NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il) Reynolds number: 500,000 Max Cl/Cd: 50.48 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6h20-il-500000-n5.txt Download as CSV file: xf-n6h20-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-H-20 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1774 0.09025 0.08617 -0.0649 0.6010 0.0221
-11.250 -0.1867 0.08537 0.08131 -0.0672 0.6004 0.0222
-11.000 -0.2043 0.07952 0.07550 -0.0703 0.5998 0.0222
-10.750 -0.2309 0.07318 0.06918 -0.0738 0.5992 0.0224
-10.500 -0.2738 0.06595 0.06193 -0.0749 0.5985 0.0224
-10.250 -0.3177 0.05948 0.05536 -0.0725 0.5979 0.0225
-10.000 -0.5340 0.03402 0.02841 -0.0472 0.5982 0.0241
-9.750 -0.5420 0.03124 0.02519 -0.0419 0.5974 0.0243
-9.500 -0.5361 0.02931 0.02296 -0.0387 0.5965 0.0246
-9.250 -0.5220 0.02801 0.02150 -0.0368 0.5957 0.0247
-9.000 -0.5047 0.02706 0.02044 -0.0354 0.5948 0.0249
-8.750 -0.4859 0.02622 0.01950 -0.0341 0.5940 0.0251
-8.500 -0.4656 0.02542 0.01859 -0.0330 0.5932 0.0253
-8.250 -0.4441 0.02468 0.01774 -0.0322 0.5924 0.0255
-8.000 -0.4218 0.02405 0.01701 -0.0314 0.5916 0.0258
-7.750 -0.3981 0.02339 0.01623 -0.0309 0.5909 0.0261
-7.500 -0.3729 0.02268 0.01541 -0.0307 0.5901 0.0264
-7.250 -0.3450 0.02186 0.01443 -0.0310 0.5893 0.0268
-7.000 -0.3140 0.02105 0.01347 -0.0318 0.5885 0.0271
-6.750 -0.2779 0.02020 0.01249 -0.0337 0.5877 0.0273
-6.500 -0.2423 0.01949 0.01169 -0.0355 0.5870 0.0276
-6.250 -0.2067 0.01889 0.01099 -0.0372 0.5863 0.0280
-6.000 -0.1722 0.01840 0.01044 -0.0386 0.5855 0.0282
-5.750 -0.1382 0.01798 0.00996 -0.0400 0.5846 0.0285
-5.500 -0.1033 0.01756 0.00950 -0.0415 0.5838 0.0287
-5.250 -0.0668 0.01708 0.00902 -0.0434 0.5830 0.0292
-5.000 -0.0354 0.01680 0.00876 -0.0443 0.5823 0.0296
-4.750 -0.0041 0.01654 0.00851 -0.0452 0.5815 0.0302
-4.500 0.0267 0.01631 0.00827 -0.0459 0.5807 0.0306
-4.250 0.0576 0.01608 0.00803 -0.0467 0.5799 0.0311
-4.000 0.0879 0.01587 0.00782 -0.0473 0.5791 0.0315
-3.750 0.1175 0.01568 0.00762 -0.0479 0.5784 0.0319
-3.500 0.1466 0.01551 0.00745 -0.0483 0.5776 0.0325
-3.250 0.1755 0.01535 0.00728 -0.0487 0.5768 0.0329
-3.000 0.2038 0.01521 0.00712 -0.0490 0.5760 0.0333
-2.750 0.2323 0.01504 0.00697 -0.0493 0.5752 0.0339
-2.500 0.2601 0.01490 0.00685 -0.0495 0.5744 0.0346
-2.250 0.2874 0.01481 0.00676 -0.0496 0.5737 0.0356
-2.000 0.3144 0.01475 0.00669 -0.0497 0.5730 0.0366
-1.750 0.3411 0.01470 0.00664 -0.0497 0.5723 0.0379
-1.500 0.3676 0.01466 0.00661 -0.0497 0.5716 0.0391
-1.250 0.3937 0.01462 0.00662 -0.0497 0.5710 0.0409
-1.000 0.4195 0.01459 0.00663 -0.0496 0.5702 0.0434
-0.750 0.4450 0.01455 0.00664 -0.0495 0.5691 0.0467
-0.500 0.4699 0.01450 0.00666 -0.0493 0.5679 0.0560
-0.250 0.4941 0.01441 0.00667 -0.0489 0.5664 0.0758
0.000 0.5126 0.01414 0.00675 -0.0476 0.5649 0.1746
0.250 0.5313 0.01398 0.00678 -0.0462 0.5638 0.2359
0.500 0.5357 0.01355 0.00677 -0.0422 0.5629 0.3684
0.750 0.5381 0.01314 0.00662 -0.0378 0.5621 0.4544
1.000 0.5126 0.01234 0.00611 -0.0280 0.5611 0.5461
1.250 0.4768 0.01191 0.00582 -0.0155 0.5601 0.6071
1.500 0.4382 0.01155 0.00569 -0.0019 0.5592 0.6912
2.500 0.5597 0.01429 0.00881 -0.0034 0.5546 0.8545
2.750 0.5848 0.01472 0.00926 -0.0032 0.5534 0.8589
3.000 0.5810 0.01458 0.00911 0.0024 0.5521 0.8619
3.250 0.6074 0.01479 0.00934 0.0022 0.5507 0.8629
3.500 0.6405 0.01513 0.00970 0.0007 0.5493 0.8640
3.750 0.6692 0.01537 0.00996 0.0000 0.5479 0.8650
4.000 0.6991 0.01565 0.01025 -0.0009 0.5468 0.8664
4.250 0.7260 0.01583 0.01044 -0.0012 0.5455 0.8676
4.500 0.7447 0.01583 0.01042 0.0000 0.5441 0.8685
4.750 0.7620 0.01565 0.01021 0.0016 0.5424 0.8689
5.000 0.7834 0.01552 0.01004 0.0024 0.5409 0.8693
5.250 0.7000 0.01661 0.01126 0.0201 0.5359 0.8719
5.500 0.6716 0.01778 0.01246 0.0278 0.5313 0.8729
5.750 0.6917 0.01770 0.01233 0.0287 0.5281 0.8730
6.000 0.7209 0.01742 0.01200 0.0282 0.5263 0.8729
6.250 0.6267 0.02151 0.01619 0.0437 0.5153 0.8745
6.500 0.6512 0.02140 0.01604 0.0438 0.5132 0.8745
6.750 0.6772 0.02125 0.01588 0.0437 0.5119 0.8745
7.250 0.6401 0.02486 0.01951 0.0539 0.4981 0.8752
7.500 0.6552 0.02526 0.01989 0.0550 0.4947 0.8752
8.000 0.6592 0.02747 0.02210 0.0598 0.4830 0.8756
8.500 0.6662 0.02972 0.02436 0.0639 0.4706 0.8762
8.750 0.6938 0.02951 0.02413 0.0634 0.4680 0.8763
9.000 0.6935 0.03095 0.02558 0.0657 0.4606 0.8764
9.250 0.7118 0.03129 0.02591 0.0661 0.4553 0.8765
9.500 0.7396 0.03107 0.02566 0.0656 0.4519 0.8766
9.750 0.7431 0.03236 0.02696 0.0674 0.4437 0.8767
10.000 0.7661 0.03241 0.02697 0.0673 0.4375 0.8768
10.250 0.7750 0.03338 0.02795 0.0685 0.4296 0.8770
10.500 0.7933 0.03373 0.02825 0.0688 0.4218 0.8771
10.750 0.8030 0.03468 0.02918 0.0698 0.4124 0.8772
11.000 0.8174 0.03531 0.02976 0.0704 0.4043 0.8774
11.250 0.8271 0.03627 0.03070 0.0713 0.3939 0.8775
11.500 0.8366 0.03725 0.03163 0.0723 0.3829 0.8777
11.750 0.8435 0.03842 0.03274 0.0733 0.3719 0.8779
12.000 0.8480 0.03979 0.03406 0.0746 0.3589 0.8781
12.250 0.8544 0.04107 0.03529 0.0756 0.3472 0.8783
12.500 0.8549 0.04276 0.03690 0.0770 0.3308 0.8784
12.750 0.8567 0.04445 0.03854 0.0782 0.3183 0.8786
13.000 0.8647 0.04574 0.03980 0.0788 0.3087 0.8788
13.250 0.8722 0.04708 0.04112 0.0794 0.2988 0.8790
13.500 0.8776 0.04863 0.04264 0.0802 0.2887 0.8792
13.750 0.8856 0.05002 0.04402 0.0806 0.2788 0.8794
14.000 0.8871 0.05191 0.04585 0.0815 0.2631 0.8796
14.250 0.8891 0.05382 0.04770 0.0822 0.2501 0.8798
14.500 0.8913 0.05575 0.04957 0.0829 0.2397 0.8800
14.750 0.8974 0.05739 0.05119 0.0832 0.2307 0.8801
15.000 0.9059 0.05887 0.05266 0.0834 0.2255 0.8803
15.250 0.9166 0.06019 0.05401 0.0834 0.2216 0.8805
15.500 0.9282 0.06144 0.05529 0.0833 0.2176 0.8807
15.750 0.9390 0.06274 0.05662 0.0832 0.2137 0.8809
16.000 0.9454 0.06445 0.05831 0.0833 0.2074 0.8811
16.250 0.9578 0.06569 0.05960 0.0831 0.2020 0.8814
16.500 0.9661 0.06731 0.06123 0.0830 0.1957 0.8816
16.750 0.9734 0.06902 0.06295 0.0829 0.1881 0.8818
17.000 0.9781 0.07100 0.06490 0.0828 0.1708 0.8820
17.250 0.9575 0.07545 0.06910 0.0837 0.1295 0.8822
17.500 0.9539 0.07835 0.07194 0.0838 0.1188 0.8824
17.750 0.9549 0.08084 0.07442 0.0837 0.1114 0.8826
18.000 0.9616 0.08277 0.07640 0.0833 0.1081 0.8828
18.250 0.9637 0.08520 0.07885 0.0830 0.1038 0.8830
18.500 0.9682 0.08740 0.08108 0.0826 0.1003 0.8832
18.750 0.9785 0.08900 0.08275 0.0820 0.0983 0.8835
19.000 0.9834 0.09122 0.08502 0.0815 0.0932 0.8837
19.250 0.9859 0.09371 0.08752 0.0810 0.0885 0.8839
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