NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.55 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf415-il-1000000-n5.txt Download as CSV file: xf-nlf415-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2734 0.08727 0.08456 -0.1407 0.8485 0.0054
-13.250 -0.3353 0.06755 0.06478 -0.1515 0.8463 0.0053
-13.000 -0.4073 0.05495 0.05194 -0.1550 0.8438 0.0052
-12.750 -0.4328 0.04988 0.04673 -0.1552 0.8422 0.0052
-12.500 -0.4603 0.04482 0.04149 -0.1544 0.8404 0.0053
-12.250 -0.4856 0.04005 0.03649 -0.1528 0.8385 0.0054
-12.000 -0.5258 0.03324 0.02924 -0.1492 0.8364 0.0058
-11.750 -0.5393 0.02922 0.02483 -0.1465 0.8347 0.0062
-11.500 -0.5354 0.02713 0.02247 -0.1449 0.8334 0.0065
-11.250 -0.5284 0.02543 0.02058 -0.1434 0.8322 0.0066
-11.000 -0.5173 0.02417 0.01914 -0.1423 0.8310 0.0067
-10.750 -0.5052 0.02286 0.01767 -0.1412 0.8299 0.0069
-10.500 -0.4903 0.02163 0.01631 -0.1402 0.8293 0.0069
-10.250 -0.4754 0.02086 0.01549 -0.1394 0.8285 0.0071
-10.000 -0.4586 0.02008 0.01464 -0.1386 0.8278 0.0072
-9.750 -0.4422 0.01949 0.01400 -0.1378 0.8270 0.0073
-9.500 -0.4244 0.01881 0.01326 -0.1370 0.8262 0.0075
-9.250 -0.4060 0.01814 0.01253 -0.1362 0.8255 0.0076
-9.000 -0.3878 0.01758 0.01192 -0.1354 0.8247 0.0078
-8.750 -0.3694 0.01697 0.01126 -0.1346 0.8240 0.0079
-8.500 -0.3516 0.01640 0.01064 -0.1336 0.8232 0.0081
-8.250 -0.3343 0.01590 0.01009 -0.1325 0.8223 0.0084
-8.000 -0.3186 0.01533 0.00948 -0.1312 0.8214 0.0086
-7.750 -0.3043 0.01489 0.00900 -0.1295 0.8205 0.0089
-7.500 -0.2906 0.01446 0.00853 -0.1276 0.8197 0.0091
-7.250 -0.2732 0.01404 0.00806 -0.1264 0.8190 0.0093
-7.000 -0.2551 0.01362 0.00759 -0.1254 0.8183 0.0095
-6.750 -0.2358 0.01324 0.00718 -0.1245 0.8176 0.0096
-6.500 -0.2179 0.01277 0.00667 -0.1234 0.8169 0.0097
-6.250 -0.2022 0.01214 0.00600 -0.1220 0.8161 0.0101
-6.000 -0.1817 0.01173 0.00556 -0.1213 0.8154 0.0103
-5.750 -0.1597 0.01140 0.00520 -0.1208 0.8150 0.0106
-5.500 -0.1373 0.01105 0.00484 -0.1204 0.8147 0.0108
-5.250 -0.1137 0.01077 0.00455 -0.1201 0.8143 0.0111
-5.000 -0.0892 0.01052 0.00430 -0.1200 0.8139 0.0116
-4.750 -0.0646 0.01027 0.00403 -0.1199 0.8134 0.0120
-4.500 -0.0394 0.01003 0.00377 -0.1199 0.8130 0.0125
-4.250 -0.0137 0.00983 0.00355 -0.1199 0.8126 0.0128
-4.000 0.0124 0.00965 0.00336 -0.1200 0.8122 0.0131
-3.750 0.0386 0.00946 0.00316 -0.1202 0.8118 0.0137
-3.500 0.0652 0.00930 0.00299 -0.1203 0.8113 0.0147
-3.250 0.0921 0.00916 0.00285 -0.1205 0.8109 0.0160
-3.000 0.1192 0.00904 0.00274 -0.1208 0.8105 0.0175
-2.750 0.1448 0.00872 0.00258 -0.1209 0.8099 0.0651
-2.500 0.1570 0.00648 0.00184 -0.1202 0.8090 0.5412
-2.250 0.1859 0.00655 0.00191 -0.1206 0.8087 0.5597
-2.000 0.2147 0.00658 0.00194 -0.1211 0.8083 0.5654
-1.750 0.2435 0.00661 0.00197 -0.1216 0.8079 0.5691
-1.500 0.2724 0.00668 0.00201 -0.1220 0.8076 0.5739
-1.250 0.3011 0.00672 0.00208 -0.1225 0.8072 0.5797
-1.000 0.3298 0.00674 0.00210 -0.1229 0.8068 0.5811
-0.750 0.3586 0.00675 0.00212 -0.1234 0.8065 0.5816
-0.500 0.3873 0.00677 0.00214 -0.1239 0.8062 0.5822
-0.250 0.4160 0.00678 0.00216 -0.1243 0.8058 0.5828
0.000 0.4447 0.00681 0.00220 -0.1248 0.8055 0.5835
0.250 0.4734 0.00683 0.00224 -0.1253 0.8052 0.5841
0.500 0.5023 0.00682 0.00223 -0.1257 0.8039 0.5847
0.750 0.5297 0.00674 0.00215 -0.1258 0.7991 0.5853
1.000 0.5549 0.00662 0.00205 -0.1253 0.7931 0.5859
1.250 0.5824 0.00655 0.00197 -0.1254 0.7887 0.5865
1.500 0.6087 0.00651 0.00195 -0.1252 0.7841 0.5870
1.750 0.6337 0.00646 0.00194 -0.1248 0.7781 0.5876
2.000 0.6598 0.00642 0.00189 -0.1245 0.7716 0.5882
2.250 0.6831 0.00637 0.00187 -0.1237 0.7597 0.5887
2.500 0.6926 0.00644 0.00175 -0.1196 0.6989 0.5892
2.750 0.6491 0.00753 0.00220 -0.1042 0.5732 0.5898
3.000 0.6167 0.00889 0.00301 -0.0920 0.4490 0.5902
3.500 0.6046 0.01090 0.00421 -0.0796 0.2587 0.5916
3.750 0.6145 0.01153 0.00462 -0.0766 0.2024 0.5924
4.000 0.6291 0.01203 0.00496 -0.0746 0.1627 0.5931
4.250 0.6469 0.01242 0.00526 -0.0730 0.1387 0.5939
4.500 0.6661 0.01276 0.00554 -0.0718 0.1204 0.5946
4.750 0.6859 0.01308 0.00583 -0.0707 0.1059 0.5954
5.000 0.7058 0.01341 0.00612 -0.0696 0.0935 0.5961
5.250 0.7260 0.01374 0.00641 -0.0686 0.0833 0.5970
5.750 0.7664 0.01442 0.00703 -0.0666 0.0631 0.5988
6.000 0.7872 0.01474 0.00734 -0.0657 0.0571 0.5998
6.250 0.8073 0.01510 0.00767 -0.0648 0.0501 0.6007
6.500 0.8282 0.01542 0.00799 -0.0639 0.0453 0.6015
6.750 0.8483 0.01581 0.00835 -0.0630 0.0389 0.6024
7.000 0.8694 0.01613 0.00869 -0.0622 0.0365 0.6032
7.250 0.8899 0.01649 0.00905 -0.0613 0.0333 0.6039
7.500 0.9100 0.01689 0.00943 -0.0604 0.0293 0.6047
7.750 0.9307 0.01724 0.00981 -0.0596 0.0273 0.6054
8.000 0.9513 0.01761 0.01019 -0.0588 0.0251 0.6064
8.250 0.9714 0.01802 0.01060 -0.0579 0.0218 0.6075
8.500 0.9915 0.01842 0.01103 -0.0571 0.0190 0.6086
8.750 1.0110 0.01888 0.01148 -0.0561 0.0158 0.6098
9.000 1.0297 0.01941 0.01201 -0.0551 0.0110 0.6109
9.250 1.0488 0.01993 0.01253 -0.0541 0.0089 0.6120
9.500 1.0679 0.02046 0.01309 -0.0532 0.0075 0.6133
9.750 1.0872 0.02098 0.01365 -0.0522 0.0068 0.6146
10.000 1.1066 0.02149 0.01420 -0.0514 0.0064 0.6159
10.250 1.1256 0.02203 0.01481 -0.0504 0.0061 0.6172
10.500 1.1442 0.02261 0.01543 -0.0495 0.0057 0.6184
10.750 1.1626 0.02322 0.01609 -0.0485 0.0055 0.6195
11.250 1.1985 0.02457 0.01756 -0.0465 0.0049 0.6223
11.500 1.2156 0.02532 0.01839 -0.0454 0.0048 0.6240
11.750 1.2332 0.02598 0.01913 -0.0445 0.0047 0.6259
12.000 1.2502 0.02668 0.01991 -0.0434 0.0046 0.6279
12.250 1.2663 0.02748 0.02080 -0.0423 0.0045 0.6299
12.500 1.2827 0.02824 0.02163 -0.0412 0.0043 0.6320
12.750 1.2979 0.02912 0.02259 -0.0401 0.0042 0.6339
13.000 1.3126 0.03001 0.02356 -0.0389 0.0041 0.6357
13.250 1.3262 0.03099 0.02464 -0.0376 0.0040 0.6380
13.500 1.3393 0.03202 0.02577 -0.0363 0.0039 0.6403
13.750 1.3518 0.03311 0.02696 -0.0350 0.0039 0.6428
14.000 1.3632 0.03426 0.02822 -0.0336 0.0038 0.6454
14.250 1.3738 0.03549 0.02955 -0.0322 0.0037 0.6481
14.500 1.3837 0.03679 0.03096 -0.0307 0.0037 0.6505
14.750 1.3917 0.03825 0.03253 -0.0292 0.0036 0.6535
15.000 1.3990 0.03981 0.03420 -0.0277 0.0035 0.6568
15.250 1.4041 0.04155 0.03607 -0.0261 0.0035 0.6602
15.500 1.4094 0.04331 0.03795 -0.0246 0.0034 0.6637
16.000 1.4112 0.04778 0.04271 -0.0215 0.0034 0.6709
16.250 1.4119 0.05012 0.04518 -0.0201 0.0033 0.6753
16.500 1.4093 0.05286 0.04807 -0.0188 0.0033 0.6796
16.750 1.4018 0.05626 0.05165 -0.0176 0.0032 0.6838
17.000 1.3948 0.05977 0.05532 -0.0167 0.0032 0.6887
17.250 1.3828 0.06409 0.05981 -0.0162 0.0032 0.6936
17.500 1.3740 0.06822 0.06411 -0.0162 0.0032 0.6992
17.750 1.3587 0.07357 0.06965 -0.0169 0.0032 0.7048
18.000 1.3371 0.08032 0.07660 -0.0186 0.0031 0.7099
18.250 1.3172 0.08744 0.08392 -0.0213 0.0031 0.7152
18.500 1.2996 0.09476 0.09141 -0.0248 0.0031 0.7214
18.750 1.2741 0.10450 0.10135 -0.0304 0.0031 0.7252
19.000 1.2434 0.11660 0.11366 -0.0379 0.0032 0.7265
19.250 1.2115 0.12966 0.12691 -0.0459 0.0032 0.7266
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Polar data table (+)
Polar graphs
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