FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il) Reynolds number: 200,000 Max Cl/Cd: 47.16 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71l150-il-200000.txt Download as CSV file: xf-fx71l150-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8655 0.09791 0.09351 -0.0208 1.0000 0.0373
-14.750 -0.8630 0.09400 0.08960 -0.0221 1.0000 0.0369
-14.500 -0.8799 0.08760 0.08309 -0.0255 1.0000 0.0365
-14.250 -0.9068 0.08038 0.07570 -0.0294 1.0000 0.0361
-14.000 -0.9341 0.07376 0.06886 -0.0325 1.0000 0.0356
-13.750 -0.9621 0.06759 0.06244 -0.0348 1.0000 0.0350
-13.500 -0.9985 0.06109 0.05555 -0.0363 1.0000 0.0342
-13.250 -1.0551 0.05472 0.04852 -0.0362 1.0000 0.0333
-13.000 -1.0711 0.05216 0.04566 -0.0350 1.0000 0.0331
-12.750 -1.0636 0.04939 0.04275 -0.0344 1.0000 0.0329
-12.500 -1.0599 0.04677 0.03995 -0.0335 1.0000 0.0328
-12.250 -1.0537 0.04433 0.03734 -0.0325 1.0000 0.0327
-12.000 -1.0476 0.04206 0.03487 -0.0313 1.0000 0.0327
-11.750 -1.0353 0.03997 0.03261 -0.0304 1.0000 0.0327
-11.500 -1.0227 0.03803 0.03048 -0.0294 1.0000 0.0327
-11.250 -1.0075 0.03627 0.02855 -0.0285 1.0000 0.0328
-11.000 -0.9904 0.03466 0.02677 -0.0277 1.0000 0.0330
-10.750 -0.9592 0.03288 0.02501 -0.0282 1.0000 0.0335
-10.500 -0.9347 0.03155 0.02371 -0.0280 1.0000 0.0340
-10.250 -0.9139 0.03037 0.02254 -0.0274 1.0000 0.0345
-10.000 -0.8940 0.02923 0.02139 -0.0267 1.0000 0.0350
-9.750 -0.8757 0.02812 0.02026 -0.0259 1.0000 0.0358
-9.500 -0.8586 0.02705 0.01917 -0.0250 1.0000 0.0365
-9.250 -0.8429 0.02600 0.01807 -0.0240 1.0000 0.0374
-9.000 -0.8309 0.02480 0.01697 -0.0227 1.0000 0.0384
-8.750 -0.8190 0.02383 0.01606 -0.0214 1.0000 0.0398
-8.500 -0.8063 0.02298 0.01520 -0.0200 1.0000 0.0415
-8.250 -0.7840 0.02183 0.01408 -0.0208 0.9553 0.0437
-8.000 -0.7524 0.02065 0.01282 -0.0231 0.9208 0.0483
-7.750 -0.7352 0.01957 0.01171 -0.0224 0.8988 0.0549
-7.500 -0.7235 0.01849 0.01069 -0.0206 0.8836 0.0691
-7.250 -0.7123 0.01741 0.00976 -0.0186 0.8718 0.0970
-7.000 -0.6981 0.01655 0.00906 -0.0170 0.8625 0.1333
-6.750 -0.6826 0.01571 0.00843 -0.0156 0.8538 0.1773
-6.500 -0.6675 0.01491 0.00786 -0.0140 0.8465 0.2300
-6.250 -0.6522 0.01407 0.00733 -0.0125 0.8384 0.2926
-6.000 -0.6351 0.01347 0.00697 -0.0109 0.8317 0.3541
-5.750 -0.6142 0.01306 0.00678 -0.0099 0.8245 0.4083
-5.500 -0.5918 0.01288 0.00671 -0.0088 0.8184 0.4512
-5.250 -0.5675 0.01283 0.00674 -0.0081 0.8124 0.4876
-5.000 -0.5424 0.01291 0.00679 -0.0074 0.8064 0.5192
-4.750 -0.5170 0.01307 0.00694 -0.0066 0.8015 0.5430
-4.500 -0.4905 0.01326 0.00715 -0.0060 0.7960 0.5629
-4.250 -0.4642 0.01352 0.00735 -0.0054 0.7911 0.5806
-4.000 -0.4373 0.01389 0.00771 -0.0047 0.7869 0.5958
-3.750 -0.4093 0.01426 0.00812 -0.0042 0.7815 0.6075
-3.500 -0.3827 0.01449 0.00824 -0.0037 0.7766 0.6186
-3.250 -0.3546 0.01479 0.00854 -0.0033 0.7719 0.6255
-3.000 -0.3277 0.01497 0.00866 -0.0030 0.7660 0.6355
-2.750 -0.3000 0.01530 0.00898 -0.0024 0.7611 0.6430
-2.500 -0.2732 0.01542 0.00904 -0.0021 0.7558 0.6516
-2.250 -0.2453 0.01559 0.00922 -0.0018 0.7507 0.6569
-2.000 -0.2188 0.01565 0.00916 -0.0015 0.7468 0.6654
-1.750 -0.1906 0.01583 0.00939 -0.0013 0.7420 0.6696
-1.500 -0.1632 0.01595 0.00949 -0.0011 0.7374 0.6758
-1.250 -0.1361 0.01600 0.00948 -0.0009 0.7337 0.6817
-1.000 -0.1085 0.01612 0.00964 -0.0007 0.7287 0.6864
-0.750 -0.0816 0.01616 0.00960 -0.0006 0.7234 0.6937
-0.500 -0.0545 0.01624 0.00969 -0.0001 0.7189 0.6980
-0.250 -0.0273 0.01625 0.00972 -0.0001 0.7126 0.7035
0.000 0.0000 0.01623 0.00965 0.0000 0.7085 0.7085
0.250 0.0273 0.01625 0.00972 0.0001 0.7035 0.7126
0.500 0.0544 0.01624 0.00969 0.0001 0.6980 0.7189
0.750 0.0816 0.01616 0.00961 0.0006 0.6937 0.7235
1.000 0.1085 0.01613 0.00965 0.0007 0.6865 0.7288
1.250 0.1360 0.01600 0.00948 0.0009 0.6817 0.7337
1.500 0.1632 0.01595 0.00949 0.0011 0.6758 0.7374
1.750 0.1906 0.01583 0.00939 0.0013 0.6696 0.7420
2.000 0.2188 0.01565 0.00915 0.0015 0.6653 0.7468
2.250 0.2453 0.01559 0.00922 0.0018 0.6569 0.7507
2.500 0.2732 0.01541 0.00903 0.0021 0.6516 0.7558
2.750 0.3000 0.01531 0.00898 0.0024 0.6430 0.7611
3.000 0.3277 0.01497 0.00867 0.0030 0.6355 0.7660
3.250 0.3546 0.01479 0.00854 0.0033 0.6255 0.7719
3.500 0.3827 0.01449 0.00825 0.0037 0.6186 0.7766
3.750 0.4093 0.01427 0.00813 0.0042 0.6075 0.7815
4.000 0.4373 0.01389 0.00771 0.0047 0.5957 0.7868
4.250 0.4642 0.01352 0.00735 0.0054 0.5806 0.7911
4.500 0.4905 0.01325 0.00713 0.0061 0.5625 0.7960
4.750 0.5170 0.01306 0.00693 0.0066 0.5426 0.8015
5.000 0.5424 0.01291 0.00679 0.0074 0.5188 0.8063
5.250 0.5674 0.01283 0.00673 0.0081 0.4871 0.8124
5.500 0.5918 0.01288 0.00670 0.0088 0.4508 0.8184
5.750 0.6143 0.01306 0.00678 0.0099 0.4087 0.8245
6.000 0.6352 0.01347 0.00697 0.0109 0.3546 0.8317
6.250 0.6522 0.01408 0.00733 0.0125 0.2923 0.8384
6.500 0.6676 0.01491 0.00786 0.0140 0.2301 0.8465
6.750 0.6826 0.01571 0.00843 0.0156 0.1773 0.8538
7.000 0.6979 0.01656 0.00906 0.0170 0.1325 0.8625
7.250 0.7122 0.01743 0.00976 0.0186 0.0964 0.8718
7.500 0.7237 0.01849 0.01069 0.0206 0.0691 0.8836
7.750 0.7354 0.01957 0.01170 0.0224 0.0549 0.8989
8.000 0.7528 0.02063 0.01281 0.0231 0.0485 0.9207
8.250 0.7841 0.02185 0.01410 0.0208 0.0438 0.9554
8.500 0.8067 0.02297 0.01519 0.0199 0.0414 1.0000
8.750 0.8191 0.02385 0.01607 0.0213 0.0397 1.0000
9.000 0.8310 0.02481 0.01697 0.0227 0.0383 1.0000
9.250 0.8434 0.02598 0.01806 0.0239 0.0375 1.0000
9.500 0.8591 0.02704 0.01915 0.0250 0.0367 1.0000
9.750 0.8764 0.02812 0.02025 0.0259 0.0359 1.0000
10.000 0.8948 0.02922 0.02137 0.0267 0.0352 1.0000
10.250 0.9142 0.03037 0.02253 0.0274 0.0345 1.0000
10.500 0.9354 0.03156 0.02372 0.0279 0.0340 1.0000
10.750 0.9584 0.03284 0.02500 0.0283 0.0336 1.0000
11.000 0.9903 0.03458 0.02670 0.0277 0.0331 1.0000
11.250 1.0104 0.03627 0.02851 0.0282 0.0329 1.0000
11.500 1.0246 0.03801 0.03045 0.0292 0.0328 1.0000
11.750 1.0365 0.03998 0.03261 0.0303 0.0327 1.0000
12.000 1.0495 0.04203 0.03482 0.0311 0.0327 1.0000
12.250 1.0548 0.04433 0.03734 0.0324 0.0327 1.0000
12.500 1.0617 0.04674 0.03991 0.0333 0.0328 1.0000
12.750 1.0644 0.04937 0.04272 0.0343 0.0329 1.0000
13.000 1.0703 0.05225 0.04575 0.0350 0.0330 1.0000
13.250 1.0585 0.05487 0.04864 0.0360 0.0332 1.0000
13.500 0.9967 0.06132 0.05581 0.0361 0.0344 1.0000
13.750 0.9625 0.06767 0.06253 0.0347 0.0351 1.0000
14.000 0.9350 0.07378 0.06889 0.0324 0.0357 1.0000
14.250 0.9098 0.08012 0.07542 0.0294 0.0361 1.0000
14.500 0.8858 0.08689 0.08235 0.0259 0.0366 1.0000
14.750 0.8659 0.09371 0.08930 0.0222 0.0369 1.0000
15.000 0.8628 0.09850 0.09412 0.0202 0.0373 1.0000
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