NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il) Reynolds number: 200,000 Max Cl/Cd: 34.14 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h20-il-200000-n5.txt Download as CSV file: xf-n5h20-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-20 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2689 0.10456 0.09961 -0.0596 0.6737 0.0376
-12.250 -0.2667 0.10090 0.09594 -0.0610 0.6714 0.0375
-12.000 -0.2644 0.09746 0.09248 -0.0624 0.6692 0.0372
-11.750 -0.2649 0.09358 0.08857 -0.0640 0.6673 0.0369
-11.500 -0.2718 0.08851 0.08349 -0.0666 0.6658 0.0364
-11.250 -0.2889 0.08140 0.07639 -0.0711 0.6642 0.0359
-11.000 -0.3351 0.07083 0.06573 -0.0773 0.6629 0.0353
-10.750 -0.3792 0.06392 0.05865 -0.0770 0.6612 0.0348
-10.500 -0.4172 0.05872 0.05324 -0.0740 0.6592 0.0344
-10.250 -0.4454 0.05483 0.04913 -0.0699 0.6571 0.0343
-10.000 -0.4684 0.05149 0.04555 -0.0650 0.6550 0.0342
-9.750 -0.4862 0.04869 0.04250 -0.0599 0.6530 0.0342
-9.500 -0.4976 0.04656 0.04014 -0.0550 0.6511 0.0343
-9.250 -0.4998 0.04468 0.03803 -0.0513 0.6494 0.0346
-8.750 -0.4960 0.04080 0.03366 -0.0447 0.6454 0.0353
-8.500 -0.4913 0.03865 0.03123 -0.0416 0.6430 0.0355
-8.250 -0.4823 0.03665 0.02895 -0.0391 0.6407 0.0357
-8.000 -0.4702 0.03475 0.02675 -0.0369 0.6384 0.0359
-7.750 -0.4548 0.03300 0.02471 -0.0351 0.6364 0.0361
-7.500 -0.4364 0.03141 0.02283 -0.0337 0.6346 0.0364
-7.250 -0.4152 0.02995 0.02108 -0.0328 0.6329 0.0367
-7.000 -0.3915 0.02864 0.01948 -0.0322 0.6314 0.0371
-6.750 -0.3656 0.02747 0.01802 -0.0321 0.6300 0.0374
-6.500 -0.3376 0.02650 0.01692 -0.0324 0.6282 0.0380
-6.250 -0.3097 0.02582 0.01625 -0.0329 0.6264 0.0386
-6.000 -0.2810 0.02518 0.01557 -0.0334 0.6245 0.0392
-5.750 -0.2501 0.02448 0.01480 -0.0343 0.6227 0.0398
-5.500 -0.2166 0.02373 0.01397 -0.0356 0.6209 0.0404
-5.250 -0.1792 0.02294 0.01310 -0.0377 0.6192 0.0411
-5.000 -0.1412 0.02221 0.01230 -0.0398 0.6176 0.0418
-4.750 -0.1051 0.02159 0.01162 -0.0416 0.6160 0.0425
-4.500 -0.0719 0.02109 0.01105 -0.0427 0.6145 0.0432
-4.250 -0.0412 0.02064 0.01063 -0.0435 0.6132 0.0441
-4.000 -0.0132 0.02035 0.01033 -0.0438 0.6120 0.0454
-3.750 0.0143 0.02010 0.01009 -0.0440 0.6107 0.0469
-3.500 0.0413 0.01988 0.00988 -0.0442 0.6092 0.0482
-3.250 0.0674 0.01965 0.00969 -0.0442 0.6077 0.0494
-3.000 0.0922 0.01943 0.00953 -0.0440 0.6061 0.0507
-2.750 0.1166 0.01927 0.00941 -0.0438 0.6046 0.0524
-2.500 0.1407 0.01914 0.00928 -0.0434 0.6032 0.0546
-2.250 0.1646 0.01899 0.00914 -0.0430 0.6017 0.0570
-2.000 0.1886 0.01887 0.00903 -0.0425 0.6001 0.0611
-1.750 0.2123 0.01871 0.00887 -0.0420 0.5986 0.0662
-1.500 0.2358 0.01856 0.00871 -0.0414 0.5971 0.0735
-1.250 0.2582 0.01836 0.00856 -0.0407 0.5958 0.0867
-1.000 0.2715 0.01758 0.00850 -0.0385 0.5946 0.2635
0.250 0.5013 0.02345 0.01619 -0.0499 0.5872 0.8932
0.500 0.5495 0.02352 0.01623 -0.0540 0.5854 0.8987
0.750 0.5727 0.02358 0.01626 -0.0536 0.5836 0.8999
1.000 0.5940 0.02362 0.01627 -0.0529 0.5821 0.9004
1.250 0.6147 0.02364 0.01627 -0.0521 0.5807 0.9005
1.500 0.6358 0.02359 0.01617 -0.0512 0.5792 0.9005
1.750 0.6567 0.02357 0.01612 -0.0504 0.5780 0.9006
2.000 0.6791 0.02345 0.01593 -0.0497 0.5763 0.9010
2.250 0.7006 0.02343 0.01586 -0.0488 0.5750 0.9014
2.500 0.7146 0.02378 0.01631 -0.0472 0.5724 0.9016
2.750 0.7284 0.02409 0.01668 -0.0455 0.5700 0.9019
3.000 0.7419 0.02436 0.01699 -0.0436 0.5677 0.9022
3.250 0.7550 0.02456 0.01721 -0.0416 0.5657 0.9026
3.500 0.7686 0.02466 0.01732 -0.0395 0.5637 0.9030
3.750 0.7848 0.02458 0.01723 -0.0377 0.5617 0.9033
4.000 0.7996 0.02450 0.01713 -0.0356 0.5601 0.9042
4.250 0.8167 0.02433 0.01692 -0.0338 0.5585 0.9047
4.500 0.8296 0.02430 0.01689 -0.0314 0.5572 0.9051
4.750 0.6144 0.03024 0.02323 0.0041 0.5449 0.9129
5.000 0.6075 0.03020 0.02317 0.0099 0.5430 0.9142
5.250 0.6138 0.02960 0.02253 0.0141 0.5418 0.9151
5.500 0.6237 0.02886 0.02175 0.0179 0.5408 0.9161
9.750 0.5539 0.04607 0.03931 0.0742 0.4088 0.9345
10.000 0.5799 0.04575 0.03900 0.0741 0.4022 0.9349
10.250 0.6061 0.04543 0.03866 0.0740 0.3943 0.9353
10.500 0.6377 0.04470 0.03791 0.0735 0.3880 0.9357
10.750 0.6698 0.04393 0.03709 0.0730 0.3812 0.9360
11.000 0.7024 0.04310 0.03620 0.0724 0.3734 0.9364
11.250 0.7336 0.04240 0.03544 0.0720 0.3657 0.9368
11.500 0.7599 0.04211 0.03508 0.0718 0.3574 0.9372
11.750 0.7850 0.04190 0.03480 0.0717 0.3496 0.9377
12.000 0.8036 0.04221 0.03503 0.0719 0.3388 0.9383
12.250 0.8239 0.04257 0.03532 0.0718 0.3300 0.9388
12.500 0.8411 0.04333 0.03609 0.0716 0.3227 0.9393
12.750 0.8608 0.04376 0.03644 0.0714 0.3139 0.9399
13.000 0.8746 0.04492 0.03769 0.0712 0.3074 0.9405
13.250 0.8895 0.04594 0.03872 0.0710 0.2998 0.9411
13.500 0.9057 0.04682 0.03960 0.0708 0.2931 0.9418
13.750 0.9166 0.04827 0.04116 0.0706 0.2852 0.9426
14.000 0.9288 0.04952 0.04243 0.0705 0.2766 0.9435
14.250 0.9374 0.05124 0.04423 0.0703 0.2643 0.9445
14.500 0.9473 0.05283 0.04586 0.0701 0.2527 0.9455
14.750 0.9544 0.05466 0.04768 0.0699 0.2380 0.9467
15.000 0.9598 0.05668 0.04965 0.0698 0.2231 0.9478
15.250 0.9642 0.05881 0.05175 0.0697 0.2090 0.9490
15.500 0.9683 0.06100 0.05390 0.0695 0.1924 0.9501
15.750 0.9710 0.06340 0.05626 0.0692 0.1716 0.9511
16.000 0.9675 0.06643 0.05916 0.0691 0.1484 0.9521
16.250 0.9664 0.06933 0.06199 0.0688 0.1368 0.9532
16.750 0.9729 0.07473 0.06739 0.0672 0.1222 0.9551
17.000 0.9760 0.07755 0.07023 0.0662 0.1167 0.9561
17.250 0.9842 0.07991 0.07267 0.0651 0.1111 0.9572
17.500 0.9886 0.08268 0.07549 0.0639 0.1059 0.9584
17.750 0.9958 0.08523 0.07813 0.0626 0.1003 0.9596
18.000 1.0020 0.08797 0.08094 0.0612 0.0929 0.9609
18.250 1.0107 0.09048 0.08357 0.0598 0.0828 0.9623
18.500 1.0132 0.09373 0.08681 0.0582 0.0717 0.9637
18.750 1.0120 0.09746 0.09050 0.0566 0.0653 0.9651
19.000 1.0122 0.10105 0.09412 0.0549 0.0615 0.9666
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