NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.78 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0215f-il-1000000-n5.txt Download as CSV file: xf-nlf0215f-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2473 0.10327 0.10142 -0.0780 0.9452 0.0077
-11.500 -0.2301 0.09539 0.09350 -0.0873 0.9359 0.0077
-11.250 -0.4589 0.03102 0.02798 -0.1377 0.9174 0.0077
-11.000 -0.4246 0.02655 0.02286 -0.1479 0.8660 0.0079
-10.750 -0.4287 0.02526 0.02124 -0.1449 0.8233 0.0078
-10.500 -0.4274 0.02456 0.02032 -0.1421 0.7962 0.0079
-10.250 -0.4256 0.02293 0.01842 -0.1401 0.7763 0.0079
-10.000 -0.4128 0.02211 0.01742 -0.1388 0.7611 0.0080
-9.750 -0.4006 0.02092 0.01601 -0.1375 0.7481 0.0080
-9.500 -0.3881 0.01945 0.01430 -0.1363 0.7371 0.0081
-9.250 -0.3710 0.01847 0.01315 -0.1354 0.7273 0.0082
-9.000 -0.3525 0.01750 0.01203 -0.1346 0.7182 0.0083
-8.750 -0.3320 0.01678 0.01119 -0.1340 0.7103 0.0084
-8.500 -0.3099 0.01621 0.01052 -0.1336 0.7022 0.0085
-8.250 -0.2874 0.01566 0.00987 -0.1331 0.6950 0.0086
-8.000 -0.2642 0.01512 0.00924 -0.1328 0.6879 0.0087
-7.750 -0.2405 0.01468 0.00872 -0.1325 0.6813 0.0088
-7.500 -0.2161 0.01419 0.00815 -0.1323 0.6759 0.0089
-7.250 -0.1914 0.01377 0.00766 -0.1321 0.6704 0.0090
-6.750 -0.1409 0.01299 0.00677 -0.1319 0.6610 0.0094
-6.500 -0.1150 0.01264 0.00636 -0.1318 0.6564 0.0096
-6.250 -0.0891 0.01232 0.00598 -0.1318 0.6517 0.0099
-6.000 -0.0629 0.01198 0.00558 -0.1318 0.6477 0.0101
-5.750 -0.0361 0.01163 0.00519 -0.1319 0.6437 0.0103
-5.500 -0.0090 0.01134 0.00486 -0.1321 0.6395 0.0105
-5.250 0.0182 0.01109 0.00456 -0.1322 0.6358 0.0107
-5.000 0.0456 0.01088 0.00430 -0.1324 0.6325 0.0108
-4.750 0.0737 0.01047 0.00387 -0.1329 0.6296 0.0113
-4.500 0.1020 0.01022 0.00359 -0.1333 0.6265 0.0117
-4.250 0.1303 0.01003 0.00338 -0.1336 0.6231 0.0121
-4.000 0.1587 0.00986 0.00319 -0.1339 0.6198 0.0125
-3.750 0.1871 0.00972 0.00301 -0.1343 0.6166 0.0130
-3.500 0.2161 0.00956 0.00285 -0.1347 0.6143 0.0135
-3.250 0.2451 0.00944 0.00271 -0.1351 0.6117 0.0141
-3.000 0.2743 0.00928 0.00254 -0.1356 0.6089 0.0154
-2.750 0.3032 0.00918 0.00242 -0.1360 0.6060 0.0167
-2.500 0.3321 0.00909 0.00232 -0.1364 0.6032 0.0186
-2.250 0.3612 0.00897 0.00222 -0.1369 0.6006 0.0277
-2.000 0.3914 0.00875 0.00213 -0.1377 0.5986 0.0626
-1.750 0.4223 0.00844 0.00204 -0.1388 0.5962 0.1320
-1.500 0.4554 0.00789 0.00191 -0.1407 0.5936 0.2800
-1.250 0.4920 0.00704 0.00171 -0.1438 0.5911 0.5074
-1.000 0.5234 0.00683 0.00189 -0.1448 0.5886 0.6547
-0.750 0.5516 0.00702 0.00205 -0.1448 0.5860 0.6760
-0.500 0.5794 0.00724 0.00228 -0.1447 0.5839 0.6887
-0.250 0.6083 0.00736 0.00238 -0.1449 0.5819 0.6945
0.000 0.6373 0.00740 0.00239 -0.1452 0.5795 0.6956
0.250 0.6660 0.00742 0.00239 -0.1455 0.5770 0.6964
0.500 0.6946 0.00745 0.00240 -0.1457 0.5746 0.6971
0.750 0.7230 0.00750 0.00242 -0.1459 0.5721 0.6977
1.000 0.7511 0.00756 0.00245 -0.1461 0.5694 0.6982
1.250 0.7799 0.00758 0.00248 -0.1464 0.5672 0.6987
1.500 0.8085 0.00761 0.00252 -0.1466 0.5642 0.6993
1.750 0.8368 0.00766 0.00256 -0.1468 0.5602 0.6999
2.000 0.8644 0.00772 0.00260 -0.1469 0.5556 0.7004
2.250 0.8924 0.00778 0.00264 -0.1470 0.5506 0.7009
2.500 0.9204 0.00782 0.00268 -0.1471 0.5447 0.7014
2.750 0.9477 0.00790 0.00274 -0.1472 0.5392 0.7018
3.000 0.9755 0.00795 0.00279 -0.1473 0.5341 0.7023
3.250 1.0029 0.00802 0.00285 -0.1473 0.5267 0.7028
3.500 1.0298 0.00811 0.00293 -0.1473 0.5190 0.7033
3.750 1.0568 0.00820 0.00300 -0.1472 0.5105 0.7040
4.000 1.0835 0.00831 0.00309 -0.1471 0.5017 0.7047
4.250 1.1094 0.00844 0.00320 -0.1469 0.4900 0.7052
4.500 1.1346 0.00861 0.00332 -0.1465 0.4743 0.7057
4.750 1.1590 0.00883 0.00346 -0.1461 0.4554 0.7062
5.000 1.1813 0.00916 0.00368 -0.1452 0.4289 0.7067
5.250 1.2019 0.00959 0.00395 -0.1440 0.3968 0.7073
5.500 1.2217 0.01006 0.00427 -0.1427 0.3640 0.7078
5.750 1.2405 0.01058 0.00462 -0.1412 0.3311 0.7083
6.000 1.2579 0.01114 0.00502 -0.1395 0.2974 0.7087
6.250 1.2754 0.01166 0.00540 -0.1379 0.2690 0.7092
6.500 1.2918 0.01216 0.00578 -0.1359 0.2437 0.7097
6.750 1.3070 0.01262 0.00613 -0.1338 0.2217 0.7101
7.000 1.3213 0.01311 0.00653 -0.1315 0.2020 0.7105
7.250 1.3365 0.01359 0.00693 -0.1294 0.1846 0.7109
7.500 1.3510 0.01409 0.00737 -0.1272 0.1670 0.7115
7.750 1.3643 0.01465 0.00785 -0.1248 0.1498 0.7123
8.000 1.3789 0.01515 0.00832 -0.1228 0.1371 0.7130
8.250 1.3931 0.01567 0.00881 -0.1207 0.1267 0.7137
8.500 1.4069 0.01623 0.00933 -0.1186 0.1166 0.7142
8.750 1.4205 0.01680 0.00988 -0.1165 0.1072 0.7148
9.000 1.4336 0.01740 0.01048 -0.1144 0.0989 0.7154
9.250 1.4456 0.01808 0.01114 -0.1122 0.0912 0.7160
9.500 1.4590 0.01871 0.01178 -0.1103 0.0856 0.7165
9.750 1.4698 0.01949 0.01255 -0.1081 0.0790 0.7171
10.000 1.4818 0.02025 0.01332 -0.1062 0.0736 0.7177
10.250 1.4902 0.02124 0.01430 -0.1039 0.0662 0.7183
10.500 1.5009 0.02215 0.01522 -0.1020 0.0613 0.7190
10.750 1.5096 0.02323 0.01630 -0.1000 0.0564 0.7196
11.000 1.5204 0.02423 0.01734 -0.0984 0.0527 0.7202
11.250 1.5289 0.02544 0.01855 -0.0966 0.0487 0.7209
11.500 1.5380 0.02665 0.01979 -0.0951 0.0452 0.7215
11.750 1.5470 0.02793 0.02110 -0.0936 0.0419 0.7221
12.000 1.5541 0.02941 0.02258 -0.0921 0.0385 0.7227
12.250 1.5636 0.03074 0.02396 -0.0909 0.0362 0.7233
12.500 1.5718 0.03223 0.02548 -0.0896 0.0339 0.7239
12.750 1.5786 0.03389 0.02716 -0.0884 0.0314 0.7245
13.000 1.5874 0.03541 0.02873 -0.0874 0.0298 0.7250
13.250 1.5946 0.03711 0.03047 -0.0864 0.0277 0.7255
13.500 1.6008 0.03896 0.03235 -0.0854 0.0258 0.7260
13.750 1.6086 0.04069 0.03413 -0.0846 0.0245 0.7265
14.000 1.6159 0.04251 0.03600 -0.0839 0.0231 0.7271
14.250 1.6214 0.04454 0.03808 -0.0831 0.0214 0.7279
14.500 1.6273 0.04658 0.04017 -0.0824 0.0202 0.7286
14.750 1.6341 0.04858 0.04223 -0.0819 0.0189 0.7295
15.000 1.6389 0.05083 0.04453 -0.0814 0.0174 0.7302
15.250 1.6433 0.05316 0.04691 -0.0809 0.0161 0.7310
15.500 1.6485 0.05544 0.04925 -0.0805 0.0147 0.7318
15.750 1.6512 0.05807 0.05194 -0.0802 0.0132 0.7325
16.000 1.6550 0.06062 0.05454 -0.0800 0.0119 0.7332
16.250 1.6576 0.06337 0.05735 -0.0798 0.0106 0.7339
16.500 1.6594 0.06625 0.06029 -0.0798 0.0095 0.7345
16.750 1.6612 0.06920 0.06330 -0.0798 0.0084 0.7352
17.000 1.6620 0.07235 0.06652 -0.0800 0.0076 0.7359
17.250 1.6633 0.07548 0.06972 -0.0802 0.0070 0.7366
17.500 1.6642 0.07872 0.07304 -0.0805 0.0064 0.7372
17.750 1.6632 0.08226 0.07666 -0.0810 0.0060 0.7379
18.000 1.6635 0.08569 0.08017 -0.0815 0.0057 0.7385
18.250 1.6639 0.08915 0.08372 -0.0822 0.0054 0.7392
18.500 1.6630 0.09288 0.08754 -0.0830 0.0052 0.7398
18.750 1.6616 0.09671 0.09146 -0.0839 0.0050 0.7404
19.000 1.6595 0.10067 0.09551 -0.0850 0.0048 0.7409
19.250 1.6563 0.10488 0.09981 -0.0862 0.0047 0.7415
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