WORTMANN FX 71-120 AIRFOIL (fx71120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 71-120 AIRFOIL (fx71120-il) Reynolds number: 500,000 Max Cl/Cd: 50.31 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71120-il-500000.txt Download as CSV file: xf-fx71120-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-120 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
------ -------- --------- --------- -------- -------- --------
-17.000 -1.1938 0.06774 0.06397 -0.0477 1.0000 0.0555
-16.750 -1.2295 0.06015 0.05613 -0.0526 1.0000 0.0559
-16.500 -1.2546 0.05484 0.05060 -0.0554 1.0000 0.0562
-16.250 -1.2750 0.05088 0.04642 -0.0568 1.0000 0.0566
-16.000 -1.2888 0.04698 0.04239 -0.0570 1.0000 0.0573
-15.750 -1.2761 0.04595 0.04141 -0.0566 1.0000 0.0580
-15.500 -1.2701 0.04470 0.04015 -0.0561 1.0000 0.0586
-15.250 -1.2656 0.04346 0.03887 -0.0553 1.0000 0.0592
-15.000 -1.2604 0.04224 0.03761 -0.0544 1.0000 0.0597
-14.750 -1.2576 0.04101 0.03630 -0.0531 1.0000 0.0604
-14.500 -1.2584 0.03964 0.03483 -0.0513 1.0000 0.0611
-14.250 -1.2612 0.03841 0.03347 -0.0488 1.0000 0.0618
-14.000 -1.2650 0.03725 0.03215 -0.0456 1.0000 0.0623
-13.750 -1.2695 0.03638 0.03113 -0.0417 1.0000 0.0628
-13.500 -1.2694 0.03586 0.03045 -0.0381 1.0000 0.0633
-13.250 -1.2628 0.03336 0.02784 -0.0364 1.0000 0.0641
-13.000 -1.2470 0.03244 0.02692 -0.0351 1.0000 0.0648
-12.750 -1.2323 0.03176 0.02621 -0.0335 1.0000 0.0654
-12.500 -1.2171 0.03119 0.02561 -0.0319 1.0000 0.0661
-12.250 -1.2001 0.03068 0.02508 -0.0304 1.0000 0.0668
-12.000 -1.1846 0.02999 0.02432 -0.0287 1.0000 0.0675
-11.750 -1.1696 0.02918 0.02342 -0.0270 1.0000 0.0682
-11.500 -1.1544 0.02833 0.02246 -0.0252 1.0000 0.0688
-11.250 -1.1387 0.02760 0.02162 -0.0234 1.0000 0.0693
-11.000 -1.1224 0.02693 0.02083 -0.0217 1.0000 0.0699
-10.750 -1.1057 0.02642 0.02020 -0.0198 1.0000 0.0703
-10.500 -1.0896 0.02546 0.01911 -0.0181 1.0000 0.0710
-10.250 -1.0696 0.02408 0.01775 -0.0172 1.0000 0.0721
-10.000 -1.0494 0.02347 0.01715 -0.0160 1.0000 0.0729
-9.750 -1.0296 0.02283 0.01647 -0.0146 1.0000 0.0733
-9.500 -1.0096 0.02205 0.01563 -0.0133 1.0000 0.0735
-9.250 -0.9893 0.02130 0.01483 -0.0120 1.0000 0.0737
-9.000 -0.9689 0.02059 0.01407 -0.0106 1.0000 0.0739
-8.750 -0.9484 0.01994 0.01337 -0.0093 1.0000 0.0742
-8.500 -0.9278 0.01929 0.01268 -0.0079 1.0000 0.0743
-8.250 -0.9073 0.01869 0.01205 -0.0065 1.0000 0.0745
-8.000 -0.8870 0.01813 0.01145 -0.0050 1.0000 0.0748
-7.750 -0.8668 0.01764 0.01094 -0.0035 1.0000 0.0752
-7.500 -0.8468 0.01714 0.01042 -0.0020 1.0000 0.0755
-7.250 -0.8270 0.01664 0.00990 -0.0003 1.0000 0.0757
-7.000 -0.8076 0.01618 0.00942 0.0013 1.0000 0.0759
-6.750 -0.7885 0.01573 0.00895 0.0031 1.0000 0.0762
-6.500 -0.7696 0.01532 0.00853 0.0049 1.0000 0.0764
-6.250 -0.7511 0.01493 0.00813 0.0067 1.0000 0.0767
-6.000 -0.7329 0.01457 0.00776 0.0086 1.0000 0.0769
-5.750 -0.7148 0.01424 0.00742 0.0105 1.0000 0.0772
-5.500 -0.6866 0.01390 0.00707 0.0104 0.9987 0.0775
-5.250 -0.6487 0.01355 0.00673 0.0083 0.9956 0.0779
-5.000 -0.6101 0.01324 0.00642 0.0061 0.9930 0.0783
-4.750 -0.5756 0.01291 0.00609 0.0048 0.9892 0.0787
-4.500 -0.5397 0.01253 0.00572 0.0031 0.9856 0.0793
-4.250 -0.5017 0.01209 0.00532 0.0010 0.9827 0.0803
-4.000 -0.4679 0.01171 0.00498 -0.0001 0.9772 0.0815
-3.750 -0.4306 0.01139 0.00470 -0.0019 0.9728 0.0828
-3.500 -0.3920 0.01106 0.00441 -0.0039 0.9674 0.0844
-3.250 -0.3532 0.01074 0.00411 -0.0058 0.9606 0.0866
-3.000 -0.3131 0.01038 0.00378 -0.0080 0.9534 0.0895
-2.750 -0.2765 0.01000 0.00347 -0.0095 0.9443 0.0947
-2.500 -0.2435 0.00966 0.00322 -0.0103 0.9330 0.1050
-2.250 -0.2119 0.00917 0.00294 -0.0108 0.9174 0.1420
-2.000 -0.1839 0.00868 0.00271 -0.0106 0.8966 0.2038
-1.750 -0.1575 0.00835 0.00254 -0.0100 0.8741 0.2560
-1.500 -0.1331 0.00809 0.00240 -0.0090 0.8478 0.3032
-1.250 -0.1097 0.00786 0.00227 -0.0077 0.8164 0.3523
-1.000 -0.0869 0.00764 0.00218 -0.0064 0.7858 0.4086
-0.750 -0.0648 0.00748 0.00209 -0.0049 0.7469 0.4639
-0.500 -0.0432 0.00739 0.00203 -0.0032 0.7027 0.5154
-0.250 -0.0218 0.00732 0.00199 -0.0016 0.6571 0.5661
0.000 0.0000 0.00730 0.00198 0.0000 0.6137 0.6137
0.250 0.0218 0.00732 0.00199 0.0016 0.5663 0.6572
0.500 0.0433 0.00739 0.00203 0.0032 0.5153 0.7021
0.750 0.0647 0.00748 0.00209 0.0049 0.4634 0.7476
1.000 0.0869 0.00764 0.00218 0.0064 0.4090 0.7856
1.250 0.1097 0.00786 0.00227 0.0077 0.3527 0.8169
1.500 0.1330 0.00809 0.00240 0.0090 0.3029 0.8481
1.750 0.1576 0.00835 0.00254 0.0100 0.2562 0.8744
2.000 0.1839 0.00868 0.00270 0.0106 0.2038 0.8963
2.250 0.2119 0.00918 0.00294 0.0108 0.1403 0.9177
2.500 0.2434 0.00967 0.00322 0.0103 0.1043 0.9329
2.750 0.2763 0.01000 0.00347 0.0095 0.0945 0.9442
3.000 0.3131 0.01037 0.00377 0.0080 0.0895 0.9533
3.250 0.3527 0.01074 0.00411 0.0059 0.0867 0.9605
3.500 0.3921 0.01107 0.00441 0.0039 0.0845 0.9677
3.750 0.4304 0.01138 0.00469 0.0019 0.0828 0.9727
4.000 0.4679 0.01171 0.00498 0.0001 0.0815 0.9772
4.250 0.5018 0.01208 0.00531 -0.0011 0.0804 0.9827
4.500 0.5396 0.01254 0.00573 -0.0031 0.0792 0.9856
4.750 0.5756 0.01290 0.00608 -0.0048 0.0787 0.9892
5.000 0.6102 0.01323 0.00641 -0.0061 0.0783 0.9930
5.250 0.6487 0.01355 0.00672 -0.0083 0.0779 0.9956
5.500 0.6868 0.01390 0.00707 -0.0104 0.0775 0.9987
5.750 0.7149 0.01423 0.00741 -0.0105 0.0772 1.0000
6.000 0.7329 0.01457 0.00775 -0.0086 0.0769 1.0000
6.250 0.7511 0.01493 0.00813 -0.0067 0.0766 1.0000
6.500 0.7697 0.01531 0.00852 -0.0049 0.0764 1.0000
6.750 0.7885 0.01574 0.00895 -0.0031 0.0762 1.0000
7.000 0.8076 0.01617 0.00941 -0.0013 0.0760 1.0000
7.250 0.8271 0.01664 0.00990 0.0003 0.0757 1.0000
7.500 0.8468 0.01715 0.01042 0.0020 0.0756 1.0000
7.750 0.8668 0.01765 0.01094 0.0035 0.0753 1.0000
8.000 0.8870 0.01814 0.01146 0.0050 0.0748 1.0000
8.250 0.9074 0.01869 0.01204 0.0065 0.0746 1.0000
8.500 0.9279 0.01929 0.01268 0.0079 0.0743 1.0000
8.750 0.9484 0.01993 0.01336 0.0093 0.0741 1.0000
9.000 0.9689 0.02060 0.01407 0.0106 0.0739 1.0000
9.250 0.9893 0.02131 0.01483 0.0120 0.0737 1.0000
9.500 1.0096 0.02204 0.01562 0.0133 0.0735 1.0000
9.750 1.0297 0.02283 0.01647 0.0146 0.0734 1.0000
10.000 1.0494 0.02352 0.01720 0.0160 0.0729 1.0000
10.250 1.0695 0.02409 0.01777 0.0172 0.0722 1.0000
10.500 1.0896 0.02554 0.01919 0.0181 0.0710 1.0000
10.750 1.1057 0.02642 0.02020 0.0198 0.0703 1.0000
11.000 1.1224 0.02690 0.02079 0.0217 0.0698 1.0000
11.250 1.1387 0.02758 0.02159 0.0234 0.0693 1.0000
11.500 1.1544 0.02836 0.02249 0.0252 0.0688 1.0000
11.750 1.1697 0.02917 0.02341 0.0270 0.0682 1.0000
12.000 1.1849 0.02993 0.02426 0.0287 0.0675 1.0000
12.250 1.2004 0.03064 0.02504 0.0304 0.0668 1.0000
12.500 1.2174 0.03116 0.02558 0.0318 0.0661 1.0000
12.750 1.2324 0.03178 0.02623 0.0335 0.0654 1.0000
13.000 1.2471 0.03245 0.02693 0.0351 0.0648 1.0000
13.250 1.2627 0.03337 0.02785 0.0364 0.0642 1.0000
13.500 1.2697 0.03589 0.03048 0.0380 0.0633 1.0000
13.750 1.2702 0.03655 0.03131 0.0415 0.0629 1.0000
14.000 1.2654 0.03722 0.03213 0.0456 0.0623 1.0000
14.250 1.2617 0.03832 0.03338 0.0487 0.0617 1.0000
14.500 1.2591 0.03963 0.03482 0.0512 0.0611 1.0000
14.750 1.2579 0.04103 0.03634 0.0530 0.0604 1.0000
15.000 1.2602 0.04233 0.03771 0.0543 0.0598 1.0000
15.250 1.2680 0.04328 0.03867 0.0552 0.0591 1.0000
15.500 1.2717 0.04462 0.04006 0.0560 0.0585 1.0000
15.750 1.2776 0.04588 0.04134 0.0565 0.0580 1.0000
16.000 1.2888 0.04707 0.04248 0.0569 0.0573 1.0000
16.250 1.2757 0.05088 0.04643 0.0567 0.0565 1.0000
16.500 1.2558 0.05482 0.05058 0.0553 0.0562 1.0000
16.750 1.2304 0.06015 0.05613 0.0524 0.0558 1.0000
17.000 1.1948 0.06778 0.06402 0.0475 0.0555 1.0000
17.250 0.7335 0.17162 0.16874 -0.0191 0.0407 1.0000
17.500 0.7397 0.17458 0.17171 -0.0206 0.0398 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 71-120 AIRFOIL (fx71120-il)