 0.0344 0.7915
9.250 1.3151 0.02710 0.01876 -0.0832 0.0250 0.7943
9.500 1.3209 0.02843 0.02015 -0.0806 0.0184 0.7970
9.750 1.3239 0.02992 0.02173 -0.0779 0.0131 0.7995
10.000 1.3281 0.03145 0.02338 -0.0756 0.0101 0.8022
10.250 1.3291 0.03334 0.02535 -0.0735 0.0082 0.8049
10.500 1.3332 0.03516 0.02733 -0.0720 0.0071 0.8077
10.750 1.3362 0.03722 0.02952 -0.0708 0.0064 0.8105
11.000 1.3363 0.03957 0.03202 -0.0696 0.0058 0.8130
11.250 1.3349 0.04231 0.03491 -0.0688 0.0055 0.8158
11.500 1.3335 0.04530 0.03807 -0.0684 0.0053 0.8187
11.750 1.3324 0.04847 0.04141 -0.0685 0.0051 0.8216
12.000 1.3309 0.05186 0.04497 -0.0687 0.0049 0.8243
12.250 1.3281 0.05541 0.04870 -0.0691 0.0048 0.8265
12.500 1.3244 0.05922 0.05268 -0.0696 0.0047 0.8289
12.750 1.3204 0.06319 0.05682 -0.0703 0.0046 0.8315
13.000 1.3167 0.06727 0.06109 -0.0712 0.0045 0.8344
13.250 1.3123 0.07155 0.06553 -0.0723 0.0044 0.8372
13.500 1.3076 0.07591 0.07004 -0.0735 0.0043 0.8397
13.750 1.3032 0.08032 0.07461 -0.0747 0.0042 0.8422
14.000 1.2989 0.08485 0.07929 -0.0760 0.0041 0.8449
14.250 1.2949 0.08947 0.08406 -0.0775 0.0041 0.8476
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