NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 200,000 Max Cl/Cd: 76.86 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0215f-il-200000-n5.txt Download as CSV file: xf-nlf0215f-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2498 0.08820 0.08461 -0.0773 0.9582 0.0214
-9.500 -0.2474 0.08329 0.07972 -0.0806 0.9439 0.0210
-9.000 -0.2876 0.05605 0.05216 -0.1059 0.9118 0.0177
-8.750 -0.2904 0.04962 0.04543 -0.1131 0.8946 0.0176
-8.500 -0.2779 0.04374 0.03915 -0.1205 0.8790 0.0175
-8.250 -0.2660 0.03812 0.03290 -0.1252 0.8627 0.0177
-8.000 -0.2474 0.03427 0.02855 -0.1281 0.8474 0.0181
-7.750 -0.2213 0.03258 0.02672 -0.1303 0.8333 0.0186
-7.500 -0.2005 0.03010 0.02384 -0.1312 0.8197 0.0188
-7.250 -0.1804 0.02742 0.02064 -0.1315 0.8074 0.0187
-7.000 -0.1578 0.02546 0.01828 -0.1316 0.7963 0.0187
-6.750 -0.1349 0.02394 0.01648 -0.1314 0.7861 0.0189
-6.500 -0.1101 0.02262 0.01488 -0.1314 0.7775 0.0190
-6.250 -0.0862 0.02150 0.01355 -0.1310 0.7687 0.0193
-6.000 -0.0609 0.02052 0.01237 -0.1308 0.7612 0.0197
-5.750 -0.0368 0.01965 0.01135 -0.1303 0.7532 0.0200
-5.250 0.0124 0.01820 0.00965 -0.1293 0.7395 0.0211
-5.000 0.0376 0.01769 0.00900 -0.1290 0.7334 0.0221
-4.750 0.0621 0.01708 0.00839 -0.1288 0.7282 0.0233
-4.500 0.0867 0.01661 0.00789 -0.1285 0.7225 0.0245
-4.250 0.1123 0.01614 0.00736 -0.1284 0.7174 0.0255
-4.000 0.1388 0.01572 0.00684 -0.1285 0.7129 0.0266
-3.750 0.1648 0.01530 0.00638 -0.1286 0.7076 0.0281
-3.500 0.1919 0.01497 0.00600 -0.1289 0.7028 0.0303
-3.250 0.2200 0.01469 0.00565 -0.1292 0.6989 0.0347
-2.750 0.2763 0.01378 0.00504 -0.1306 0.6908 0.1101
-2.500 0.3069 0.01281 0.00476 -0.1327 0.6868 0.2964
-2.250 0.3266 0.01275 0.00604 -0.1305 0.6833 0.6469
-2.000 0.3539 0.01350 0.00667 -0.1297 0.6798 0.6918
-1.750 0.3757 0.01419 0.00734 -0.1274 0.6760 0.7127
-1.500 0.3957 0.01478 0.00792 -0.1248 0.6725 0.7282
-1.250 0.4169 0.01511 0.00820 -0.1226 0.6691 0.7354
-1.000 0.4480 0.01513 0.00808 -0.1236 0.6661 0.7407
-0.750 0.4765 0.01513 0.00799 -0.1240 0.6628 0.7432
-0.500 0.5029 0.01515 0.00798 -0.1238 0.6594 0.7449
-0.250 0.5301 0.01517 0.00794 -0.1238 0.6561 0.7466
0.000 0.5583 0.01519 0.00789 -0.1240 0.6530 0.7483
0.250 0.5877 0.01522 0.00784 -0.1246 0.6502 0.7501
0.500 0.6168 0.01524 0.00782 -0.1252 0.6474 0.7520
0.750 0.6456 0.01526 0.00782 -0.1257 0.6439 0.7539
1.000 0.6755 0.01528 0.00780 -0.1266 0.6406 0.7558
1.250 0.7063 0.01530 0.00778 -0.1276 0.6376 0.7573
1.500 0.7350 0.01535 0.00778 -0.1280 0.6349 0.7583
1.750 0.7633 0.01541 0.00782 -0.1283 0.6322 0.7593
2.000 0.7898 0.01547 0.00792 -0.1283 0.6287 0.7602
2.250 0.8173 0.01553 0.00800 -0.1285 0.6253 0.7610
2.500 0.8453 0.01559 0.00807 -0.1287 0.6220 0.7619
2.750 0.8739 0.01566 0.00813 -0.1291 0.6190 0.7631
3.000 0.9027 0.01575 0.00822 -0.1296 0.6160 0.7641
3.250 0.9289 0.01583 0.00837 -0.1296 0.6116 0.7650
3.500 0.9563 0.01589 0.00846 -0.1298 0.6072 0.7659
3.750 0.9848 0.01594 0.00851 -0.1301 0.6029 0.7668
4.000 1.0117 0.01602 0.00862 -0.1302 0.5978 0.7680
4.250 1.0375 0.01607 0.00873 -0.1301 0.5914 0.7692
4.500 1.0659 0.01610 0.00875 -0.1304 0.5858 0.7701
4.750 1.0909 0.01618 0.00891 -0.1302 0.5791 0.7709
5.000 1.1171 0.01622 0.00898 -0.1301 0.5723 0.7718
5.250 1.1429 0.01628 0.00908 -0.1299 0.5649 0.7726
5.500 1.1669 0.01633 0.00920 -0.1294 0.5568 0.7732
5.750 1.1906 0.01640 0.00934 -0.1288 0.5489 0.7740
6.000 1.2136 0.01647 0.00947 -0.1280 0.5400 0.7749
6.250 1.2356 0.01657 0.00967 -0.1270 0.5300 0.7758
6.500 1.2575 0.01666 0.00981 -0.1261 0.5192 0.7766
6.750 1.2784 0.01677 0.00996 -0.1250 0.5065 0.7773
7.000 1.2979 0.01692 0.01016 -0.1236 0.4910 0.7782
7.250 1.3158 0.01712 0.01039 -0.1219 0.4718 0.7790
7.500 1.3307 0.01739 0.01062 -0.1197 0.4485 0.7799
7.750 1.3409 0.01777 0.01092 -0.1166 0.4220 0.7809
8.000 1.3474 0.01836 0.01138 -0.1131 0.3917 0.7819
8.250 1.3512 0.01919 0.01206 -0.1093 0.3593 0.7829
8.500 1.3533 0.02019 0.01291 -0.1055 0.3283 0.7841
8.750 1.3554 0.02128 0.01389 -0.1019 0.3007 0.7854
9.000 1.3567 0.02251 0.01501 -0.0985 0.2755 0.7867
9.250 1.3592 0.02380 0.01622 -0.0954 0.2523 0.7878
9.500 1.3604 0.02520 0.01756 -0.0925 0.2322 0.7886
9.750 1.3628 0.02664 0.01898 -0.0899 0.2138 0.7894
10.000 1.3655 0.02818 0.02050 -0.0876 0.1968 0.7902
10.250 1.3685 0.02980 0.02211 -0.0855 0.1814 0.7911
10.500 1.3718 0.03151 0.02380 -0.0837 0.1675 0.7920
10.750 1.3752 0.03331 0.02560 -0.0820 0.1547 0.7929
11.000 1.3785 0.03520 0.02749 -0.0805 0.1434 0.7939
11.250 1.3840 0.03701 0.02934 -0.0794 0.1326 0.7948
11.500 1.3893 0.03889 0.03126 -0.0783 0.1237 0.7958
11.750 1.3929 0.04099 0.03336 -0.0772 0.1154 0.7968
12.000 1.3996 0.04287 0.03531 -0.0764 0.1076 0.7978
12.250 1.4037 0.04503 0.03750 -0.0756 0.1010 0.7988
12.500 1.4098 0.04707 0.03960 -0.0750 0.0943 0.7999
12.750 1.4136 0.04939 0.04194 -0.0743 0.0889 0.8009
13.000 1.4203 0.05147 0.04413 -0.0739 0.0836 0.8021
13.500 1.4291 0.05618 0.04897 -0.0730 0.0748 0.8043
13.750 1.4341 0.05854 0.05142 -0.0726 0.0706 0.8054
14.000 1.4361 0.06129 0.05421 -0.0724 0.0670 0.8065
14.250 1.4416 0.06368 0.05672 -0.0722 0.0638 0.8077
14.500 1.4464 0.06622 0.05936 -0.0721 0.0605 0.8088
14.750 1.4485 0.06914 0.06234 -0.0721 0.0573 0.8099
15.000 1.4518 0.07195 0.06525 -0.0722 0.0543 0.8111
15.250 1.4567 0.07462 0.06803 -0.0724 0.0510 0.8124
15.500 1.4583 0.07776 0.07123 -0.0727 0.0480 0.8136
15.750 1.4600 0.08094 0.07449 -0.0731 0.0454 0.8148
16.000 1.4642 0.08383 0.07752 -0.0736 0.0427 0.8162
16.250 1.4656 0.08718 0.08095 -0.0742 0.0404 0.8175
16.500 1.4637 0.09102 0.08485 -0.0750 0.0385 0.8187
16.750 1.4666 0.09417 0.08818 -0.0756 0.0366 0.8199
17.000 1.4679 0.09761 0.09176 -0.0764 0.0347 0.8213
17.250 1.4669 0.10144 0.09570 -0.0775 0.0330 0.8227
17.500 1.4634 0.10575 0.10009 -0.0789 0.0315 0.8241
17.750 1.4640 0.10945 0.10394 -0.0800 0.0299 0.8257
18.000 1.4634 0.11340 0.10804 -0.0815 0.0283 0.8274
18.250 1.4608 0.11774 0.11250 -0.0832 0.0269 0.8291
18.500 1.4559 0.12251 0.11737 -0.0852 0.0258 0.8308
18.750 1.4527 0.12704 0.12203 -0.0872 0.0247 0.8326
19.000 1.4501 0.13148 0.12664 -0.0893 0.0234 0.8344
19.250 1.4461 0.13622 0.13152 -0.0916 0.0223 0.8363
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