NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 200,000 Max Cl/Cd: 53.37 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf414f-il-200000-n5.txt Download as CSV file: xf-nlf414f-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4305 0.11275 0.10857 -0.0465 0.8355 0.0193
-11.500 -0.4248 0.10976 0.10559 -0.0478 0.8352 0.0190
-11.250 -0.4220 0.10581 0.10165 -0.0499 0.8349 0.0187
-11.000 -0.4214 0.10117 0.09703 -0.0526 0.8346 0.0184
-10.750 -0.4235 0.09569 0.09157 -0.0560 0.8343 0.0180
-10.250 -0.5092 0.06344 0.05896 -0.0792 0.8331 0.0157
-10.000 -0.5218 0.05906 0.05442 -0.0811 0.8323 0.0157
-9.750 -0.5325 0.05507 0.05024 -0.0821 0.8311 0.0156
-9.500 -0.5421 0.05175 0.04669 -0.0818 0.8303 0.0156
-9.250 -0.5451 0.04812 0.04276 -0.0815 0.8296 0.0156
-9.000 -0.5446 0.04437 0.03862 -0.0809 0.8290 0.0156
-8.750 -0.5389 0.04113 0.03498 -0.0803 0.8283 0.0159
-8.500 -0.5224 0.03979 0.03355 -0.0803 0.8278 0.0162
-8.250 -0.5051 0.03846 0.03208 -0.0802 0.8273 0.0166
-8.000 -0.4887 0.03658 0.02994 -0.0798 0.8265 0.0171
-7.750 -0.4717 0.03434 0.02735 -0.0791 0.8258 0.0173
-7.500 -0.4525 0.03216 0.02481 -0.0785 0.8252 0.0173
-7.250 -0.4311 0.03036 0.02270 -0.0781 0.8248 0.0174
-7.000 -0.4076 0.02885 0.02093 -0.0779 0.8242 0.0176
-6.750 -0.3826 0.02756 0.01943 -0.0780 0.8235 0.0179
-6.500 -0.3573 0.02645 0.01816 -0.0781 0.8226 0.0182
-6.250 -0.3321 0.02551 0.01708 -0.0781 0.8214 0.0186
-6.000 -0.3073 0.02471 0.01618 -0.0780 0.8204 0.0191
-5.750 -0.2833 0.02401 0.01542 -0.0779 0.8194 0.0196
-5.500 -0.2598 0.02346 0.01489 -0.0777 0.8184 0.0202
-5.250 -0.2362 0.02301 0.01444 -0.0775 0.8172 0.0212
-5.000 -0.2125 0.02264 0.01401 -0.0773 0.8159 0.0228
-4.750 -0.1893 0.02221 0.01357 -0.0770 0.8148 0.0243
-4.500 -0.1659 0.02185 0.01321 -0.0768 0.8139 0.0259
-4.250 -0.1421 0.02151 0.01282 -0.0765 0.8129 0.0278
-4.000 -0.1181 0.02114 0.01243 -0.0761 0.8119 0.0304
-3.750 -0.0934 0.02084 0.01210 -0.0759 0.8110 0.0350
-3.500 -0.0687 0.02054 0.01184 -0.0757 0.8102 0.0448
-3.250 -0.0443 0.02021 0.01162 -0.0755 0.8096 0.0681
-3.000 -0.0240 0.01972 0.01162 -0.0757 0.8070 0.1671
-2.750 -0.0082 0.01837 0.01150 -0.0758 0.8039 0.4473
-2.500 -0.0002 0.01911 0.01338 -0.0702 0.8016 0.6676
-2.250 0.0289 0.01962 0.01374 -0.0708 0.7999 0.7263
-2.000 0.0516 0.02056 0.01462 -0.0689 0.7983 0.7610
-1.750 0.0681 0.02134 0.01545 -0.0649 0.7969 0.7821
-1.500 0.0933 0.02150 0.01554 -0.0643 0.7959 0.7900
-1.250 0.1198 0.02154 0.01550 -0.0639 0.7950 0.7928
-1.000 0.1474 0.02156 0.01546 -0.0639 0.7942 0.7959
-0.750 0.1650 0.02208 0.01595 -0.0636 0.7884 0.8001
-0.500 0.1901 0.02222 0.01604 -0.0637 0.7855 0.8036
-0.250 0.2146 0.02230 0.01609 -0.0632 0.7835 0.8060
0.000 0.2414 0.02232 0.01609 -0.0631 0.7819 0.8083
0.250 0.2697 0.02233 0.01606 -0.0633 0.7806 0.8102
0.500 0.2989 0.02231 0.01601 -0.0637 0.7796 0.8120
0.750 0.3288 0.02229 0.01596 -0.0643 0.7787 0.8137
1.250 0.3720 0.02297 0.01665 -0.0643 0.7682 0.8177
1.500 0.4011 0.02292 0.01659 -0.0647 0.7663 0.8187
1.750 0.4310 0.02279 0.01647 -0.0650 0.7649 0.8196
2.000 0.4614 0.02263 0.01633 -0.0654 0.7637 0.8205
2.250 0.4917 0.02249 0.01622 -0.0657 0.7626 0.8214
2.500 0.5044 0.02309 0.01687 -0.0647 0.7523 0.8225
2.750 0.5351 0.02292 0.01674 -0.0652 0.7505 0.8232
3.000 0.5665 0.02268 0.01654 -0.0657 0.7490 0.8242
3.500 0.6209 0.02199 0.01595 -0.0655 0.7354 0.8258
3.750 0.6434 0.02167 0.01569 -0.0649 0.7236 0.8265
4.000 0.6664 0.02125 0.01533 -0.0642 0.7107 0.8272
4.250 0.6869 0.02098 0.01511 -0.0632 0.6966 0.8283
4.750 0.7344 0.02042 0.01464 -0.0620 0.6596 0.8300
5.000 0.7901 0.01760 0.01172 -0.0636 0.6181 0.8300
5.250 0.8325 0.01560 0.00876 -0.0621 0.4844 0.8299
5.500 0.8312 0.01697 0.00962 -0.0585 0.3964 0.8308
5.750 0.8327 0.01852 0.01070 -0.0558 0.3126 0.8318
6.000 0.8387 0.01996 0.01169 -0.0536 0.2355 0.8327
6.250 0.8493 0.02112 0.01253 -0.0521 0.1805 0.8332
6.500 0.8641 0.02202 0.01323 -0.0509 0.1461 0.8335
6.750 0.8800 0.02283 0.01392 -0.0499 0.1202 0.8339
7.000 0.8969 0.02357 0.01456 -0.0489 0.0996 0.8344
7.250 0.9138 0.02431 0.01523 -0.0479 0.0839 0.8350
7.500 0.9309 0.02504 0.01592 -0.0470 0.0722 0.8355
7.750 0.9483 0.02579 0.01665 -0.0461 0.0640 0.8358
8.000 0.9648 0.02659 0.01742 -0.0452 0.0581 0.8360
8.250 0.9823 0.02733 0.01821 -0.0443 0.0541 0.8363
8.500 0.9990 0.02814 0.01904 -0.0434 0.0505 0.8366
8.750 1.0143 0.02906 0.01996 -0.0423 0.0476 0.8368
9.000 1.0314 0.02985 0.02083 -0.0414 0.0450 0.8371
9.250 1.0477 0.03071 0.02174 -0.0405 0.0428 0.8374
9.500 1.0624 0.03169 0.02274 -0.0395 0.0411 0.8377
9.750 1.0760 0.03279 0.02387 -0.0383 0.0397 0.8380
10.000 1.0918 0.03372 0.02490 -0.0373 0.0385 0.8385
10.250 1.1072 0.03469 0.02595 -0.0363 0.0371 0.8391
10.500 1.1224 0.03568 0.02700 -0.0353 0.0358 0.8396
10.750 1.1369 0.03673 0.02810 -0.0344 0.0346 0.8399
11.000 1.1500 0.03794 0.02933 -0.0333 0.0336 0.8401
11.250 1.1645 0.03912 0.03058 -0.0323 0.0328 0.8404
11.500 1.1797 0.04025 0.03183 -0.0313 0.0321 0.8407
11.750 1.1946 0.04143 0.03314 -0.0303 0.0313 0.8410
12.000 1.2091 0.04266 0.03448 -0.0294 0.0305 0.8413
12.250 1.2228 0.04393 0.03585 -0.0285 0.0298 0.8416
12.500 1.2355 0.04525 0.03725 -0.0276 0.0291 0.8420
12.750 1.2472 0.04663 0.03869 -0.0266 0.0284 0.8423
13.000 1.2587 0.04812 0.04024 -0.0257 0.0278 0.8426
13.250 1.2703 0.04979 0.04202 -0.0247 0.0273 0.8430
13.500 1.2800 0.05155 0.04399 -0.0237 0.0269 0.8433
13.750 1.2881 0.05347 0.04612 -0.0226 0.0265 0.8437
14.000 1.2945 0.05557 0.04842 -0.0215 0.0260 0.8440
14.250 1.2989 0.05786 0.05092 -0.0204 0.0257 0.8444
14.500 1.3010 0.06034 0.05361 -0.0193 0.0253 0.8447
14.750 1.3012 0.06302 0.05650 -0.0183 0.0250 0.8451
15.000 1.2997 0.06589 0.05957 -0.0175 0.0247 0.8454
15.250 1.2968 0.06897 0.06284 -0.0168 0.0244 0.8458
15.500 1.2924 0.07227 0.06632 -0.0164 0.0241 0.8461
15.750 1.2870 0.07580 0.07004 -0.0163 0.0239 0.8465
16.000 1.2805 0.07961 0.07401 -0.0165 0.0236 0.8468
16.250 1.2735 0.08364 0.07821 -0.0170 0.0234 0.8472
16.500 1.2649 0.08806 0.08279 -0.0179 0.0233 0.8476
16.750 1.2552 0.09282 0.08772 -0.0192 0.0231 0.8479
17.000 1.2432 0.09821 0.09327 -0.0210 0.0229 0.8482
17.250 1.2289 0.10427 0.09952 -0.0236 0.0228 0.8486
17.750 1.1871 0.12011 0.11581 -0.0320 0.0227 0.8493
18.000 1.1461 0.13393 0.12997 -0.0409 0.0228 0.8493
18.500 0.9650 0.20580 0.20221 -0.0838 0.0228 0.8472
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Polar data table (+)
Polar graphs
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