NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 500,000 Max Cl/Cd: 110.84 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0215f-il-500000.txt Download as CSV file: xf-nlf0215f-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1520 0.10511 0.10292 -0.0716 0.9866 0.0220
-11.250 -0.1418 0.10103 0.09883 -0.0747 0.9853 0.0226
-11.000 -0.2968 0.10853 0.10627 -0.0597 0.9957 0.0210
-10.750 -0.2796 0.10530 0.10303 -0.0628 0.9943 0.0213
-10.500 -0.2629 0.10227 0.10000 -0.0657 0.9920 0.0218
-10.250 -0.2505 0.09760 0.09533 -0.0702 0.9893 0.0221
-10.000 -0.1538 0.07113 0.06898 -0.0914 0.9516 0.0256
-9.750 -0.1448 0.06745 0.06529 -0.0931 0.9402 0.0259
-9.500 -0.1312 0.06301 0.06083 -0.0970 0.9314 0.0262
-9.250 -0.1161 0.05739 0.05518 -0.1032 0.9238 0.0268
-9.000 -0.1147 0.04722 0.04496 -0.1152 0.9165 0.0270
-8.750 -0.1186 0.03649 0.03401 -0.1304 0.9038 0.0273
-8.500 -0.1190 0.03065 0.02783 -0.1384 0.8714 0.0277
-8.250 -0.1299 0.02788 0.02474 -0.1387 0.8393 0.0283
-8.000 -0.1508 0.02538 0.02157 -0.1365 0.8143 0.0307
-7.750 -0.1594 0.02041 0.01625 -0.1354 0.7990 0.0313
-7.500 -0.1435 0.01849 0.01432 -0.1352 0.7871 0.0319
-7.250 -0.1282 0.01704 0.01275 -0.1347 0.7759 0.0326
-7.000 -0.1129 0.01560 0.01117 -0.1342 0.7655 0.0338
-6.750 -0.0939 0.01575 0.01079 -0.1328 0.7554 0.0373
-6.500 -0.0876 0.02106 0.01504 -0.1385 0.7660 0.0261
-6.250 -0.0639 0.01921 0.01305 -0.1379 0.7574 0.0235
-6.000 -0.0399 0.01794 0.01155 -0.1373 0.7492 0.0236
-5.750 -0.0157 0.01650 0.00988 -0.1366 0.7423 0.0228
-5.500 0.0086 0.01540 0.00861 -0.1358 0.7353 0.0223
-5.250 0.0335 0.01468 0.00777 -0.1353 0.7293 0.0225
-5.000 0.0583 0.01406 0.00711 -0.1348 0.7233 0.0227
-4.750 0.0834 0.01355 0.00655 -0.1344 0.7173 0.0234
-4.500 0.1096 0.01313 0.00603 -0.1343 0.7121 0.0241
-4.250 0.1358 0.01271 0.00559 -0.1343 0.7072 0.0247
-4.000 0.1628 0.01237 0.00521 -0.1344 0.7024 0.0253
-3.750 0.1902 0.01184 0.00465 -0.1348 0.6981 0.0272
-3.500 0.2188 0.01161 0.00438 -0.1353 0.6940 0.0293
-3.250 0.2472 0.01131 0.00406 -0.1357 0.6898 0.0313
-3.000 0.2760 0.01103 0.00376 -0.1361 0.6856 0.0363
-2.750 0.3070 0.01035 0.00341 -0.1376 0.6819 0.1243
-2.500 0.3463 0.00852 0.00331 -0.1426 0.6785 0.6198
-2.250 0.3743 0.00883 0.00361 -0.1423 0.6751 0.6677
-2.000 0.4017 0.00917 0.00392 -0.1419 0.6715 0.6849
-1.750 0.4273 0.00966 0.00440 -0.1408 0.6680 0.6999
-1.500 0.4522 0.01020 0.00491 -0.1396 0.6650 0.7130
-1.250 0.4772 0.01080 0.00548 -0.1383 0.6619 0.7260
-1.000 0.4958 0.01128 0.00605 -0.1353 0.6589 0.7332
-0.750 0.5219 0.01155 0.00630 -0.1347 0.6557 0.7426
-0.500 0.5453 0.01171 0.00647 -0.1333 0.6528 0.7456
-0.250 0.5726 0.01178 0.00649 -0.1332 0.6499 0.7480
0.000 0.6023 0.01186 0.00649 -0.1337 0.6470 0.7502
0.250 0.6320 0.01186 0.00646 -0.1344 0.6443 0.7525
0.500 0.6627 0.01184 0.00641 -0.1354 0.6414 0.7548
0.750 0.6941 0.01183 0.00636 -0.1366 0.6384 0.7568
1.000 0.7219 0.01178 0.00630 -0.1367 0.6355 0.7578
1.250 0.7504 0.01179 0.00628 -0.1370 0.6329 0.7587
1.500 0.7798 0.01189 0.00633 -0.1375 0.6299 0.7596
1.750 0.8068 0.01187 0.00635 -0.1375 0.6272 0.7606
2.000 0.8347 0.01187 0.00637 -0.1377 0.6240 0.7615
2.250 0.8631 0.01187 0.00637 -0.1380 0.6205 0.7624
2.500 0.8917 0.01189 0.00637 -0.1383 0.6170 0.7636
2.750 0.9212 0.01197 0.00641 -0.1389 0.6131 0.7645
3.000 0.9481 0.01192 0.00641 -0.1390 0.6086 0.7653
3.250 0.9759 0.01189 0.00638 -0.1392 0.6037 0.7662
3.500 1.0047 0.01192 0.00638 -0.1396 0.5992 0.7673
3.750 1.0326 0.01194 0.00643 -0.1399 0.5947 0.7682
4.000 1.0596 0.01191 0.00642 -0.1399 0.5893 0.7689
4.250 1.0874 0.01191 0.00641 -0.1402 0.5840 0.7696
4.500 1.1151 0.01195 0.00646 -0.1404 0.5789 0.7702
4.750 1.1418 0.01194 0.00650 -0.1404 0.5732 0.7711
5.000 1.1691 0.01198 0.00652 -0.1405 0.5674 0.7719
5.250 1.1949 0.01198 0.00658 -0.1404 0.5612 0.7724
5.500 1.2201 0.01195 0.00660 -0.1400 0.5542 0.7729
5.750 1.2454 0.01199 0.00664 -0.1397 0.5474 0.7734
6.000 1.2696 0.01198 0.00671 -0.1391 0.5386 0.7739
6.250 1.2939 0.01203 0.00678 -0.1386 0.5301 0.7745
6.500 1.3171 0.01209 0.00686 -0.1379 0.5196 0.7750
6.750 1.3398 0.01216 0.00698 -0.1371 0.5070 0.7757
7.000 1.3611 0.01228 0.00711 -0.1359 0.4919 0.7766
7.250 1.3798 0.01248 0.00727 -0.1344 0.4722 0.7774
7.500 1.3966 0.01278 0.00751 -0.1325 0.4459 0.7780
7.750 1.4071 0.01324 0.00784 -0.1294 0.4142 0.7787
8.000 1.4130 0.01389 0.00831 -0.1256 0.3781 0.7795
8.250 1.4188 0.01470 0.00894 -0.1219 0.3410 0.7802
8.500 1.4238 0.01560 0.00966 -0.1183 0.3067 0.7810
8.750 1.4291 0.01652 0.01044 -0.1148 0.2763 0.7818
9.000 1.4345 0.01746 0.01126 -0.1115 0.2496 0.7826
9.500 1.4455 0.01947 0.01309 -0.1054 0.2051 0.7841
9.750 1.4509 0.02056 0.01410 -0.1026 0.1862 0.7850
10.000 1.4557 0.02176 0.01524 -0.0999 0.1692 0.7859
10.250 1.4606 0.02302 0.01645 -0.0974 0.1543 0.7867
10.500 1.4659 0.02435 0.01774 -0.0951 0.1412 0.7873
10.750 1.4717 0.02571 0.01909 -0.0931 0.1299 0.7880
11.000 1.4766 0.02719 0.02057 -0.0912 0.1196 0.7887
11.250 1.4800 0.02887 0.02223 -0.0892 0.1099 0.7894
11.500 1.4869 0.03038 0.02378 -0.0878 0.1016 0.7901
11.750 1.4916 0.03212 0.02554 -0.0862 0.0944 0.7909
12.000 1.4966 0.03391 0.02733 -0.0849 0.0875 0.7917
12.250 1.5020 0.03573 0.02919 -0.0837 0.0813 0.7925
12.500 1.5065 0.03768 0.03114 -0.0826 0.0752 0.7933
12.750 1.5121 0.03960 0.03310 -0.0816 0.0701 0.7942
13.000 1.5176 0.04157 0.03510 -0.0807 0.0654 0.7950
13.250 1.5203 0.04387 0.03743 -0.0798 0.0611 0.7959
13.500 1.5282 0.04571 0.03935 -0.0792 0.0578 0.7968
13.750 1.5324 0.04796 0.04163 -0.0785 0.0545 0.7977
14.000 1.5341 0.05056 0.04427 -0.0779 0.0515 0.7986
14.250 1.5422 0.05251 0.04631 -0.0775 0.0491 0.7995
14.500 1.5470 0.05485 0.04871 -0.0772 0.0466 0.8005
14.750 1.5480 0.05768 0.05157 -0.0768 0.0440 0.8015
15.000 1.5529 0.06013 0.05411 -0.0766 0.0420 0.8025
15.250 1.5593 0.06243 0.05650 -0.0765 0.0398 0.8036
15.500 1.5626 0.06512 0.05924 -0.0764 0.0377 0.8046
15.750 1.5602 0.06861 0.06278 -0.0765 0.0356 0.8055
16.000 1.5678 0.07088 0.06517 -0.0766 0.0339 0.8066
16.250 1.5718 0.07364 0.06801 -0.0768 0.0320 0.8077
16.500 1.5714 0.07707 0.07149 -0.0771 0.0302 0.8087
16.750 1.5722 0.08038 0.07489 -0.0775 0.0285 0.8098
17.000 1.5756 0.08339 0.07801 -0.0780 0.0266 0.8110
17.250 1.5744 0.08712 0.08179 -0.0787 0.0249 0.8121
17.500 1.5715 0.09115 0.08592 -0.0795 0.0232 0.8132
17.750 1.5727 0.09466 0.08953 -0.0803 0.0216 0.8144
18.000 1.5685 0.09903 0.09396 -0.0815 0.0202 0.8155
18.250 1.5619 0.10386 0.09889 -0.0829 0.0189 0.8165
18.500 1.5607 0.10790 0.10305 -0.0842 0.0177 0.8176
18.750 1.5566 0.11245 0.10769 -0.0859 0.0167 0.8188
19.000 1.5473 0.11794 0.11327 -0.0880 0.0159 0.8198
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Polar data table (+)
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