WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 500,000 Max Cl/Cd: 46.11 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71089a-il-500000.txt Download as CSV file: xf-fx71089a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-089A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9332 0.06903 0.06601 -0.0288 1.0000 0.0425
-12.750 -0.9764 0.05920 0.05601 -0.0362 1.0000 0.0422
-12.500 -1.0141 0.05298 0.04957 -0.0389 1.0000 0.0421
-12.250 -1.0448 0.04893 0.04530 -0.0375 1.0000 0.0422
-12.000 -1.0684 0.04615 0.04227 -0.0337 1.0000 0.0423
-11.750 -1.0778 0.04405 0.03988 -0.0309 1.0000 0.0426
-11.500 -1.0924 0.03929 0.03476 -0.0283 1.0000 0.0431
-11.250 -1.0828 0.03703 0.03243 -0.0271 1.0000 0.0437
-11.000 -1.0636 0.03633 0.03177 -0.0263 1.0000 0.0443
-10.750 -1.0419 0.03606 0.03155 -0.0256 1.0000 0.0449
-10.500 -1.0243 0.03529 0.03074 -0.0245 1.0000 0.0456
-10.250 -1.0106 0.03391 0.02921 -0.0231 1.0000 0.0465
-10.000 -0.9982 0.03219 0.02726 -0.0215 1.0000 0.0472
-9.750 -0.9845 0.03050 0.02532 -0.0199 1.0000 0.0478
-9.500 -0.9686 0.02914 0.02372 -0.0184 1.0000 0.0483
-9.250 -0.9511 0.02795 0.02232 -0.0169 1.0000 0.0487
-9.000 -0.9329 0.02664 0.02083 -0.0156 1.0000 0.0488
-8.750 -0.9145 0.02530 0.01928 -0.0142 1.0000 0.0491
-8.500 -0.8956 0.02349 0.01730 -0.0130 1.0000 0.0492
-8.250 -0.8753 0.02196 0.01564 -0.0119 1.0000 0.0494
-8.000 -0.8540 0.02066 0.01424 -0.0109 1.0000 0.0496
-7.750 -0.8323 0.01950 0.01301 -0.0098 1.0000 0.0498
-7.500 -0.8101 0.01853 0.01198 -0.0088 1.0000 0.0501
-7.250 -0.7877 0.01769 0.01110 -0.0078 1.0000 0.0504
-7.000 -0.7651 0.01696 0.01035 -0.0067 1.0000 0.0507
-6.750 -0.7425 0.01630 0.00966 -0.0056 1.0000 0.0511
-6.500 -0.7198 0.01569 0.00903 -0.0045 1.0000 0.0515
-6.250 -0.6972 0.01513 0.00845 -0.0034 1.0000 0.0519
-6.000 -0.6746 0.01462 0.00793 -0.0023 1.0000 0.0524
-5.750 -0.6520 0.01416 0.00746 -0.0011 1.0000 0.0531
-5.500 -0.6296 0.01370 0.00698 0.0001 1.0000 0.0536
-5.250 -0.6073 0.01325 0.00651 0.0013 1.0000 0.0541
-5.000 -0.5852 0.01283 0.00608 0.0026 1.0000 0.0546
-4.750 -0.5632 0.01243 0.00568 0.0039 1.0000 0.0551
-4.500 -0.5412 0.01209 0.00532 0.0052 1.0000 0.0556
-4.250 -0.5193 0.01178 0.00501 0.0066 1.0000 0.0561
-4.000 -0.4989 0.01128 0.00451 0.0081 1.0000 0.0570
-3.750 -0.4780 0.01090 0.00417 0.0096 1.0000 0.0581
-3.500 -0.4566 0.01064 0.00393 0.0110 1.0000 0.0592
-3.250 -0.4352 0.01042 0.00373 0.0123 1.0000 0.0605
-3.000 -0.4136 0.01025 0.00357 0.0136 1.0000 0.0622
-2.750 -0.3731 0.01006 0.00340 0.0111 0.9964 0.0642
-2.500 -0.3326 0.00971 0.00312 0.0085 0.9922 0.0684
-2.250 -0.2913 0.00943 0.00289 0.0059 0.9865 0.0748
-2.000 -0.2498 0.00894 0.00266 0.0030 0.9818 0.1113
-1.750 -0.2121 0.00837 0.00245 0.0010 0.9734 0.1818
-1.500 -0.1716 0.00780 0.00224 -0.0016 0.9624 0.2658
-1.250 -0.1339 0.00722 0.00206 -0.0035 0.9471 0.3604
-1.000 -0.0996 0.00669 0.00193 -0.0047 0.9287 0.4654
-0.750 -0.0692 0.00625 0.00181 -0.0048 0.8945 0.5654
-0.500 -0.0447 0.00599 0.00173 -0.0036 0.8546 0.6444
-0.250 -0.0222 0.00585 0.00171 -0.0018 0.8109 0.7090
0.000 0.0000 0.00583 0.00169 0.0000 0.7621 0.7619
0.250 0.0222 0.00585 0.00171 0.0018 0.7093 0.8108
0.500 0.0447 0.00599 0.00173 0.0035 0.6449 0.8539
0.750 0.0691 0.00625 0.00181 0.0048 0.5651 0.8943
1.000 0.0995 0.00669 0.00193 0.0047 0.4659 0.9285
1.250 0.1341 0.00723 0.00207 0.0035 0.3604 0.9474
1.500 0.1715 0.00781 0.00224 0.0016 0.2641 0.9624
1.750 0.2125 0.00838 0.00245 -0.0011 0.1819 0.9735
2.000 0.2500 0.00892 0.00266 -0.0031 0.1145 0.9818
2.250 0.2912 0.00943 0.00289 -0.0059 0.0748 0.9865
2.500 0.3323 0.00971 0.00312 -0.0084 0.0684 0.9921
2.750 0.3733 0.01006 0.00340 -0.0111 0.0642 0.9964
3.000 0.4135 0.01024 0.00357 -0.0136 0.0621 1.0000
3.250 0.4351 0.01042 0.00373 -0.0123 0.0604 1.0000
3.500 0.4565 0.01064 0.00393 -0.0109 0.0592 1.0000
3.750 0.4779 0.01091 0.00417 -0.0096 0.0580 1.0000
4.000 0.4988 0.01128 0.00452 -0.0081 0.0569 1.0000
4.250 0.5192 0.01178 0.00500 -0.0066 0.0560 1.0000
4.500 0.5412 0.01208 0.00532 -0.0052 0.0556 1.0000
4.750 0.5631 0.01243 0.00567 -0.0039 0.0551 1.0000
5.000 0.5851 0.01282 0.00607 -0.0026 0.0546 1.0000
5.250 0.6073 0.01324 0.00651 -0.0013 0.0541 1.0000
5.500 0.6295 0.01370 0.00698 -0.0001 0.0536 1.0000
5.750 0.6519 0.01417 0.00746 0.0011 0.0531 1.0000
6.000 0.6745 0.01463 0.00793 0.0023 0.0524 1.0000
6.250 0.6972 0.01512 0.00844 0.0034 0.0519 1.0000
6.500 0.7198 0.01569 0.00903 0.0046 0.0515 1.0000
6.750 0.7424 0.01630 0.00965 0.0056 0.0511 1.0000
7.000 0.7651 0.01696 0.01035 0.0067 0.0507 1.0000
7.250 0.7876 0.01770 0.01111 0.0078 0.0504 1.0000
7.500 0.8101 0.01853 0.01198 0.0088 0.0501 1.0000
7.750 0.8322 0.01952 0.01302 0.0098 0.0498 1.0000
8.000 0.8540 0.02067 0.01424 0.0109 0.0496 1.0000
8.250 0.8752 0.02199 0.01567 0.0119 0.0494 1.0000
8.500 0.8956 0.02348 0.01729 0.0130 0.0492 1.0000
8.750 0.9146 0.02529 0.01927 0.0142 0.0491 1.0000
9.000 0.9330 0.02655 0.02073 0.0156 0.0488 1.0000
9.250 0.9513 0.02787 0.02224 0.0169 0.0487 1.0000
9.500 0.9689 0.02900 0.02358 0.0183 0.0482 1.0000
9.750 0.9849 0.03038 0.02519 0.0199 0.0477 1.0000
10.000 0.9985 0.03213 0.02720 0.0215 0.0471 1.0000
10.250 1.0111 0.03385 0.02914 0.0231 0.0464 1.0000
10.500 1.0256 0.03511 0.03053 0.0244 0.0456 1.0000
10.750 1.0432 0.03591 0.03138 0.0255 0.0448 1.0000
11.000 1.0629 0.03646 0.03191 0.0263 0.0443 1.0000
11.250 1.0828 0.03707 0.03247 0.0271 0.0437 1.0000
11.500 1.0930 0.03921 0.03468 0.0283 0.0431 1.0000
12.000 1.0683 0.04597 0.04211 0.0337 0.0422 1.0000
12.250 1.0447 0.04896 0.04533 0.0374 0.0421 1.0000
12.500 1.0141 0.05297 0.04956 0.0388 0.0420 1.0000
12.750 0.9784 0.05917 0.05597 0.0362 0.0422 1.0000
13.000 0.9414 0.06796 0.06490 0.0303 0.0426 1.0000
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