NACA 2415 (n2415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 50,000 Max Cl/Cd: 31.59 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2415-il-50000-n5.txt Download as CSV file: xf-n2415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5222 0.10284 0.09441 -0.0413 1.0000 0.0963
-11.500 -0.5432 0.09462 0.08624 -0.0455 1.0000 0.0978
-11.250 -0.6144 0.07692 0.06854 -0.0570 1.0000 0.0978
-11.000 -0.6957 0.06443 0.05585 -0.0635 1.0000 0.0964
-10.750 -0.7361 0.05987 0.05115 -0.0613 1.0000 0.0965
-10.500 -0.7598 0.05647 0.04758 -0.0584 1.0000 0.0974
-10.250 -0.7773 0.05333 0.04421 -0.0553 1.0000 0.0988
-10.000 -0.7913 0.05025 0.04081 -0.0520 1.0000 0.1007
-9.750 -0.7976 0.04761 0.03785 -0.0490 1.0000 0.1029
-9.500 -0.7865 0.04648 0.03678 -0.0470 1.0000 0.1055
-9.250 -0.7809 0.04485 0.03504 -0.0446 1.0000 0.1086
-9.000 -0.7778 0.04278 0.03266 -0.0420 1.0000 0.1120
-8.750 -0.7705 0.04106 0.03075 -0.0397 1.0000 0.1155
-8.500 -0.7580 0.04002 0.02972 -0.0377 1.0000 0.1192
-8.250 -0.7479 0.03856 0.02806 -0.0356 1.0000 0.1237
-8.000 -0.7363 0.03717 0.02649 -0.0336 1.0000 0.1285
-7.750 -0.7223 0.03625 0.02560 -0.0318 1.0000 0.1333
-7.500 -0.7091 0.03499 0.02405 -0.0299 1.0000 0.1395
-7.250 -0.6939 0.03413 0.02326 -0.0282 1.0000 0.1451
-7.000 -0.6787 0.03318 0.02219 -0.0266 1.0000 0.1521
-6.750 -0.6628 0.03233 0.02132 -0.0250 1.0000 0.1591
-6.500 -0.6464 0.03156 0.02044 -0.0235 1.0000 0.1675
-6.250 -0.6296 0.03084 0.01974 -0.0221 1.0000 0.1757
-6.000 -0.6122 0.03015 0.01890 -0.0207 1.0000 0.1864
-5.750 -0.5948 0.02960 0.01844 -0.0194 1.0000 0.1959
-5.500 -0.5767 0.02905 0.01788 -0.0183 1.0000 0.2075
-5.250 -0.5553 0.02855 0.01733 -0.0177 0.9990 0.2213
-5.000 -0.5177 0.02807 0.01688 -0.0202 0.9919 0.2397
-4.750 -0.4807 0.02763 0.01648 -0.0226 0.9841 0.2599
-4.500 -0.4446 0.02723 0.01611 -0.0248 0.9758 0.2822
-4.250 -0.4057 0.02687 0.01573 -0.0274 0.9682 0.3082
-4.000 -0.3717 0.02649 0.01547 -0.0290 0.9587 0.3330
-3.750 -0.3359 0.02615 0.01516 -0.0309 0.9498 0.3621
-3.500 -0.2996 0.02581 0.01496 -0.0328 0.9411 0.3927
-3.250 -0.2681 0.02551 0.01476 -0.0337 0.9307 0.4249
-3.000 -0.2298 0.02521 0.01462 -0.0357 0.9229 0.4627
-2.750 -0.2018 0.02497 0.01452 -0.0358 0.9113 0.4994
-2.500 -0.1667 0.02472 0.01444 -0.0369 0.9028 0.5423
-2.250 -0.1367 0.02452 0.01441 -0.0369 0.8920 0.5861
-2.000 -0.1059 0.02436 0.01440 -0.0370 0.8820 0.6322
-1.750 -0.0721 0.02421 0.01442 -0.0372 0.8729 0.6794
-1.500 -0.0440 0.02416 0.01448 -0.0364 0.8618 0.7250
-1.250 -0.0068 0.02408 0.01448 -0.0369 0.8536 0.7710
-1.000 0.0248 0.02415 0.01461 -0.0366 0.8419 0.8129
-0.750 0.0724 0.02412 0.01455 -0.0391 0.8347 0.8534
-0.500 0.1139 0.02424 0.01464 -0.0410 0.8228 0.8888
-0.250 0.1707 0.02414 0.01444 -0.0456 0.8157 0.9198
0.000 0.2231 0.02420 0.01443 -0.0501 0.8033 0.9454
0.250 0.2834 0.02403 0.01417 -0.0560 0.7938 0.9677
0.500 0.3441 0.02380 0.01387 -0.0623 0.7821 0.9868
0.750 0.3898 0.02364 0.01365 -0.0661 0.7687 1.0000
1.000 0.4106 0.02353 0.01345 -0.0650 0.7556 1.0000
1.250 0.4337 0.02340 0.01323 -0.0642 0.7431 1.0000
1.500 0.4506 0.02350 0.01326 -0.0624 0.7284 1.0000
1.750 0.4699 0.02358 0.01327 -0.0609 0.7148 1.0000
2.000 0.4940 0.02355 0.01316 -0.0600 0.7029 1.0000
2.250 0.5148 0.02365 0.01320 -0.0586 0.6896 1.0000
2.750 0.5561 0.02398 0.01343 -0.0558 0.6633 1.0000
3.000 0.5810 0.02405 0.01343 -0.0549 0.6513 1.0000
3.250 0.5993 0.02435 0.01372 -0.0532 0.6373 1.0000
3.500 0.6206 0.02458 0.01392 -0.0519 0.6244 1.0000
3.750 0.6468 0.02467 0.01393 -0.0511 0.6128 1.0000
4.000 0.6659 0.02500 0.01428 -0.0495 0.5988 1.0000
4.250 0.6862 0.02533 0.01461 -0.0481 0.5853 1.0000
4.500 0.7097 0.02555 0.01480 -0.0470 0.5726 1.0000
4.750 0.7339 0.02576 0.01498 -0.0460 0.5597 1.0000
5.000 0.7527 0.02617 0.01542 -0.0443 0.5452 1.0000
5.250 0.7734 0.02653 0.01578 -0.0429 0.5313 1.0000
5.500 0.7961 0.02682 0.01605 -0.0417 0.5177 1.0000
5.750 0.8203 0.02704 0.01625 -0.0407 0.5041 1.0000
6.000 0.8382 0.02751 0.01677 -0.0390 0.4888 1.0000
6.250 0.8570 0.02795 0.01724 -0.0373 0.4736 1.0000
6.500 0.8763 0.02837 0.01769 -0.0358 0.4584 1.0000
6.750 0.8957 0.02877 0.01810 -0.0342 0.4431 1.0000
7.000 0.9147 0.02918 0.01851 -0.0326 0.4274 1.0000
7.250 0.9330 0.02961 0.01895 -0.0309 0.4115 1.0000
7.500 0.9503 0.03008 0.01940 -0.0291 0.3953 1.0000
7.750 0.9663 0.03059 0.01993 -0.0271 0.3789 1.0000
8.000 0.9803 0.03120 0.02057 -0.0250 0.3622 1.0000
8.250 0.9935 0.03185 0.02124 -0.0228 0.3455 1.0000
8.500 1.0057 0.03257 0.02196 -0.0206 0.3289 1.0000
8.750 1.0168 0.03335 0.02275 -0.0183 0.3125 1.0000
9.000 1.0265 0.03422 0.02362 -0.0159 0.2964 1.0000
9.250 1.0340 0.03516 0.02457 -0.0133 0.2812 1.0000
9.500 1.0409 0.03621 0.02561 -0.0107 0.2664 1.0000
9.750 1.0477 0.03736 0.02675 -0.0084 0.2524 1.0000
10.000 1.0543 0.03860 0.02796 -0.0062 0.2390 1.0000
10.250 1.0611 0.03989 0.02919 -0.0042 0.2266 1.0000
10.500 1.0655 0.04144 0.03080 -0.0022 0.2142 1.0000
10.750 1.0701 0.04312 0.03252 -0.0005 0.2028 1.0000
11.000 1.0756 0.04476 0.03414 0.0011 0.1927 1.0000
11.250 1.0803 0.04654 0.03594 0.0025 0.1830 1.0000
11.500 1.0836 0.04859 0.03809 0.0038 0.1739 1.0000
11.750 1.0908 0.05025 0.03965 0.0049 0.1661 1.0000
12.000 1.0911 0.05278 0.04237 0.0059 0.1582 1.0000
12.250 1.0989 0.05449 0.04397 0.0068 0.1514 1.0000
12.500 1.0971 0.05742 0.04716 0.0075 0.1449 1.0000
12.750 1.1035 0.05937 0.04908 0.0082 0.1390 1.0000
13.000 1.1014 0.06248 0.05237 0.0085 0.1337 1.0000
13.250 1.1012 0.06538 0.05539 0.0088 0.1287 1.0000
13.500 1.1093 0.06731 0.05726 0.0093 0.1241 1.0000
13.750 1.0975 0.07186 0.06211 0.0088 0.1203 1.0000
14.000 1.0920 0.07565 0.06605 0.0083 0.1166 1.0000
14.250 1.1066 0.07678 0.06707 0.0091 0.1126 1.0000
14.500 1.0833 0.08325 0.07389 0.0071 0.1103 1.0000
14.750 1.0563 0.09077 0.08170 0.0043 0.1083 1.0000
15.000 1.0222 0.10009 0.09130 0.0001 0.1065 1.0000
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