NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il) Reynolds number: 500,000 Max Cl/Cd: 67.58 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6h20-il-500000.txt Download as CSV file: xf-n6h20-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1387 0.10904 0.10521 -0.0570 0.6267 0.0324
-11.750 -0.1357 0.10590 0.10207 -0.0584 0.6260 0.0333
-11.500 -0.1815 0.09531 0.09155 -0.0670 0.6258 0.0354
-11.250 -0.1753 0.09260 0.08884 -0.0671 0.6250 0.0356
-11.000 -0.1686 0.09039 0.08664 -0.0673 0.6240 0.0358
-10.750 -0.1648 0.08767 0.08394 -0.0682 0.6235 0.0360
-10.500 -0.1601 0.08526 0.08156 -0.0689 0.6229 0.0364
-10.250 -0.1658 0.08155 0.07788 -0.0710 0.6223 0.0366
-10.000 -0.1738 0.07798 0.07433 -0.0725 0.6216 0.0369
-9.750 -0.1850 0.07446 0.07082 -0.0732 0.6207 0.0372
-9.500 -0.1994 0.07102 0.06737 -0.0729 0.6199 0.0376
-9.250 -0.2160 0.06771 0.06404 -0.0716 0.6191 0.0379
-9.000 -0.2330 0.06461 0.06091 -0.0691 0.6183 0.0384
-8.750 -0.3452 0.05542 0.05110 -0.0539 0.6178 0.0410
-8.500 -0.3291 0.05324 0.04902 -0.0537 0.6169 0.0413
-8.250 -0.3214 0.05176 0.04753 -0.0518 0.6160 0.0415
-8.000 -0.3119 0.05062 0.04637 -0.0499 0.6152 0.0418
-7.750 -0.3051 0.04915 0.04484 -0.0476 0.6143 0.0422
-7.500 -0.2964 0.04783 0.04346 -0.0455 0.6135 0.0428
-7.250 -0.2895 0.04611 0.04163 -0.0429 0.6128 0.0437
-7.000 -0.3183 0.04129 0.03606 -0.0331 0.6121 0.0475
-6.750 -0.2997 0.03958 0.03437 -0.0324 0.6114 0.0479
-6.500 -0.2828 0.03827 0.03302 -0.0312 0.6106 0.0484
-6.250 -0.2659 0.03712 0.03180 -0.0298 0.6098 0.0490
-6.000 -0.2499 0.03596 0.03052 -0.0282 0.6089 0.0501
-5.750 -0.2443 0.03716 0.03113 -0.0227 0.6078 0.0539
-5.500 -0.2334 0.02727 0.02027 -0.0189 0.6072 0.0411
-5.250 -0.2015 0.02580 0.01875 -0.0200 0.6064 0.0403
-5.000 -0.1674 0.02427 0.01709 -0.0214 0.6056 0.0400
-4.750 -0.1301 0.02308 0.01577 -0.0235 0.6047 0.0399
-4.500 -0.0908 0.02219 0.01477 -0.0259 0.6037 0.0401
-4.250 -0.0589 0.02184 0.01432 -0.0270 0.6027 0.0406
-4.000 0.0128 0.02037 0.01279 -0.0360 0.6018 0.0412
-3.750 0.0706 0.01955 0.01201 -0.0420 0.6009 0.0418
-3.500 0.1100 0.01923 0.01171 -0.0444 0.5999 0.0425
-3.250 0.1445 0.01901 0.01151 -0.0458 0.5989 0.0433
-3.000 0.1775 0.01882 0.01133 -0.0470 0.5980 0.0441
-2.750 0.2087 0.01867 0.01118 -0.0478 0.5972 0.0450
-2.500 0.2380 0.01856 0.01108 -0.0483 0.5964 0.0462
-2.250 0.2671 0.01842 0.01094 -0.0487 0.5957 0.0475
-2.000 0.2952 0.01825 0.01081 -0.0490 0.5950 0.0492
-1.750 0.3219 0.01818 0.01075 -0.0490 0.5943 0.0509
-1.500 0.3481 0.01812 0.01070 -0.0489 0.5937 0.0529
-1.250 0.3740 0.01806 0.01065 -0.0488 0.5930 0.0560
-1.000 0.3991 0.01811 0.01071 -0.0485 0.5921 0.0602
-0.750 0.4224 0.01831 0.01098 -0.0481 0.5909 0.0694
-0.500 0.4371 0.01818 0.01140 -0.0464 0.5896 0.1983
-0.250 0.4343 0.01806 0.01193 -0.0417 0.5878 0.3698
0.000 0.4211 0.01799 0.01226 -0.0350 0.5855 0.4787
0.250 0.3889 0.01769 0.01224 -0.0246 0.5833 0.5508
0.500 0.3526 0.01770 0.01236 -0.0128 0.5814 0.5913
0.750 0.3156 0.01763 0.01237 0.0000 0.5798 0.6322
1.000 0.7575 0.02446 0.01957 -0.0706 0.5820 0.9214
1.250 0.7945 0.02403 0.01910 -0.0728 0.5811 0.9226
1.500 0.8271 0.02376 0.01880 -0.0741 0.5802 0.9238
1.750 0.8571 0.02362 0.01864 -0.0750 0.5794 0.9249
2.000 0.8855 0.02354 0.01853 -0.0756 0.5786 0.9260
2.250 0.9133 0.02346 0.01843 -0.0761 0.5779 0.9274
2.500 0.9398 0.02350 0.01845 -0.0763 0.5772 0.9294
2.750 0.9202 0.02604 0.02097 -0.0671 0.5761 0.9355
3.000 0.9539 0.02537 0.02033 -0.0692 0.5747 0.9361
3.250 0.9814 0.02539 0.02045 -0.0705 0.5727 0.9366
3.500 1.0077 0.02535 0.02045 -0.0711 0.5704 0.9369
3.750 1.0340 0.02523 0.02035 -0.0716 0.5686 0.9372
4.000 1.0610 0.02480 0.01991 -0.0718 0.5669 0.9374
4.250 1.0867 0.02464 0.01975 -0.0719 0.5658 0.9376
4.500 1.1139 0.02424 0.01934 -0.0722 0.5646 0.9378
4.750 1.1420 0.02375 0.01883 -0.0724 0.5635 0.9380
5.000 1.1710 0.02318 0.01821 -0.0728 0.5623 0.9382
5.250 1.2001 0.02265 0.01762 -0.0731 0.5610 0.9383
5.500 1.2250 0.02264 0.01765 -0.0733 0.5590 0.9387
5.750 1.2459 0.02300 0.01813 -0.0734 0.5563 0.9393
6.000 1.2683 0.02320 0.01841 -0.0734 0.5541 0.9399
6.250 1.2923 0.02319 0.01844 -0.0735 0.5521 0.9405
6.500 1.3177 0.02304 0.01831 -0.0737 0.5505 0.9411
6.750 1.3451 0.02268 0.01796 -0.0740 0.5490 0.9417
7.000 1.3733 0.02227 0.01753 -0.0743 0.5476 0.9422
7.250 1.4029 0.02173 0.01696 -0.0748 0.5460 0.9427
7.500 1.4242 0.02188 0.01718 -0.0745 0.5436 0.9439
7.750 1.4314 0.02283 0.01827 -0.0724 0.5399 0.9475
8.000 1.4168 0.02402 0.01953 -0.0653 0.5369 0.9525
8.250 1.4448 0.02359 0.01913 -0.0661 0.5346 0.9529
8.500 1.4774 0.02284 0.01837 -0.0671 0.5322 0.9531
8.750 1.5076 0.02231 0.01783 -0.0679 0.5294 0.9535
9.000 1.4196 0.02725 0.02304 -0.0557 0.5195 0.9627
9.250 1.4165 0.02769 0.02346 -0.0503 0.5169 0.9679
9.500 1.4598 0.02645 0.02221 -0.0523 0.5150 0.9678
9.750 1.3893 0.03179 0.02769 -0.0446 0.5020 0.9720
10.000 1.3178 0.03764 0.03360 -0.0342 0.4892 0.9812
10.250 1.3574 0.03622 0.03218 -0.0358 0.4870 0.9814
10.500 1.3343 0.03943 0.03545 -0.0329 0.4746 0.9827
10.750 1.3733 0.03813 0.03414 -0.0344 0.4714 0.9831
11.000 1.3609 0.04099 0.03705 -0.0325 0.4594 0.9846
11.250 1.3665 0.04234 0.03841 -0.0315 0.4492 0.9859
11.500 1.3888 0.04218 0.03821 -0.0314 0.4415 0.9868
11.750 1.3840 0.04415 0.04019 -0.0293 0.4290 0.9881
12.000 1.3843 0.04543 0.04143 -0.0270 0.4167 0.9886
12.250 0.8826 0.03816 0.03347 0.0780 0.4316 0.9137
12.500 0.9153 0.03753 0.03282 0.0769 0.4268 0.9137
12.750 0.9157 0.03909 0.03438 0.0786 0.4160 0.9138
13.000 0.9379 0.03915 0.03440 0.0784 0.4086 0.9138
13.250 0.9449 0.04030 0.03553 0.0794 0.3984 0.9138
13.500 0.9552 0.04122 0.03643 0.0801 0.3880 0.9139
13.750 0.9694 0.04186 0.03701 0.0804 0.3783 0.9140
14.000 0.9728 0.04335 0.03848 0.0815 0.3667 0.9141
14.250 0.9791 0.04463 0.03973 0.0823 0.3557 0.9142
14.500 0.9857 0.04590 0.04094 0.0831 0.3441 0.9144
14.750 0.9909 0.04734 0.04234 0.0838 0.3326 0.9145
15.000 0.9944 0.04897 0.04397 0.0846 0.3217 0.9146
15.250 0.9977 0.05063 0.04558 0.0854 0.3096 0.9148
15.500 1.0023 0.05222 0.04712 0.0859 0.2989 0.9149
15.750 1.0021 0.05428 0.04916 0.0867 0.2853 0.9151
16.000 1.0046 0.05616 0.05100 0.0872 0.2724 0.9152
16.250 1.0080 0.05800 0.05280 0.0876 0.2613 0.9154
16.500 1.0082 0.06014 0.05490 0.0881 0.2510 0.9156
16.750 1.0138 0.06185 0.05661 0.0883 0.2418 0.9158
17.000 1.0186 0.06365 0.05837 0.0884 0.2341 0.9160
17.250 1.0236 0.06551 0.06025 0.0884 0.2263 0.9162
17.500 1.0284 0.06737 0.06208 0.0885 0.2194 0.9164
17.750 1.0360 0.06904 0.06379 0.0883 0.2118 0.9166
18.000 1.0379 0.07124 0.06596 0.0883 0.2037 0.9168
18.250 1.0436 0.07316 0.06793 0.0880 0.1939 0.9170
18.500 1.0432 0.07571 0.07046 0.0880 0.1769 0.9172
18.750 1.0188 0.08075 0.07525 0.0885 0.1363 0.9173
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