NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 500,000 Max Cl/Cd: 85.28 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf415-il-500000.txt Download as CSV file: xf-nlf415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(2)-0415 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2281 0.08789 0.08508 -0.1439 0.9309 0.0188
-12.500 -0.2260 0.08325 0.08042 -0.1473 0.9270 0.0193
-12.250 -0.2359 0.07498 0.07210 -0.1537 0.9228 0.0194
-12.000 -0.2626 0.06633 0.06329 -0.1595 0.9183 0.0191
-11.250 -0.2461 0.04504 0.04195 -0.1526 0.9021 0.0212
-11.000 -0.2670 0.04115 0.03796 -0.1525 0.9001 0.0214
-10.750 -0.2870 0.03767 0.03438 -0.1518 0.8979 0.0212
-10.500 -0.3034 0.03516 0.03172 -0.1505 0.8956 0.0223
-10.250 -0.3204 0.03268 0.02909 -0.1485 0.8932 0.0225
-10.000 -0.3410 0.03344 0.02960 -0.1441 0.8900 0.0235
-9.750 -0.3562 0.03218 0.02817 -0.1399 0.8880 0.0236
-9.500 -0.3656 0.03050 0.02631 -0.1365 0.8864 0.0236
-6.750 -0.2309 0.02045 0.01397 -0.1289 0.8769 0.0241
-6.500 -0.1983 0.01880 0.01234 -0.1296 0.8767 0.0226
-6.250 -0.1733 0.01781 0.01132 -0.1291 0.8761 0.0223
-6.000 -0.1532 0.01716 0.01063 -0.1279 0.8753 0.0223
-5.750 -0.1361 0.01673 0.01017 -0.1264 0.8745 0.0227
-5.500 -0.1231 0.01633 0.00975 -0.1242 0.8736 0.0227
-5.250 -0.1110 0.01605 0.00945 -0.1219 0.8727 0.0231
-5.000 -0.0961 0.01595 0.00934 -0.1200 0.8717 0.0237
-4.750 -0.0884 0.01560 0.00896 -0.1169 0.8703 0.0240
-4.500 -0.0787 0.01534 0.00867 -0.1141 0.8688 0.0245
-4.250 -0.0655 0.01519 0.00848 -0.1119 0.8674 0.0250
-4.000 -0.0495 0.01504 0.00830 -0.1102 0.8660 0.0262
-3.750 -0.0324 0.01502 0.00825 -0.1086 0.8649 0.0276
-3.500 -0.0136 0.01503 0.00822 -0.1073 0.8640 0.0299
-3.250 0.0063 0.01500 0.00819 -0.1062 0.8631 0.0372
-3.000 0.0118 0.01263 0.00758 -0.1049 0.8619 0.5454
-2.750 -0.0433 0.01718 0.01038 -0.0866 0.8540 0.0417
-2.500 0.0069 0.01474 0.00969 -0.0934 0.8564 0.5899
-2.250 0.0534 0.01504 0.01007 -0.0968 0.8575 0.6097
-2.000 -0.0023 0.01673 0.01169 -0.0814 0.8488 0.6062
-1.750 0.0221 0.01713 0.01215 -0.0809 0.8480 0.6140
-1.500 0.0484 0.01749 0.01246 -0.0808 0.8474 0.6216
-1.250 0.0770 0.01772 0.01274 -0.0810 0.8468 0.6268
-1.000 0.1072 0.01810 0.01310 -0.0815 0.8463 0.6354
-0.750 0.1370 0.01817 0.01321 -0.0821 0.8459 0.6390
-0.500 0.1457 0.01883 0.01386 -0.0790 0.8431 0.6397
-0.250 0.1865 0.01865 0.01364 -0.0818 0.8438 0.6401
0.000 0.2252 0.01851 0.01349 -0.0843 0.8442 0.6405
0.250 0.2634 0.01840 0.01337 -0.0867 0.8446 0.6410
0.500 0.2172 0.01996 0.01493 -0.0735 0.8330 0.6419
0.750 0.2489 0.01998 0.01495 -0.0746 0.8323 0.6424
1.000 0.2803 0.02003 0.01499 -0.0756 0.8317 0.6430
1.250 0.3127 0.02006 0.01504 -0.0769 0.8312 0.6436
1.500 0.3458 0.02009 0.01508 -0.0782 0.8308 0.6443
1.750 0.3796 0.02012 0.01513 -0.0797 0.8304 0.6449
2.000 0.4288 0.01946 0.01451 -0.0837 0.8298 0.6456
2.250 0.5654 0.01525 0.01035 -0.1031 0.8291 0.6463
2.500 0.5338 0.01626 0.01137 -0.0917 0.8189 0.6474
2.750 0.6492 0.01356 0.00873 -0.1082 0.8197 0.6482
3.000 0.7318 0.01173 0.00689 -0.1186 0.8153 0.6489
3.250 0.7470 0.01143 0.00665 -0.1158 0.8064 0.6497
3.500 0.7844 0.01069 0.00591 -0.1174 0.7975 0.6504
3.750 0.8120 0.01007 0.00533 -0.1170 0.7854 0.6512
4.000 0.8220 0.00977 0.00510 -0.1130 0.7701 0.6521
4.250 0.8212 0.00963 0.00503 -0.1068 0.7484 0.6530
4.500 0.8017 0.00981 0.00452 -0.0962 0.6127 0.6538
4.750 0.7655 0.01135 0.00551 -0.0837 0.5073 0.6547
5.000 0.7407 0.01296 0.00661 -0.0743 0.4016 0.6556
5.250 0.7309 0.01441 0.00754 -0.0681 0.2963 0.6565
5.500 0.7338 0.01551 0.00823 -0.0643 0.2131 0.6575
5.750 0.7456 0.01627 0.00875 -0.0621 0.1624 0.6586
6.000 0.7609 0.01690 0.00923 -0.0604 0.1299 0.6597
6.250 0.7780 0.01744 0.00968 -0.0590 0.1074 0.6609
6.500 0.7961 0.01796 0.01013 -0.0577 0.0916 0.6621
6.750 0.8147 0.01846 0.01060 -0.0566 0.0802 0.6635
7.000 0.8327 0.01903 0.01113 -0.0554 0.0710 0.6648
7.250 0.8527 0.01945 0.01155 -0.0545 0.0639 0.6660
7.500 0.8713 0.01995 0.01207 -0.0534 0.0578 0.6673
7.750 0.8915 0.02035 0.01250 -0.0526 0.0528 0.6687
8.000 0.9086 0.02100 0.01316 -0.0513 0.0480 0.6701
8.250 0.9298 0.02135 0.01360 -0.0506 0.0452 0.6715
8.500 0.9499 0.02180 0.01408 -0.0498 0.0421 0.6731
8.750 0.9665 0.02256 0.01485 -0.0485 0.0379 0.6748
9.000 0.9885 0.02285 0.01521 -0.0480 0.0349 0.6766
9.250 1.0071 0.02345 0.01579 -0.0471 0.0300 0.6783
9.500 1.0281 0.02386 0.01623 -0.0465 0.0249 0.6801
9.750 1.0459 0.02459 0.01699 -0.0454 0.0201 0.6820
10.000 1.0615 0.02553 0.01795 -0.0441 0.0171 0.6839
10.250 1.0797 0.02623 0.01875 -0.0430 0.0157 0.6860
10.500 1.0970 0.02700 0.01960 -0.0420 0.0145 0.6883
10.750 1.1127 0.02795 0.02062 -0.0407 0.0136 0.6906
11.000 1.1244 0.02945 0.02221 -0.0390 0.0128 0.6930
11.250 1.1407 0.03043 0.02331 -0.0378 0.0125 0.6956
11.500 1.1559 0.03154 0.02457 -0.0365 0.0121 0.6984
11.750 1.1708 0.03272 0.02591 -0.0353 0.0118 0.7015
12.000 1.1851 0.03395 0.02728 -0.0340 0.0114 0.7049
12.250 1.1983 0.03531 0.02878 -0.0327 0.0111 0.7085
12.500 1.2104 0.03651 0.03009 -0.0313 0.0106 0.7121
12.750 1.2210 0.03796 0.03168 -0.0299 0.0103 0.7160
13.000 1.2303 0.03956 0.03342 -0.0284 0.0101 0.7204
13.250 1.2362 0.04178 0.03583 -0.0266 0.0098 0.7250
13.500 1.2384 0.04455 0.03886 -0.0247 0.0097 0.7294
13.750 1.2368 0.04761 0.04220 -0.0225 0.0096 0.7346
14.000 1.2314 0.05097 0.04585 -0.0203 0.0095 0.7401
14.250 1.2254 0.05403 0.04918 -0.0183 0.0095 0.7465
14.500 1.2178 0.05731 0.05271 -0.0166 0.0095 0.7543
14.750 1.2069 0.06103 0.05672 -0.0150 0.0094 0.7630
15.000 1.1938 0.06516 0.06113 -0.0138 0.0094 0.7737
15.250 1.1761 0.07015 0.06639 -0.0132 0.0094 0.7867
15.500 1.1586 0.07531 0.07186 -0.0133 0.0094 0.8071
15.750 1.1383 0.08097 0.07788 -0.0138 0.0094 0.8517
16.000 1.1090 0.08840 0.08569 -0.0157 0.0095 1.0000
16.250 1.0859 0.09651 0.09398 -0.0195 0.0095 1.0000
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Polar data table (+)
Polar graphs
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