NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 200,000 Max Cl/Cd: 45.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf415-il-200000-n5.txt Download as CSV file: xf-nlf415-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1796 0.09170 0.08766 -0.1260 0.9207 0.0244
-12.750 -0.1969 0.07986 0.07579 -0.1308 0.9201 0.0177
-12.500 -0.2028 0.07402 0.06993 -0.1336 0.9190 0.0174
-12.250 -0.2956 0.07944 0.07521 -0.1363 0.9292 0.0173
-12.000 -0.3052 0.07361 0.06930 -0.1405 0.9260 0.0171
-11.750 -0.3177 0.06805 0.06362 -0.1442 0.9228 0.0169
-11.500 -0.3303 0.06299 0.05841 -0.1474 0.9197 0.0167
-11.250 -0.3428 0.05896 0.05424 -0.1490 0.9161 0.0165
-11.000 -0.3584 0.05536 0.05049 -0.1490 0.9119 0.0163
-10.750 -0.3724 0.05199 0.04693 -0.1486 0.9083 0.0162
-10.500 -0.3827 0.04897 0.04371 -0.1479 0.9052 0.0160
-10.250 -0.3945 0.04629 0.04082 -0.1459 0.9020 0.0160
-10.000 -0.4075 0.04428 0.03864 -0.1424 0.8983 0.0159
-9.750 -0.4173 0.04231 0.03646 -0.1387 0.8951 0.0159
-9.500 -0.4197 0.03999 0.03387 -0.1360 0.8928 0.0159
-9.250 -0.4165 0.03764 0.03124 -0.1338 0.8909 0.0158
-9.000 -0.4087 0.03547 0.02876 -0.1320 0.8895 0.0161
-8.750 -0.4008 0.03378 0.02678 -0.1297 0.8875 0.0167
-8.500 -0.3942 0.03251 0.02522 -0.1267 0.8850 0.0173
-8.250 -0.3824 0.03103 0.02345 -0.1245 0.8832 0.0175
-8.000 -0.3660 0.02954 0.02174 -0.1231 0.8818 0.0175
-7.750 -0.3468 0.02817 0.02016 -0.1220 0.8806 0.0176
-7.500 -0.3257 0.02703 0.01881 -0.1211 0.8795 0.0178
-7.250 -0.2978 0.02537 0.01708 -0.1213 0.8790 0.0182
-7.000 -0.2733 0.02434 0.01599 -0.1209 0.8783 0.0186
-6.750 -0.2517 0.02358 0.01521 -0.1200 0.8774 0.0190
-6.500 -0.2331 0.02304 0.01465 -0.1189 0.8765 0.0199
-6.250 -0.2151 0.02255 0.01413 -0.1176 0.8756 0.0211
-6.000 -0.1980 0.02202 0.01357 -0.1162 0.8747 0.0218
-5.750 -0.1917 0.02174 0.01325 -0.1127 0.8728 0.0220
-5.500 -0.2043 0.02195 0.01346 -0.1056 0.8687 0.0222
-5.250 -0.2040 0.02182 0.01330 -0.1011 0.8661 0.0225
-5.000 -0.1966 0.02154 0.01298 -0.0979 0.8642 0.0228
-4.750 -0.1843 0.02120 0.01259 -0.0958 0.8628 0.0233
-4.500 -0.1687 0.02078 0.01211 -0.0943 0.8617 0.0240
-4.250 -0.1484 0.02031 0.01155 -0.0937 0.8607 0.0250
-4.000 -0.1250 0.01994 0.01112 -0.0936 0.8600 0.0269
-3.750 -0.1737 0.02124 0.01244 -0.0793 0.8522 0.0260
-3.500 -0.1550 0.02108 0.01222 -0.0783 0.8504 0.0285
-3.250 -0.1337 0.02090 0.01201 -0.0777 0.8492 0.0335
-3.000 -0.1112 0.02069 0.01180 -0.0773 0.8483 0.0454
-2.750 -0.0944 0.01857 0.01165 -0.0781 0.8474 0.5592
-2.500 -0.0691 0.01925 0.01230 -0.0774 0.8466 0.5943
-2.250 -0.0419 0.01970 0.01271 -0.0771 0.8459 0.6092
-2.000 -0.0152 0.02026 0.01329 -0.0766 0.8453 0.6245
-1.750 -0.0217 0.02120 0.01423 -0.0706 0.8406 0.6289
-1.500 -0.0061 0.02168 0.01466 -0.0685 0.8379 0.6373
-1.250 0.0155 0.02190 0.01485 -0.0678 0.8364 0.6389
-1.000 0.0403 0.02201 0.01488 -0.0677 0.8351 0.6394
-0.750 0.0673 0.02207 0.01489 -0.0680 0.8339 0.6400
-0.500 0.0949 0.02214 0.01491 -0.0684 0.8329 0.6406
-0.250 0.1225 0.02223 0.01495 -0.0689 0.8321 0.6413
0.000 0.1515 0.02229 0.01498 -0.0696 0.8313 0.6420
0.250 0.1816 0.02234 0.01501 -0.0704 0.8307 0.6427
0.500 0.2119 0.02240 0.01505 -0.0713 0.8301 0.6435
1.000 0.2279 0.02340 0.01605 -0.0653 0.8208 0.6458
1.250 0.2554 0.02351 0.01616 -0.0657 0.8193 0.6469
1.500 0.2841 0.02361 0.01627 -0.0663 0.8181 0.6478
1.750 0.3137 0.02370 0.01637 -0.0671 0.8171 0.6487
2.000 0.3444 0.02377 0.01646 -0.0680 0.8163 0.6495
2.250 0.3757 0.02385 0.01657 -0.0691 0.8155 0.6504
2.750 0.3994 0.02468 0.01751 -0.0644 0.8050 0.6520
3.000 0.4292 0.02473 0.01764 -0.0651 0.8035 0.6528
3.250 0.4852 0.02359 0.01660 -0.0695 0.8013 0.6536
3.750 0.5354 0.02233 0.01548 -0.0677 0.7801 0.6554
4.000 0.5841 0.02089 0.01416 -0.0706 0.7740 0.6565
5.000 0.7184 0.01573 0.00809 -0.0696 0.4830 0.6619
5.250 0.6992 0.01754 0.00917 -0.0618 0.3527 0.6633
5.500 0.6970 0.01891 0.01004 -0.0574 0.2588 0.6645
6.000 0.7195 0.02064 0.01129 -0.0530 0.1576 0.6669
6.250 0.7358 0.02127 0.01185 -0.0516 0.1310 0.6680
6.500 0.7532 0.02187 0.01239 -0.0504 0.1120 0.6693
6.750 0.7713 0.02244 0.01294 -0.0492 0.0981 0.6706
7.000 0.7898 0.02301 0.01351 -0.0482 0.0874 0.6721
7.250 0.8087 0.02356 0.01413 -0.0472 0.0793 0.6737
7.500 0.8267 0.02422 0.01477 -0.0461 0.0719 0.6753
7.750 0.8463 0.02476 0.01540 -0.0453 0.0658 0.6771
8.000 0.8644 0.02546 0.01611 -0.0442 0.0609 0.6789
8.500 0.9024 0.02670 0.01754 -0.0424 0.0523 0.6824
8.750 0.9200 0.02746 0.01831 -0.0413 0.0477 0.6842
9.000 0.9406 0.02793 0.01891 -0.0407 0.0426 0.6865
9.250 0.9588 0.02864 0.01962 -0.0399 0.0379 0.6888
9.500 0.9790 0.02920 0.02033 -0.0392 0.0336 0.6915
9.750 0.9973 0.02996 0.02112 -0.0384 0.0299 0.6941
10.000 1.0160 0.03072 0.02202 -0.0375 0.0266 0.6965
10.250 1.0336 0.03154 0.02292 -0.0366 0.0234 0.6988
10.500 1.0503 0.03257 0.02408 -0.0355 0.0208 0.7014
10.750 1.0670 0.03357 0.02521 -0.0345 0.0186 0.7043
11.000 1.0820 0.03470 0.02642 -0.0334 0.0173 0.7075
11.500 1.1130 0.03709 0.02917 -0.0312 0.0147 0.7139
11.750 1.1270 0.03825 0.03046 -0.0301 0.0138 0.7175
12.000 1.1387 0.03964 0.03197 -0.0288 0.0131 0.7216
12.500 1.1598 0.04317 0.03595 -0.0260 0.0121 0.7299
12.750 1.1682 0.04513 0.03818 -0.0245 0.0117 0.7349
13.250 1.1788 0.04952 0.04310 -0.0212 0.0111 0.7463
13.500 1.1804 0.05199 0.04582 -0.0195 0.0109 0.7532
13.750 1.1795 0.05469 0.04879 -0.0178 0.0107 0.7605
14.000 1.1763 0.05760 0.05197 -0.0162 0.0105 0.7691
14.250 1.1705 0.06078 0.05542 -0.0147 0.0104 0.7789
14.500 1.1617 0.06440 0.05933 -0.0134 0.0103 0.7904
14.750 1.1509 0.06830 0.06351 -0.0125 0.0102 0.8053
15.000 1.1372 0.07266 0.06817 -0.0119 0.0101 0.8268
15.250 1.1187 0.07720 0.07313 -0.0111 0.0101 0.9015
15.500 1.0959 0.08342 0.07963 -0.0123 0.0101 1.0000
15.750 1.0714 0.09120 0.08768 -0.0153 0.0102 1.0000
16.000 1.0396 0.10167 0.09843 -0.0209 0.0102 1.0000
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Polar data table (+)
Polar graphs
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