NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M15 AIRFOIL (m15-il) Reynolds number: 200,000 Max Cl/Cd: 72.16 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m15-il-200000.txt Download as CSV file: xf-m15-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M15 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2678 0.09736 0.09405 -0.0373 1.0000 0.0616
-9.500 -0.2906 0.09344 0.09019 -0.0432 1.0000 0.0626
-9.250 -0.3062 0.08938 0.08619 -0.0473 1.0000 0.0628
-9.000 -0.2834 0.08489 0.08172 -0.0428 1.0000 0.0640
-8.750 -0.2734 0.08252 0.07940 -0.0411 1.0000 0.0651
-8.500 -0.2776 0.08065 0.07762 -0.0396 0.9982 0.0660
-8.250 -0.2632 0.07597 0.07293 -0.0437 0.9920 0.0680
-8.000 -0.4027 0.08091 0.07775 -0.0420 0.9969 0.0643
-7.750 -0.3762 0.07772 0.07455 -0.0440 0.9916 0.0659
-7.500 -0.3510 0.07319 0.06995 -0.0504 0.9833 0.0683
-7.250 -0.3357 0.06637 0.06245 -0.0668 0.9614 0.0742
-7.000 -0.3149 0.06007 0.05635 -0.0683 0.9540 0.0755
-6.750 -0.2941 0.05736 0.05365 -0.0687 0.9411 0.0767
-6.500 -0.2774 0.05493 0.05116 -0.0688 0.9260 0.0785
-6.250 -0.2629 0.05242 0.04851 -0.0687 0.9107 0.0816
-6.000 -0.2544 0.04811 0.04364 -0.0697 0.8951 0.0885
-5.750 -0.2380 0.04584 0.04140 -0.0687 0.8827 0.0899
-5.500 -0.2214 0.04392 0.03940 -0.0677 0.8712 0.0920
-5.250 -0.2007 0.04473 0.03943 -0.0662 0.8589 0.1013
-5.000 -0.1879 0.03901 0.03381 -0.0661 0.8472 0.1035
-4.750 -0.1686 0.03701 0.03178 -0.0653 0.8362 0.1055
-4.500 -0.1481 0.03535 0.02997 -0.0644 0.8266 0.1091
-4.250 -0.1275 0.03342 0.02763 -0.0637 0.8170 0.1192
-4.000 -0.1027 0.02540 0.01840 -0.0610 0.8108 0.0709
-3.750 -0.0780 0.02206 0.01429 -0.0596 0.8030 0.0643
-3.500 -0.0515 0.02092 0.01285 -0.0589 0.7955 0.0636
-3.250 -0.0248 0.01977 0.01150 -0.0585 0.7882 0.0637
-3.000 0.0019 0.01867 0.01030 -0.0582 0.7808 0.0648
-2.750 0.0288 0.01802 0.00957 -0.0579 0.7743 0.0668
-2.500 0.0562 0.01737 0.00885 -0.0576 0.7666 0.0683
-2.250 0.0834 0.01673 0.00809 -0.0572 0.7607 0.0697
-2.000 0.1106 0.01619 0.00751 -0.0569 0.7530 0.0716
-1.750 0.1377 0.01575 0.00698 -0.0564 0.7464 0.0738
-1.500 0.1635 0.01512 0.00641 -0.0560 0.7399 0.0778
-1.250 0.1901 0.01484 0.00614 -0.0557 0.7327 0.0846
-1.000 0.2160 0.01442 0.00573 -0.0551 0.7268 0.0942
-0.750 0.2413 0.01393 0.00539 -0.0545 0.7189 0.1216
-0.500 0.2640 0.01308 0.00510 -0.0537 0.7128 0.2630
-0.250 0.3432 0.01165 0.00573 -0.0624 0.7051 0.9802
0.000 0.4173 0.01171 0.00554 -0.0720 0.6970 1.0000
0.250 0.4429 0.01175 0.00549 -0.0717 0.6890 1.0000
0.500 0.4683 0.01178 0.00539 -0.0712 0.6815 1.0000
0.750 0.4935 0.01183 0.00537 -0.0707 0.6732 1.0000
1.000 0.5187 0.01187 0.00529 -0.0702 0.6651 1.0000
1.250 0.5438 0.01194 0.00531 -0.0697 0.6565 1.0000
1.500 0.5689 0.01200 0.00526 -0.0691 0.6484 1.0000
1.750 0.5937 0.01208 0.00530 -0.0686 0.6391 1.0000
2.000 0.6188 0.01216 0.00526 -0.0680 0.6310 1.0000
2.250 0.6433 0.01225 0.00535 -0.0674 0.6210 1.0000
2.500 0.6684 0.01235 0.00534 -0.0668 0.6131 1.0000
2.750 0.6927 0.01243 0.00543 -0.0661 0.6026 1.0000
3.000 0.7173 0.01255 0.00549 -0.0655 0.5939 1.0000
3.250 0.7418 0.01265 0.00555 -0.0649 0.5845 1.0000
3.500 0.7660 0.01278 0.00568 -0.0642 0.5751 1.0000
3.750 0.7907 0.01289 0.00572 -0.0636 0.5668 1.0000
4.000 0.8146 0.01304 0.00589 -0.0629 0.5572 1.0000
4.250 0.8394 0.01317 0.00594 -0.0623 0.5497 1.0000
4.500 0.8629 0.01332 0.00614 -0.0615 0.5399 1.0000
4.750 0.8873 0.01347 0.00625 -0.0608 0.5319 1.0000
5.000 0.9108 0.01358 0.00638 -0.0600 0.5217 1.0000
5.250 0.9342 0.01372 0.00652 -0.0592 0.5115 1.0000
5.500 0.9583 0.01388 0.00659 -0.0585 0.5030 1.0000
5.750 0.9814 0.01408 0.00687 -0.0577 0.4938 1.0000
6.000 1.0056 0.01431 0.00706 -0.0570 0.4864 1.0000
6.250 1.0286 0.01454 0.00735 -0.0562 0.4775 1.0000
6.500 1.0526 0.01481 0.00760 -0.0556 0.4701 1.0000
6.750 1.0755 0.01508 0.00794 -0.0548 0.4617 1.0000
7.000 1.0992 0.01538 0.00823 -0.0541 0.4540 1.0000
7.250 1.1218 0.01566 0.00857 -0.0532 0.4453 1.0000
7.500 1.1449 0.01599 0.00894 -0.0525 0.4368 1.0000
7.750 1.1673 0.01627 0.00918 -0.0516 0.4258 1.0000
8.000 1.1870 0.01649 0.00946 -0.0502 0.4119 1.0000
8.250 1.2064 0.01673 0.00973 -0.0488 0.3970 1.0000
8.500 1.2252 0.01698 0.01003 -0.0473 0.3817 1.0000
8.750 1.2436 0.01725 0.01033 -0.0458 0.3658 1.0000
9.000 1.2618 0.01756 0.01070 -0.0443 0.3504 1.0000
9.250 1.2793 0.01791 0.01109 -0.0427 0.3342 1.0000
9.500 1.2951 0.01834 0.01154 -0.0409 0.3162 1.0000
9.750 1.3097 0.01881 0.01206 -0.0390 0.2942 1.0000
10.000 1.3202 0.01948 0.01268 -0.0365 0.2685 1.0000
10.250 1.3258 0.02039 0.01348 -0.0335 0.2378 1.0000
10.500 1.3231 0.02159 0.01452 -0.0292 0.2051 1.0000
10.750 1.3149 0.02337 0.01609 -0.0250 0.1694 1.0000
11.000 1.3024 0.02580 0.01825 -0.0212 0.1237 1.0000
11.250 1.2868 0.02886 0.02099 -0.0180 0.0863 1.0000
11.500 1.2759 0.03189 0.02390 -0.0157 0.0707 1.0000
11.750 1.2697 0.03473 0.02676 -0.0141 0.0625 1.0000
12.000 1.2612 0.03794 0.02998 -0.0128 0.0577 1.0000
12.250 1.2597 0.04062 0.03276 -0.0119 0.0537 1.0000
12.500 1.2543 0.04372 0.03591 -0.0111 0.0509 1.0000
12.750 1.2466 0.04708 0.03930 -0.0103 0.0487 1.0000
13.000 1.2474 0.04966 0.04199 -0.0097 0.0464 1.0000
13.250 1.2468 0.05239 0.04480 -0.0092 0.0443 1.0000
13.500 1.2447 0.05527 0.04769 -0.0087 0.0426 1.0000
13.750 1.2430 0.05796 0.05034 -0.0076 0.0410 1.0000
14.000 1.2475 0.06023 0.05275 -0.0071 0.0398 1.0000
14.250 1.2523 0.06245 0.05505 -0.0064 0.0385 1.0000
14.500 1.2575 0.06462 0.05727 -0.0059 0.0372 1.0000
14.750 1.2636 0.06667 0.05933 -0.0052 0.0360 1.0000
15.000 1.2775 0.06745 0.05999 -0.0030 0.0344 1.0000
15.250 1.2810 0.07004 0.06277 -0.0030 0.0336 1.0000
15.500 1.2861 0.07244 0.06531 -0.0027 0.0328 1.0000
15.750 1.2926 0.07468 0.06768 -0.0022 0.0320 1.0000
16.000 1.2991 0.07693 0.07004 -0.0017 0.0313 1.0000
16.250 1.3038 0.07943 0.07266 -0.0014 0.0307 1.0000
16.500 1.3086 0.08195 0.07529 -0.0012 0.0301 1.0000
16.750 1.3149 0.08429 0.07769 -0.0008 0.0295 1.0000
17.000 1.3308 0.08593 0.07934 0.0011 0.0286 1.0000
17.250 1.3203 0.09040 0.08405 -0.0002 0.0284 1.0000
17.500 1.3095 0.09514 0.08903 -0.0017 0.0282 1.0000
17.750 1.2978 0.10021 0.09434 -0.0035 0.0280 1.0000
18.000 1.2854 0.10562 0.09998 -0.0056 0.0278 1.0000
18.250 1.2716 0.11144 0.10603 -0.0082 0.0277 1.0000
18.500 1.2568 0.11762 0.11244 -0.0111 0.0277 1.0000
18.750 1.2405 0.12434 0.11939 -0.0145 0.0277 1.0000
19.000 1.2229 0.13158 0.12683 -0.0186 0.0277 1.0000
19.250 1.2042 0.13938 0.13484 -0.0232 0.0279 1.0000
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