NACA 0015 (naca0015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0015 (naca0015-il) Reynolds number: 200,000 Max Cl/Cd: 49.63 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0015-il-200000.txt Download as CSV file: xf-naca0015-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9069 0.11931 0.11495 -0.0134 1.0000 0.0575
-16.500 -1.0046 0.09629 0.09159 -0.0282 1.0000 0.0561
-16.250 -1.0607 0.08367 0.07865 -0.0360 1.0000 0.0555
-16.000 -1.0983 0.07517 0.06986 -0.0407 1.0000 0.0553
-15.750 -1.1260 0.06870 0.06313 -0.0436 1.0000 0.0554
-15.500 -1.1477 0.06342 0.05761 -0.0454 1.0000 0.0557
-15.250 -1.1655 0.05898 0.05292 -0.0463 1.0000 0.0561
-15.000 -1.1804 0.05515 0.04884 -0.0465 1.0000 0.0565
-14.750 -1.1931 0.05184 0.04527 -0.0460 1.0000 0.0569
-14.500 -1.2040 0.04899 0.04215 -0.0449 1.0000 0.0574
-14.250 -1.2130 0.04658 0.03948 -0.0432 1.0000 0.0578
-14.000 -1.1945 0.04426 0.03718 -0.0429 1.0000 0.0589
-13.750 -1.1830 0.04267 0.03557 -0.0421 1.0000 0.0598
-13.500 -1.1751 0.04113 0.03395 -0.0409 1.0000 0.0608
-13.250 -1.1690 0.03956 0.03226 -0.0394 1.0000 0.0619
-13.000 -1.1622 0.03804 0.03059 -0.0378 1.0000 0.0631
-12.750 -1.1558 0.03658 0.02894 -0.0359 1.0000 0.0642
-12.500 -1.1499 0.03528 0.02741 -0.0336 1.0000 0.0652
-12.250 -1.1272 0.03352 0.02570 -0.0336 1.0000 0.0667
-12.000 -1.1117 0.03242 0.02462 -0.0324 1.0000 0.0683
-11.750 -1.0987 0.03139 0.02354 -0.0308 1.0000 0.0700
-11.500 -1.0867 0.03038 0.02240 -0.0289 1.0000 0.0719
-11.250 -1.0757 0.02948 0.02133 -0.0267 1.0000 0.0736
-11.000 -1.0559 0.02808 0.02003 -0.0260 1.0000 0.0759
-10.750 -1.0416 0.02719 0.01916 -0.0242 1.0000 0.0782
-10.500 -1.0275 0.02637 0.01826 -0.0223 1.0000 0.0810
-10.250 -1.0125 0.02539 0.01722 -0.0206 1.0000 0.0841
-10.000 -0.9985 0.02450 0.01641 -0.0187 1.0000 0.0875
-9.750 -0.9839 0.02379 0.01565 -0.0167 1.0000 0.0917
-9.500 -0.9709 0.02284 0.01473 -0.0145 1.0000 0.0961
-9.250 -0.9573 0.02217 0.01407 -0.0123 1.0000 0.1013
-9.000 -0.9448 0.02138 0.01330 -0.0098 1.0000 0.1074
-8.750 -0.9312 0.02079 0.01272 -0.0075 1.0000 0.1144
-8.500 -0.9189 0.02007 0.01206 -0.0049 1.0000 0.1220
-8.250 -0.9043 0.01954 0.01150 -0.0027 1.0000 0.1310
-8.000 -0.8911 0.01894 0.01098 -0.0002 1.0000 0.1403
-7.750 -0.8775 0.01836 0.01047 0.0021 1.0000 0.1505
-7.500 -0.8627 0.01787 0.01000 0.0044 1.0000 0.1619
-7.250 -0.8472 0.01743 0.00958 0.0065 1.0000 0.1746
-7.000 -0.8318 0.01699 0.00920 0.0086 1.0000 0.1883
-6.750 -0.8163 0.01654 0.00883 0.0106 1.0000 0.2030
-6.500 -0.8001 0.01614 0.00850 0.0126 1.0000 0.2191
-6.250 -0.7833 0.01578 0.00821 0.0144 1.0000 0.2366
-6.000 -0.7661 0.01545 0.00796 0.0161 1.0000 0.2552
-5.750 -0.7485 0.01512 0.00774 0.0177 1.0000 0.2748
-5.500 -0.7302 0.01485 0.00756 0.0192 1.0000 0.2954
-5.250 -0.7113 0.01461 0.00741 0.0205 1.0000 0.3166
-5.000 -0.6920 0.01442 0.00728 0.0218 1.0000 0.3380
-4.750 -0.6677 0.01422 0.00717 0.0220 0.9989 0.3606
-4.500 -0.6253 0.01402 0.00709 0.0187 0.9938 0.3888
-4.250 -0.5848 0.01381 0.00697 0.0158 0.9875 0.4156
-4.000 -0.5417 0.01363 0.00689 0.0125 0.9820 0.4435
-3.750 -0.5033 0.01341 0.00677 0.0102 0.9743 0.4692
-3.500 -0.4602 0.01321 0.00668 0.0070 0.9688 0.4965
-3.250 -0.4234 0.01300 0.00656 0.0052 0.9603 0.5219
-3.000 -0.3803 0.01277 0.00645 0.0022 0.9547 0.5486
-2.750 -0.3431 0.01257 0.00633 0.0005 0.9463 0.5742
-2.500 -0.3012 0.01231 0.00620 -0.0021 0.9401 0.5987
-2.250 -0.2651 0.01208 0.00606 -0.0034 0.9315 0.6225
-2.000 -0.2286 0.01184 0.00588 -0.0047 0.9229 0.6465
-1.750 -0.1973 0.01161 0.00576 -0.0048 0.9117 0.6681
-1.500 -0.1627 0.01136 0.00560 -0.0054 0.9029 0.6901
-1.250 -0.1357 0.01119 0.00551 -0.0046 0.8886 0.7110
-1.000 -0.1080 0.01103 0.00541 -0.0039 0.8744 0.7319
-0.750 -0.0803 0.01090 0.00532 -0.0031 0.8601 0.7526
-0.500 -0.0531 0.01079 0.00525 -0.0021 0.8448 0.7728
-0.250 -0.0264 0.01073 0.00519 -0.0011 0.8284 0.7922
0.000 0.0000 0.01071 0.00518 0.0000 0.8109 0.8109
0.250 0.0264 0.01073 0.00519 0.0011 0.7922 0.8284
0.500 0.0531 0.01079 0.00525 0.0021 0.7727 0.8449
0.750 0.0803 0.01090 0.00532 0.0031 0.7526 0.8601
1.000 0.1080 0.01103 0.00541 0.0039 0.7319 0.8744
1.250 0.1357 0.01119 0.00551 0.0046 0.7110 0.8886
1.500 0.1627 0.01136 0.00560 0.0054 0.6901 0.9029
1.750 0.1973 0.01161 0.00576 0.0048 0.6681 0.9117
2.000 0.2286 0.01183 0.00588 0.0047 0.6464 0.9229
2.250 0.2650 0.01208 0.00606 0.0034 0.6225 0.9315
2.500 0.3012 0.01231 0.00619 0.0021 0.5987 0.9401
2.750 0.3430 0.01257 0.00633 -0.0005 0.5742 0.9464
3.000 0.3803 0.01277 0.00645 -0.0022 0.5486 0.9547
3.250 0.4234 0.01300 0.00656 -0.0052 0.5219 0.9604
3.500 0.4602 0.01321 0.00668 -0.0070 0.4965 0.9688
3.750 0.5033 0.01341 0.00677 -0.0102 0.4692 0.9744
4.000 0.5417 0.01363 0.00689 -0.0125 0.4435 0.9820
4.250 0.5848 0.01381 0.00697 -0.0158 0.4156 0.9875
4.500 0.6253 0.01402 0.00708 -0.0187 0.3887 0.9938
4.750 0.6677 0.01422 0.00717 -0.0220 0.3606 0.9990
5.000 0.6919 0.01441 0.00728 -0.0217 0.3381 1.0000
5.250 0.7112 0.01461 0.00740 -0.0205 0.3167 1.0000
5.500 0.7300 0.01484 0.00755 -0.0191 0.2954 1.0000
5.750 0.7483 0.01512 0.00773 -0.0177 0.2748 1.0000
6.000 0.7659 0.01544 0.00795 -0.0161 0.2553 1.0000
6.250 0.7832 0.01578 0.00821 -0.0144 0.2366 1.0000
6.500 0.8000 0.01614 0.00850 -0.0125 0.2191 1.0000
6.750 0.8162 0.01654 0.00883 -0.0106 0.2031 1.0000
7.000 0.8317 0.01698 0.00919 -0.0086 0.1883 1.0000
7.250 0.8471 0.01742 0.00958 -0.0065 0.1746 1.0000
7.500 0.8626 0.01786 0.01000 -0.0043 0.1619 1.0000
7.750 0.8774 0.01836 0.01046 -0.0021 0.1505 1.0000
8.000 0.8910 0.01893 0.01097 0.0003 0.1403 1.0000
8.250 0.9042 0.01953 0.01150 0.0027 0.1310 1.0000
8.500 0.9189 0.02006 0.01205 0.0050 0.1220 1.0000
8.750 0.9312 0.02079 0.01271 0.0075 0.1144 1.0000
9.000 0.9448 0.02138 0.01330 0.0098 0.1074 1.0000
9.250 0.9574 0.02216 0.01406 0.0122 0.1013 1.0000
9.500 0.9710 0.02284 0.01473 0.0145 0.0961 1.0000
9.750 0.9841 0.02379 0.01565 0.0167 0.0917 1.0000
10.000 0.9987 0.02450 0.01641 0.0187 0.0875 1.0000
10.250 1.0128 0.02539 0.01722 0.0205 0.0841 1.0000
10.500 1.0278 0.02636 0.01825 0.0223 0.0810 1.0000
10.750 1.0420 0.02719 0.01916 0.0242 0.0782 1.0000
11.000 1.0564 0.02808 0.02003 0.0259 0.0759 1.0000
11.250 1.0762 0.02948 0.02133 0.0266 0.0736 1.0000
11.500 1.0872 0.03038 0.02240 0.0288 0.0719 1.0000
11.750 1.0993 0.03140 0.02354 0.0307 0.0700 1.0000
12.000 1.1124 0.03242 0.02462 0.0323 0.0683 1.0000
12.250 1.1280 0.03353 0.02570 0.0334 0.0667 1.0000
12.500 1.1504 0.03528 0.02741 0.0335 0.0651 1.0000
12.750 1.1565 0.03659 0.02895 0.0358 0.0642 1.0000
13.000 1.1629 0.03805 0.03060 0.0377 0.0631 1.0000
13.250 1.1699 0.03957 0.03226 0.0393 0.0619 1.0000
13.500 1.1760 0.04113 0.03395 0.0408 0.0608 1.0000
13.750 1.1841 0.04267 0.03557 0.0420 0.0598 1.0000
14.000 1.1959 0.04426 0.03717 0.0428 0.0588 1.0000
14.250 1.2139 0.04660 0.03950 0.0430 0.0578 1.0000
14.500 1.2047 0.04901 0.04217 0.0447 0.0574 1.0000
14.750 1.1940 0.05186 0.04530 0.0458 0.0569 1.0000
15.000 1.1814 0.05518 0.04887 0.0463 0.0565 1.0000
15.250 1.1666 0.05902 0.05296 0.0461 0.0560 1.0000
15.500 1.1489 0.06346 0.05765 0.0452 0.0557 1.0000
15.750 1.1273 0.06873 0.06317 0.0434 0.0554 1.0000
16.000 1.0996 0.07523 0.06993 0.0404 0.0553 1.0000
16.250 1.0615 0.08381 0.07879 0.0357 0.0555 1.0000
16.500 1.0046 0.09664 0.09195 0.0276 0.0561 1.0000
16.750 0.9052 0.12012 0.11576 0.0126 0.0575 1.0000
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