NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 500,000 Max Cl/Cd: 82.68 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf415-il-500000-n5.txt Download as CSV file: xf-nlf415-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2521 0.08587 0.08261 -0.1417 0.8775 0.0081
-12.750 -0.2676 0.07639 0.07310 -0.1473 0.8751 0.0081
-12.500 -0.2999 0.06674 0.06336 -0.1524 0.8725 0.0081
-12.250 -0.3187 0.06161 0.05814 -0.1543 0.8699 0.0084
-12.000 -0.3500 0.05565 0.05203 -0.1551 0.8669 0.0079
-11.750 -0.3688 0.05168 0.04792 -0.1549 0.8645 0.0079
-11.500 -0.3823 0.04847 0.04456 -0.1543 0.8623 0.0083
-11.250 -0.3971 0.04519 0.04111 -0.1531 0.8601 0.0083
-11.000 -0.4139 0.04170 0.03742 -0.1511 0.8581 0.0084
-10.750 -0.4301 0.03817 0.03366 -0.1483 0.8561 0.0086
-10.500 -0.4393 0.03542 0.03070 -0.1456 0.8541 0.0085
-10.250 -0.4477 0.03214 0.02710 -0.1423 0.8522 0.0088
-10.000 -0.4484 0.02968 0.02435 -0.1395 0.8507 0.0090
-9.750 -0.4430 0.02751 0.02187 -0.1371 0.8493 0.0092
-9.500 -0.4318 0.02587 0.01995 -0.1354 0.8482 0.0094
-9.250 -0.4167 0.02448 0.01832 -0.1342 0.8473 0.0095
-9.000 -0.3958 0.02280 0.01643 -0.1339 0.8465 0.0098
-8.750 -0.3698 0.02144 0.01496 -0.1344 0.8460 0.0100
-8.500 -0.3508 0.02077 0.01423 -0.1337 0.8451 0.0104
-8.250 -0.3325 0.02022 0.01363 -0.1328 0.8442 0.0108
-8.000 -0.3101 0.01948 0.01283 -0.1325 0.8435 0.0111
-7.750 -0.2863 0.01872 0.01200 -0.1322 0.8427 0.0114
-7.500 -0.2640 0.01803 0.01126 -0.1316 0.8420 0.0117
-7.250 -0.2449 0.01743 0.01059 -0.1305 0.8412 0.0121
-7.000 -0.2288 0.01690 0.01002 -0.1289 0.8404 0.0123
-6.750 -0.2128 0.01641 0.00949 -0.1274 0.8395 0.0126
-6.500 -0.1966 0.01593 0.00897 -0.1260 0.8386 0.0128
-6.250 -0.1798 0.01549 0.00850 -0.1247 0.8377 0.0130
-6.000 -0.1626 0.01506 0.00802 -0.1234 0.8369 0.0132
-5.750 -0.1490 0.01441 0.00736 -0.1217 0.8360 0.0138
-5.500 -0.1318 0.01391 0.00684 -0.1205 0.8352 0.0142
-5.250 -0.1118 0.01352 0.00643 -0.1197 0.8345 0.0149
-5.000 -0.0907 0.01316 0.00604 -0.1191 0.8339 0.0152
-4.750 -0.0685 0.01283 0.00567 -0.1187 0.8333 0.0157
-4.500 -0.0452 0.01254 0.00534 -0.1184 0.8327 0.0164
-4.250 -0.0210 0.01230 0.00506 -0.1182 0.8322 0.0169
-4.000 0.0040 0.01210 0.00481 -0.1182 0.8317 0.0177
-3.750 0.0293 0.01189 0.00457 -0.1182 0.8312 0.0189
-3.500 0.0551 0.01171 0.00438 -0.1182 0.8306 0.0215
-3.250 0.0797 0.01139 0.00418 -0.1182 0.8300 0.0550
-3.000 0.0851 0.00901 0.00346 -0.1166 0.8291 0.5450
-2.750 0.1123 0.00921 0.00366 -0.1167 0.8286 0.5676
-2.500 0.1396 0.00935 0.00376 -0.1168 0.8281 0.5774
-2.250 0.1666 0.00947 0.00388 -0.1168 0.8276 0.5829
-2.000 0.1938 0.00962 0.00398 -0.1170 0.8271 0.5899
-1.750 0.2204 0.00981 0.00423 -0.1168 0.8265 0.5974
-1.500 0.2473 0.00987 0.00428 -0.1170 0.8260 0.5993
-1.250 0.2742 0.00991 0.00430 -0.1171 0.8255 0.5999
-1.000 0.3010 0.00995 0.00433 -0.1172 0.8249 0.6005
-0.750 0.3278 0.00999 0.00437 -0.1173 0.8243 0.6011
-0.500 0.3545 0.01003 0.00441 -0.1174 0.8235 0.6017
-0.250 0.3813 0.01008 0.00447 -0.1175 0.8228 0.6024
0.000 0.4080 0.01015 0.00454 -0.1176 0.8223 0.6031
0.250 0.4346 0.01023 0.00463 -0.1177 0.8217 0.6039
0.500 0.4613 0.01030 0.00472 -0.1178 0.8211 0.6046
0.750 0.4879 0.01038 0.00482 -0.1179 0.8206 0.6052
1.000 0.5145 0.01046 0.00493 -0.1179 0.8201 0.6057
1.250 0.5459 0.01033 0.00482 -0.1188 0.8181 0.6063
1.500 0.5758 0.01001 0.00451 -0.1192 0.8119 0.6070
1.750 0.6027 0.00972 0.00425 -0.1189 0.8054 0.6076
2.000 0.6374 0.00944 0.00396 -0.1204 0.8006 0.6082
2.250 0.6550 0.00940 0.00401 -0.1183 0.7947 0.6089
2.500 0.6834 0.00918 0.00380 -0.1184 0.7882 0.6096
2.750 0.7020 0.00911 0.00380 -0.1165 0.7802 0.6104
3.000 0.7221 0.00897 0.00372 -0.1149 0.7690 0.6111
3.250 0.7350 0.00889 0.00369 -0.1117 0.7506 0.6119
3.500 0.7237 0.00888 0.00316 -0.1027 0.6419 0.6128
3.750 0.6845 0.01030 0.00399 -0.0891 0.5300 0.6136
4.000 0.6506 0.01207 0.00513 -0.0777 0.4015 0.6145
4.250 0.6438 0.01333 0.00593 -0.0719 0.3014 0.6153
4.500 0.6507 0.01420 0.00649 -0.0686 0.2318 0.6162
4.750 0.6636 0.01486 0.00694 -0.0664 0.1839 0.6171
5.000 0.6792 0.01544 0.00736 -0.0647 0.1470 0.6181
5.250 0.6974 0.01589 0.00772 -0.0634 0.1257 0.6192
5.500 0.7166 0.01630 0.00808 -0.0623 0.1090 0.6201
5.750 0.7363 0.01670 0.00844 -0.0613 0.0959 0.6209
6.000 0.7559 0.01709 0.00882 -0.0603 0.0848 0.6219
6.250 0.7757 0.01749 0.00921 -0.0593 0.0748 0.6228
6.500 0.7958 0.01787 0.00960 -0.0584 0.0669 0.6238
6.750 0.8155 0.01830 0.01002 -0.0574 0.0596 0.6248
7.000 0.8360 0.01868 0.01044 -0.0566 0.0545 0.6259
7.250 0.8555 0.01914 0.01088 -0.0556 0.0479 0.6270
7.500 0.8759 0.01954 0.01131 -0.0548 0.0436 0.6282
7.750 0.8952 0.02002 0.01178 -0.0539 0.0386 0.6294
8.000 0.9156 0.02043 0.01224 -0.0531 0.0357 0.6306
8.250 0.9356 0.02088 0.01271 -0.0522 0.0325 0.6319
8.500 0.9550 0.02139 0.01323 -0.0513 0.0297 0.6332
8.750 0.9752 0.02183 0.01373 -0.0505 0.0276 0.6345
9.250 1.0141 0.02284 0.01481 -0.0488 0.0211 0.6371
9.500 1.0329 0.02341 0.01539 -0.0479 0.0171 0.6385
9.750 1.0516 0.02400 0.01602 -0.0470 0.0138 0.6400
10.000 1.0700 0.02464 0.01670 -0.0461 0.0117 0.6417
10.250 1.0880 0.02534 0.01744 -0.0451 0.0101 0.6435
10.500 1.1058 0.02608 0.01826 -0.0441 0.0092 0.6455
10.750 1.1235 0.02680 0.01907 -0.0430 0.0086 0.6474
11.000 1.1410 0.02755 0.01989 -0.0420 0.0082 0.6495
11.250 1.1578 0.02835 0.02078 -0.0410 0.0077 0.6514
11.500 1.1741 0.02922 0.02175 -0.0399 0.0074 0.6535
11.750 1.1892 0.03022 0.02285 -0.0387 0.0071 0.6557
12.000 1.2032 0.03128 0.02402 -0.0374 0.0068 0.6580
12.250 1.2171 0.03233 0.02522 -0.0361 0.0067 0.6605
12.500 1.2305 0.03343 0.02644 -0.0348 0.0065 0.6631
12.750 1.2428 0.03463 0.02776 -0.0334 0.0063 0.6657
13.000 1.2545 0.03584 0.02912 -0.0321 0.0062 0.6684
13.250 1.2649 0.03717 0.03059 -0.0306 0.0060 0.6715
13.500 1.2748 0.03856 0.03212 -0.0292 0.0058 0.6749
13.750 1.2833 0.04007 0.03376 -0.0277 0.0057 0.6784
14.000 1.2912 0.04162 0.03545 -0.0263 0.0056 0.6819
14.250 1.2977 0.04330 0.03728 -0.0248 0.0054 0.6859
14.500 1.3026 0.04516 0.03930 -0.0233 0.0053 0.6903
14.750 1.3049 0.04731 0.04161 -0.0218 0.0052 0.6948
15.000 1.3056 0.04966 0.04412 -0.0203 0.0051 0.6995
15.250 1.3042 0.05227 0.04691 -0.0189 0.0051 0.7048
15.750 1.2952 0.05845 0.05346 -0.0165 0.0049 0.7168
16.000 1.2864 0.06228 0.05748 -0.0157 0.0049 0.7238
16.250 1.2780 0.06623 0.06164 -0.0154 0.0049 0.7311
16.500 1.2665 0.07083 0.06645 -0.0155 0.0048 0.7398
16.750 1.2495 0.07657 0.07241 -0.0164 0.0048 0.7481
17.000 1.2347 0.08241 0.07848 -0.0181 0.0048 0.7586
17.250 1.2182 0.08906 0.08536 -0.0207 0.0048 0.7704
17.750 1.1792 0.10548 0.10227 -0.0295 0.0048 0.7982
18.000 1.1554 0.11601 0.11304 -0.0360 0.0048 0.8114
18.250 1.1315 0.12720 0.12446 -0.0430 0.0049 0.8257
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