NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 200,000 Max Cl/Cd: 76.32 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0215f-il-200000.txt Download as CSV file: xf-nlf0215f-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(1)-0215F 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2699 0.09969 0.09642 -0.0625 0.9880 0.0507
-9.250 -0.2595 0.09344 0.09017 -0.0714 0.9820 0.0536
-9.000 -0.2769 0.08197 0.07865 -0.0922 0.9658 0.0549
-8.500 -0.2377 0.07345 0.07021 -0.0950 0.9532 0.0572
-8.250 -0.2218 0.06974 0.06648 -0.0985 0.9435 0.0589
-8.000 -0.2186 0.06417 0.06084 -0.1053 0.9310 0.0609
-7.750 -0.2136 0.05757 0.05400 -0.1154 0.9176 0.0638
-7.500 -0.2049 0.05032 0.04622 -0.1253 0.9069 0.0682
-7.250 -0.1761 0.04730 0.04324 -0.1277 0.8970 0.0706
-7.000 -0.1049 0.02699 0.02271 -0.1330 0.8624 0.0831
-6.750 -0.0867 0.02482 0.02044 -0.1336 0.8514 0.0876
-6.500 -0.0761 0.02168 0.01690 -0.1345 0.8410 0.0970
-6.250 -0.0578 0.01984 0.01501 -0.1343 0.8311 0.1012
-6.000 -0.0507 0.03345 0.02793 -0.1417 0.8440 0.1117
-5.750 -0.0205 0.02449 0.01740 -0.1388 0.8350 0.0439
-5.500 0.0089 0.02234 0.01493 -0.1392 0.8273 0.0420
-5.250 0.0335 0.02087 0.01320 -0.1384 0.8183 0.0412
-5.000 0.0622 0.01967 0.01178 -0.1384 0.8116 0.0410
-4.750 0.0873 0.01897 0.01097 -0.1378 0.8042 0.0429
-4.500 0.1142 0.01835 0.01021 -0.1375 0.7976 0.0446
-4.250 0.1411 0.01771 0.00947 -0.1372 0.7919 0.0453
-4.000 0.1623 0.01678 0.00862 -0.1360 0.7850 0.0470
-3.750 0.1887 0.01620 0.00803 -0.1359 0.7796 0.0499
-3.500 0.2147 0.01578 0.00758 -0.1359 0.7743 0.0541
-3.250 0.2402 0.01527 0.00710 -0.1360 0.7687 0.0635
-3.000 0.2716 0.01255 0.00622 -0.1400 0.7641 0.4776
-2.750 0.2891 0.01401 0.00816 -0.1354 0.7598 0.6799
-2.500 0.3072 0.01502 0.00915 -0.1319 0.7544 0.7048
-2.250 0.3217 0.01617 0.01029 -0.1270 0.7499 0.7287
-2.000 0.3335 0.01719 0.01129 -0.1210 0.7463 0.7497
-1.750 0.3483 0.01779 0.01185 -0.1167 0.7425 0.7670
-1.500 0.3635 0.01827 0.01231 -0.1131 0.7377 0.7874
-1.250 0.3771 0.01849 0.01250 -0.1087 0.7336 0.8033
-1.000 0.3960 0.01852 0.01246 -0.1058 0.7304 0.8140
-0.750 0.4204 0.01849 0.01233 -0.1051 0.7273 0.8214
-0.500 0.4389 0.01846 0.01230 -0.1034 0.7228 0.8274
-0.250 0.4675 0.01854 0.01230 -0.1046 0.7187 0.8328
0.000 0.4899 0.01835 0.01205 -0.1034 0.7155 0.8359
0.250 0.5184 0.01830 0.01191 -0.1037 0.7126 0.8389
0.500 0.5419 0.01833 0.01193 -0.1034 0.7088 0.8420
0.750 0.5670 0.01838 0.01197 -0.1036 0.7047 0.8446
1.000 0.5971 0.01845 0.01200 -0.1049 0.7011 0.8468
1.250 0.6270 0.01843 0.01191 -0.1058 0.6980 0.8485
1.500 0.6567 0.01842 0.01183 -0.1064 0.6953 0.8501
1.750 0.6765 0.01850 0.01199 -0.1054 0.6910 0.8516
2.000 0.7013 0.01857 0.01207 -0.1053 0.6869 0.8533
2.250 0.7309 0.01861 0.01209 -0.1062 0.6834 0.8543
2.500 0.7629 0.01866 0.01210 -0.1075 0.6805 0.8556
2.750 0.7902 0.01881 0.01228 -0.1080 0.6767 0.8569
3.000 0.8149 0.01897 0.01249 -0.1081 0.6718 0.8576
3.250 0.8453 0.01904 0.01256 -0.1091 0.6677 0.8585
3.500 0.8794 0.01906 0.01254 -0.1107 0.6641 0.8595
3.750 0.9064 0.01923 0.01277 -0.1112 0.6593 0.8602
4.000 0.9332 0.01934 0.01294 -0.1115 0.6536 0.8606
4.250 0.9674 0.01928 0.01285 -0.1131 0.6489 0.8612
4.500 0.9977 0.01936 0.01295 -0.1140 0.6435 0.8621
4.750 1.0226 0.01939 0.01306 -0.1139 0.6368 0.8627
5.000 1.0563 0.01925 0.01289 -0.1152 0.6318 0.8631
5.250 1.0807 0.01930 0.01302 -0.1149 0.6249 0.8635
5.500 1.1095 0.01917 0.01292 -0.1153 0.6180 0.8640
5.750 1.1404 0.01905 0.01281 -0.1160 0.6119 0.8648
6.000 1.1622 0.01904 0.01291 -0.1151 0.6040 0.8658
6.250 1.1974 0.01882 0.01263 -0.1166 0.5977 0.8663
6.500 1.2165 0.01885 0.01284 -0.1153 0.5886 0.8668
6.750 1.2502 0.01861 0.01256 -0.1164 0.5812 0.8673
7.000 1.2688 0.01860 0.01271 -0.1150 0.5711 0.8679
7.250 1.2948 0.01847 0.01263 -0.1148 0.5618 0.8685
7.500 1.3188 0.01832 0.01253 -0.1142 0.5512 0.8693
7.750 1.3371 0.01828 0.01261 -0.1126 0.5390 0.8705
8.000 1.3565 0.01822 0.01266 -0.1112 0.5258 0.8715
8.250 1.3744 0.01820 0.01272 -0.1096 0.5102 0.8722
8.500 1.3900 0.01825 0.01280 -0.1075 0.4920 0.8730
8.750 1.4012 0.01836 0.01292 -0.1047 0.4709 0.8738
9.000 1.4095 0.01871 0.01324 -0.1015 0.4437 0.8747
9.250 1.4148 0.01935 0.01374 -0.0980 0.4114 0.8756
9.500 1.4157 0.02031 0.01454 -0.0942 0.3756 0.8765
9.750 1.4125 0.02156 0.01562 -0.0900 0.3414 0.8775
10.000 1.4071 0.02303 0.01694 -0.0858 0.3105 0.8790
10.250 1.4016 0.02472 0.01850 -0.0821 0.2831 0.8805
10.500 1.3968 0.02660 0.02029 -0.0789 0.2579 0.8818
10.750 1.3937 0.02861 0.02222 -0.0764 0.2348 0.8829
11.000 1.3909 0.03078 0.02431 -0.0742 0.2143 0.8841
11.250 1.3887 0.03308 0.02653 -0.0723 0.1966 0.8853
11.500 1.3876 0.03543 0.02882 -0.0708 0.1807 0.8866
11.750 1.3879 0.03778 0.03113 -0.0696 0.1662 0.8878
12.000 1.3898 0.04009 0.03343 -0.0686 0.1533 0.8891
12.250 1.3929 0.04239 0.03573 -0.0678 0.1417 0.8904
12.500 1.3956 0.04475 0.03811 -0.0670 0.1318 0.8916
12.750 1.3962 0.04729 0.04058 -0.0661 0.1235 0.8929
13.000 1.4023 0.04939 0.04279 -0.0656 0.1151 0.8945
13.250 1.4049 0.05188 0.04523 -0.0649 0.1084 0.8961
13.500 1.4113 0.05406 0.04752 -0.0645 0.1017 0.8980
13.750 1.4150 0.05651 0.04991 -0.0640 0.0960 0.9000
14.000 1.4221 0.05873 0.05230 -0.0638 0.0905 0.9024
14.250 1.4269 0.06120 0.05474 -0.0636 0.0857 0.9047
14.500 1.4334 0.06345 0.05710 -0.0632 0.0811 0.9071
14.750 1.4382 0.06593 0.05968 -0.0632 0.0768 0.9098
15.000 1.4440 0.06825 0.06192 -0.0628 0.0723 0.9124
15.250 1.4477 0.07102 0.06492 -0.0631 0.0688 0.9159
15.500 1.4513 0.07377 0.06777 -0.0633 0.0653 0.9197
15.750 1.4565 0.07609 0.07003 -0.0629 0.0615 0.9242
16.000 1.4575 0.07910 0.07329 -0.0632 0.0589 0.9319
16.250 1.4573 0.08187 0.07622 -0.0632 0.0561 0.9652
16.500 1.4601 0.08498 0.07935 -0.0639 0.0533 1.0000
16.750 1.4642 0.08805 0.08252 -0.0645 0.0504 1.0000
17.000 1.4653 0.09174 0.08639 -0.0656 0.0478 1.0000
17.250 1.4666 0.09535 0.09006 -0.0669 0.0453 1.0000
17.500 1.4700 0.09849 0.09319 -0.0676 0.0426 1.0000
17.750 1.4673 0.10292 0.09786 -0.0693 0.0405 1.0000
18.000 1.4669 0.10695 0.10201 -0.0710 0.0384 1.0000
18.250 1.4689 0.11040 0.10544 -0.0723 0.0364 1.0000
18.500 1.4673 0.11455 0.10976 -0.0738 0.0345 1.0000
18.750 1.4631 0.11936 0.11478 -0.0760 0.0329 1.0000
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