FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il) Reynolds number: 100,000 Max Cl/Cd: 35.18 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71l150-il-100000-n5.txt Download as CSV file: xf-fx71l150-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/30 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7380 0.14024 0.13453 0.0098 1.0000 0.0290
-15.500 -0.7914 0.12042 0.11454 -0.0017 1.0000 0.0284
-15.250 -0.8360 0.10566 0.09954 -0.0111 1.0000 0.0279
-15.000 -0.8695 0.09497 0.08858 -0.0180 1.0000 0.0277
-14.750 -0.8926 0.08718 0.08056 -0.0225 1.0000 0.0275
-14.500 -0.9111 0.08077 0.07391 -0.0259 1.0000 0.0274
-14.250 -0.9271 0.07516 0.06807 -0.0285 1.0000 0.0275
-14.000 -0.9388 0.07040 0.06309 -0.0303 1.0000 0.0276
-13.750 -0.9463 0.06630 0.05877 -0.0315 1.0000 0.0276
-13.500 -0.9509 0.06265 0.05492 -0.0324 1.0000 0.0277
-13.250 -0.9555 0.05913 0.05115 -0.0329 1.0000 0.0282
-13.000 -0.9560 0.05612 0.04791 -0.0332 1.0000 0.0286
-12.750 -0.9526 0.05348 0.04506 -0.0331 1.0000 0.0288
-12.500 -0.9460 0.05131 0.04282 -0.0330 1.0000 0.0293
-12.250 -0.9379 0.04934 0.04079 -0.0328 1.0000 0.0297
-12.000 -0.9303 0.04742 0.03882 -0.0325 1.0000 0.0304
-11.750 -0.9201 0.04559 0.03689 -0.0321 1.0000 0.0309
-11.500 -0.9095 0.04382 0.03501 -0.0315 1.0000 0.0317
-11.250 -0.8973 0.04218 0.03325 -0.0309 1.0000 0.0323
-11.000 -0.8846 0.04061 0.03156 -0.0302 1.0000 0.0330
-10.750 -0.8740 0.03904 0.03002 -0.0295 1.0000 0.0336
-10.500 -0.8638 0.03751 0.02849 -0.0288 1.0000 0.0344
-10.250 -0.8534 0.03603 0.02697 -0.0281 1.0000 0.0353
-10.000 -0.8433 0.03458 0.02546 -0.0273 1.0000 0.0364
-9.750 -0.8338 0.03312 0.02395 -0.0264 1.0000 0.0377
-9.500 -0.8253 0.03171 0.02255 -0.0255 1.0000 0.0389
-9.250 -0.8168 0.03035 0.02116 -0.0243 1.0000 0.0411
-9.000 -0.8087 0.02907 0.01987 -0.0230 1.0000 0.0433
-8.750 -0.8007 0.02790 0.01869 -0.0214 1.0000 0.0465
-8.500 -0.7926 0.02681 0.01762 -0.0196 1.0000 0.0502
-8.250 -0.7822 0.02576 0.01661 -0.0182 1.0000 0.0558
-8.000 -0.7593 0.02465 0.01551 -0.0191 0.9352 0.0654
-7.750 -0.7325 0.02362 0.01447 -0.0204 0.9017 0.0823
-7.250 -0.6970 0.02179 0.01279 -0.0190 0.8640 0.1284
-7.000 -0.6817 0.02094 0.01205 -0.0178 0.8515 0.1586
-6.750 -0.6669 0.02006 0.01135 -0.0164 0.8420 0.1957
-6.500 -0.6524 0.01917 0.01068 -0.0150 0.8339 0.2454
-6.250 -0.6383 0.01829 0.01015 -0.0134 0.8264 0.3086
-6.000 -0.6217 0.01768 0.00988 -0.0118 0.8194 0.3746
-5.750 -0.6011 0.01743 0.00985 -0.0105 0.8132 0.4294
-5.500 -0.5782 0.01740 0.00989 -0.0094 0.8068 0.4710
-5.250 -0.5540 0.01744 0.00988 -0.0085 0.8011 0.5000
-5.000 -0.5290 0.01754 0.00993 -0.0077 0.7947 0.5229
-4.750 -0.5040 0.01761 0.00988 -0.0070 0.7892 0.5414
-4.500 -0.4779 0.01778 0.00997 -0.0063 0.7836 0.5568
-4.250 -0.4515 0.01800 0.01015 -0.0056 0.7781 0.5701
-4.000 -0.4255 0.01816 0.01018 -0.0049 0.7735 0.5834
-3.750 -0.3990 0.01830 0.01026 -0.0045 0.7676 0.5954
-3.500 -0.3719 0.01849 0.01039 -0.0039 0.7625 0.6044
-3.250 -0.3455 0.01859 0.01039 -0.0035 0.7578 0.6137
-3.000 -0.3186 0.01867 0.01043 -0.0032 0.7529 0.6210
-2.750 -0.2919 0.01879 0.01046 -0.0028 0.7486 0.6289
-2.500 -0.2657 0.01883 0.01041 -0.0024 0.7446 0.6367
-2.250 -0.2387 0.01890 0.01046 -0.0022 0.7398 0.6432
-2.000 -0.2130 0.01886 0.01030 -0.0019 0.7352 0.6510
-1.750 -0.1860 0.01895 0.01036 -0.0014 0.7301 0.6561
-1.500 -0.1600 0.01893 0.01028 -0.0012 0.7241 0.6632
-1.250 -0.1333 0.01895 0.01024 -0.0008 0.7198 0.6682
-1.000 -0.1066 0.01899 0.01030 -0.0006 0.7135 0.6730
-0.750 -0.0803 0.01897 0.01021 -0.0005 0.7092 0.6796
-0.500 -0.0532 0.01903 0.01030 -0.0003 0.7047 0.6839
-0.250 -0.0267 0.01908 0.01036 -0.0001 0.6995 0.6897
0.000 0.0000 0.01906 0.01032 0.0000 0.6953 0.6953
0.250 0.0267 0.01908 0.01036 0.0001 0.6897 0.6995
0.500 0.0532 0.01903 0.01030 0.0003 0.6839 0.7048
0.750 0.0803 0.01897 0.01021 0.0005 0.6796 0.7092
1.000 0.1066 0.01899 0.01030 0.0006 0.6730 0.7135
1.250 0.1333 0.01895 0.01024 0.0008 0.6682 0.7198
1.500 0.1600 0.01893 0.01028 0.0012 0.6632 0.7241
1.750 0.1860 0.01895 0.01036 0.0014 0.6561 0.7301
2.000 0.2130 0.01886 0.01030 0.0019 0.6510 0.7352
2.250 0.2387 0.01890 0.01046 0.0022 0.6432 0.7398
2.500 0.2657 0.01883 0.01041 0.0024 0.6367 0.7446
2.750 0.2919 0.01878 0.01045 0.0028 0.6288 0.7486
3.000 0.3186 0.01867 0.01042 0.0032 0.6210 0.7529
3.250 0.3456 0.01859 0.01039 0.0035 0.6136 0.7578
3.500 0.3719 0.01849 0.01038 0.0039 0.6043 0.7625
3.750 0.3990 0.01830 0.01026 0.0045 0.5954 0.7676
4.000 0.4255 0.01816 0.01019 0.0049 0.5835 0.7735
4.250 0.4515 0.01800 0.01015 0.0056 0.5701 0.7781
4.500 0.4780 0.01778 0.00997 0.0063 0.5569 0.7836
4.750 0.5040 0.01761 0.00988 0.0070 0.5414 0.7892
5.000 0.5290 0.01754 0.00993 0.0077 0.5229 0.7947
5.250 0.5540 0.01744 0.00988 0.0085 0.5001 0.8011
5.500 0.5782 0.01740 0.00989 0.0094 0.4709 0.8068
5.750 0.6012 0.01743 0.00985 0.0105 0.4299 0.8132
6.000 0.6219 0.01768 0.00989 0.0118 0.3759 0.8194
6.250 0.6385 0.01828 0.01015 0.0134 0.3095 0.8264
6.500 0.6525 0.01917 0.01068 0.0150 0.2456 0.8340
6.750 0.6670 0.02005 0.01135 0.0164 0.1960 0.8420
7.000 0.6816 0.02094 0.01206 0.0178 0.1576 0.8515
7.250 0.6971 0.02180 0.01279 0.0190 0.1280 0.8639
7.750 0.7327 0.02362 0.01447 0.0203 0.0821 0.9019
8.000 0.7595 0.02465 0.01551 0.0190 0.0655 0.9352
8.250 0.7824 0.02576 0.01660 0.0181 0.0557 1.0000
8.500 0.7929 0.02681 0.01762 0.0196 0.0502 1.0000
8.750 0.8008 0.02791 0.01870 0.0214 0.0462 1.0000
9.000 0.8089 0.02908 0.01987 0.0230 0.0432 1.0000
9.250 0.8172 0.03034 0.02115 0.0243 0.0410 1.0000
9.500 0.8259 0.03169 0.02253 0.0254 0.0390 1.0000
9.750 0.8343 0.03311 0.02394 0.0263 0.0377 1.0000
10.000 0.8439 0.03455 0.02543 0.0272 0.0364 1.0000
10.250 0.8540 0.03602 0.02696 0.0280 0.0353 1.0000
10.500 0.8643 0.03751 0.02848 0.0288 0.0343 1.0000
10.750 0.8751 0.03899 0.02998 0.0294 0.0338 1.0000
11.000 0.8854 0.04057 0.03154 0.0301 0.0331 1.0000
11.250 0.8982 0.04214 0.03320 0.0308 0.0324 1.0000
11.500 0.9106 0.04378 0.03497 0.0315 0.0318 1.0000
11.750 0.9212 0.04557 0.03687 0.0320 0.0310 1.0000
12.000 0.9317 0.04738 0.03878 0.0324 0.0306 1.0000
12.250 0.9390 0.04932 0.04078 0.0327 0.0298 1.0000
12.500 0.9473 0.05130 0.04283 0.0329 0.0294 1.0000
12.750 0.9535 0.05345 0.04503 0.0330 0.0288 1.0000
13.000 0.9558 0.05620 0.04801 0.0330 0.0284 1.0000
13.250 0.9547 0.05928 0.05132 0.0327 0.0280 1.0000
13.500 0.9533 0.06248 0.05473 0.0323 0.0279 1.0000
13.750 0.9478 0.06626 0.05872 0.0314 0.0277 1.0000
14.000 0.9400 0.07039 0.06307 0.0302 0.0276 1.0000
14.250 0.9292 0.07503 0.06793 0.0284 0.0276 1.0000
14.500 0.9139 0.08051 0.07365 0.0259 0.0276 1.0000
14.750 0.8940 0.08715 0.08052 0.0224 0.0276 1.0000
15.000 0.8695 0.09520 0.08882 0.0176 0.0277 1.0000
15.250 0.8394 0.10519 0.09906 0.0113 0.0280 1.0000
15.500 0.7905 0.12098 0.11510 0.0012 0.0284 1.0000
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