NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 500,000 Max Cl/Cd: 80.9 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf414f-il-500000.txt Download as CSV file: xf-nlf414f-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4566 0.08013 0.07736 -0.0701 0.8355 0.0235
-10.250 -0.4764 0.07384 0.07096 -0.0752 0.8353 0.0235
-10.000 -0.4952 0.06900 0.06598 -0.0781 0.8349 0.0235
-9.750 -0.5118 0.06499 0.06181 -0.0801 0.8345 0.0235
-9.500 -0.5251 0.05955 0.05631 -0.0807 0.8342 0.0238
-9.250 -0.5191 0.05677 0.05351 -0.0812 0.8335 0.0240
-9.000 -0.5129 0.05427 0.05094 -0.0816 0.8329 0.0242
-8.750 -0.5045 0.05196 0.04855 -0.0820 0.8326 0.0245
-8.500 -0.4948 0.04961 0.04610 -0.0823 0.8322 0.0248
-8.250 -0.4836 0.04720 0.04354 -0.0825 0.8318 0.0254
-8.000 -0.4715 0.04453 0.04067 -0.0825 0.8312 0.0264
-7.750 -0.4697 0.03996 0.03534 -0.0809 0.8301 0.0290
-7.500 -0.4495 0.03781 0.03320 -0.0813 0.8295 0.0294
-7.250 -0.4289 0.03620 0.03152 -0.0815 0.8291 0.0301
-7.000 -0.4168 0.02762 0.02157 -0.0779 0.8284 0.0195
-6.750 -0.3922 0.02585 0.01970 -0.0778 0.8280 0.0191
-6.500 -0.3680 0.02431 0.01801 -0.0775 0.8274 0.0189
-6.250 -0.3432 0.02347 0.01699 -0.0771 0.8267 0.0191
-6.000 -0.3182 0.02276 0.01613 -0.0768 0.8261 0.0194
-5.750 -0.2934 0.02168 0.01499 -0.0764 0.8257 0.0195
-5.500 -0.2693 0.02089 0.01416 -0.0760 0.8252 0.0196
-5.250 -0.2465 0.02033 0.01360 -0.0754 0.8245 0.0199
-5.000 -0.2188 0.01968 0.01298 -0.0764 0.8228 0.0204
-4.750 -0.1926 0.01935 0.01267 -0.0770 0.8213 0.0211
-4.500 -0.1671 0.01910 0.01242 -0.0774 0.8199 0.0220
-4.250 -0.1417 0.01886 0.01217 -0.0775 0.8182 0.0231
-4.000 -0.1172 0.01848 0.01178 -0.0775 0.8166 0.0244
-3.750 -0.0916 0.01828 0.01159 -0.0775 0.8154 0.0265
-3.500 -0.0659 0.01806 0.01137 -0.0775 0.8143 0.0304
-3.250 -0.0401 0.01780 0.01115 -0.0774 0.8132 0.0396
-3.000 -0.0156 0.01716 0.01082 -0.0772 0.8122 0.1081
-2.750 0.0065 0.01578 0.01046 -0.0776 0.8113 0.3692
-2.500 0.0262 0.01505 0.01105 -0.0763 0.8105 0.6815
-2.250 0.0548 0.01567 0.01155 -0.0761 0.8099 0.7323
-2.000 0.0785 0.01676 0.01269 -0.0765 0.8039 0.7480
-1.750 0.1041 0.01732 0.01323 -0.0760 0.8015 0.7590
-1.500 0.1273 0.01782 0.01378 -0.0743 0.7997 0.7694
-1.250 0.1481 0.01854 0.01455 -0.0716 0.7983 0.7882
-1.000 0.1683 0.01881 0.01486 -0.0690 0.7971 0.7962
-0.750 0.1975 0.01887 0.01486 -0.0692 0.7963 0.8011
-0.500 0.2260 0.01880 0.01475 -0.0694 0.7955 0.8039
-0.250 0.2526 0.01875 0.01468 -0.0689 0.7948 0.8057
0.000 0.2798 0.01876 0.01467 -0.0685 0.7942 0.8076
0.250 0.2980 0.01938 0.01534 -0.0687 0.7846 0.8105
0.500 0.3267 0.01935 0.01529 -0.0689 0.7831 0.8135
0.750 0.3575 0.01926 0.01518 -0.0695 0.7819 0.8168
1.000 0.3885 0.01905 0.01494 -0.0700 0.7810 0.8186
1.250 0.4174 0.01876 0.01465 -0.0699 0.7802 0.8199
1.500 0.4467 0.01854 0.01443 -0.0699 0.7795 0.8209
1.750 0.4760 0.01833 0.01422 -0.0699 0.7788 0.8220
2.000 0.4958 0.01883 0.01478 -0.0701 0.7688 0.8235
2.250 0.5281 0.01824 0.01420 -0.0703 0.7672 0.8245
2.500 0.5628 0.01723 0.01318 -0.0704 0.7660 0.8255
2.750 0.5972 0.01620 0.01213 -0.0705 0.7648 0.8263
3.000 0.6312 0.01516 0.01107 -0.0706 0.7635 0.8270
3.250 0.6596 0.01477 0.01074 -0.0710 0.7551 0.8282
3.500 0.6940 0.01355 0.00950 -0.0712 0.7514 0.8289
3.750 0.7280 0.01248 0.00840 -0.0715 0.7485 0.8294
4.000 0.7567 0.01227 0.00828 -0.0721 0.7391 0.8300
4.250 0.7881 0.01166 0.00771 -0.0726 0.7315 0.8306
4.500 0.8167 0.01160 0.00775 -0.0733 0.7133 0.8314
4.750 0.8498 0.01054 0.00660 -0.0735 0.6791 0.8319
5.000 0.8673 0.01072 0.00604 -0.0713 0.5620 0.8323
5.250 0.8706 0.01239 0.00706 -0.0685 0.4417 0.8328
5.500 0.8713 0.01403 0.00818 -0.0658 0.3420 0.8333
5.750 0.8734 0.01545 0.00915 -0.0631 0.2562 0.8338
6.000 0.8833 0.01661 0.00992 -0.0613 0.1873 0.8345
6.250 0.8980 0.01746 0.01055 -0.0601 0.1465 0.8349
6.500 0.9146 0.01821 0.01113 -0.0591 0.1153 0.8351
6.750 0.9313 0.01896 0.01170 -0.0581 0.0884 0.8353
7.000 0.9481 0.01969 0.01230 -0.0570 0.0701 0.8354
7.250 0.9660 0.02035 0.01290 -0.0561 0.0602 0.8357
7.500 0.9843 0.02098 0.01353 -0.0552 0.0543 0.8362
7.750 1.0018 0.02167 0.01420 -0.0543 0.0498 0.8365
8.000 1.0193 0.02238 0.01493 -0.0533 0.0468 0.8366
8.250 1.0383 0.02298 0.01556 -0.0526 0.0443 0.8367
8.500 1.0553 0.02372 0.01629 -0.0516 0.0419 0.8367
8.750 1.0685 0.02473 0.01731 -0.0502 0.0398 0.8370
9.000 1.0868 0.02537 0.01801 -0.0493 0.0387 0.8374
9.250 1.1041 0.02609 0.01878 -0.0484 0.0373 0.8375
9.500 1.1210 0.02685 0.01957 -0.0475 0.0361 0.8375
9.750 1.1368 0.02769 0.02042 -0.0465 0.0350 0.8376
10.000 1.1489 0.02885 0.02159 -0.0449 0.0338 0.8376
10.250 1.1631 0.02987 0.02267 -0.0437 0.0329 0.8376
10.500 1.1803 0.03064 0.02351 -0.0428 0.0322 0.8376
10.750 1.1966 0.03150 0.02443 -0.0418 0.0314 0.8376
11.000 1.2125 0.03240 0.02538 -0.0409 0.0306 0.8377
11.250 1.2281 0.03332 0.02636 -0.0399 0.0299 0.8377
11.500 1.2432 0.03429 0.02737 -0.0389 0.0293 0.8378
11.750 1.2578 0.03534 0.02845 -0.0378 0.0287 0.8378
12.000 1.2726 0.03658 0.02971 -0.0367 0.0280 0.8378
12.250 1.2896 0.03799 0.03121 -0.0355 0.0274 0.8380
12.500 1.3029 0.03904 0.03238 -0.0345 0.0270 0.8383
12.750 1.3160 0.04020 0.03366 -0.0334 0.0265 0.8385
13.000 1.3291 0.04147 0.03504 -0.0324 0.0260 0.8386
13.250 1.3415 0.04282 0.03650 -0.0313 0.0256 0.8387
13.500 1.3530 0.04424 0.03802 -0.0302 0.0252 0.8387
13.750 1.3630 0.04577 0.03967 -0.0290 0.0248 0.8388
14.000 1.3716 0.04739 0.04140 -0.0278 0.0244 0.8389
14.250 1.3794 0.04908 0.04319 -0.0267 0.0241 0.8389
14.500 1.3861 0.05087 0.04507 -0.0255 0.0238 0.8390
14.750 1.3920 0.05278 0.04708 -0.0244 0.0235 0.8391
15.000 1.3972 0.05490 0.04930 -0.0232 0.0233 0.8392
15.250 1.4001 0.05750 0.05202 -0.0220 0.0230 0.8393
15.500 1.3963 0.06110 0.05583 -0.0205 0.0228 0.8394
15.750 1.3851 0.06528 0.06026 -0.0190 0.0226 0.8394
16.000 1.3753 0.06873 0.06391 -0.0181 0.0225 0.8395
16.250 1.3641 0.07253 0.06792 -0.0176 0.0225 0.8395
16.500 1.3511 0.07683 0.07242 -0.0175 0.0224 0.8396
16.750 1.3360 0.08173 0.07754 -0.0179 0.0223 0.8396
17.000 1.3186 0.08723 0.08325 -0.0190 0.0222 0.8397
17.250 1.2992 0.09346 0.08970 -0.0208 0.0221 0.8397
17.500 1.2767 0.10065 0.09710 -0.0235 0.0221 0.8397
17.750 1.2516 0.10886 0.10553 -0.0274 0.0221 0.8397
18.000 1.2228 0.11840 0.11529 -0.0327 0.0222 0.8396
18.250 1.1890 0.12989 0.12699 -0.0397 0.0223 0.8395
18.500 1.1434 0.14555 0.14287 -0.0502 0.0225 0.8393
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