NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M27 AIRFOIL (m27-il) Reynolds number: 200,000 Max Cl/Cd: 62.75 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m27-il-200000.txt Download as CSV file: xf-m27-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M27 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 -0.2072 0.12108 0.11693 -0.0093 0.6740 0.0294
-9.500 -0.2001 0.11838 0.11420 -0.0112 0.6701 0.0301
-9.250 -0.1977 0.11721 0.11299 -0.0151 0.6669 0.0307
-8.750 -0.1839 0.11045 0.10626 -0.0186 0.6588 0.0311
-8.500 -0.1732 0.10648 0.10226 -0.0183 0.6547 0.0314
-8.250 -0.1649 0.10342 0.09916 -0.0191 0.6513 0.0319
-8.000 -0.1570 0.10059 0.09629 -0.0204 0.6480 0.0324
-7.750 -0.1486 0.09772 0.09346 -0.0223 0.6434 0.0330
-7.500 -0.1410 0.09489 0.09063 -0.0244 0.6394 0.0337
-7.250 -0.1356 0.09229 0.08799 -0.0262 0.6360 0.0345
-7.000 -0.1281 0.08983 0.08545 -0.0284 0.6332 0.0354
-6.750 -0.1120 0.08939 0.08494 -0.0374 0.6296 0.0366
-6.500 -0.0975 0.08613 0.08167 -0.0407 0.6257 0.0369
-6.250 -0.0879 0.08151 0.07706 -0.0389 0.6220 0.0372
-6.000 -0.0760 0.07821 0.07370 -0.0389 0.6188 0.0377
-5.750 -0.0620 0.07545 0.07085 -0.0399 0.6159 0.0384
-5.500 -0.0449 0.07276 0.06817 -0.0418 0.6115 0.0394
-5.250 -0.0265 0.07015 0.06551 -0.0437 0.6075 0.0406
-5.000 -0.0053 0.06770 0.06295 -0.0460 0.6042 0.0423
-4.750 0.0325 0.06680 0.06171 -0.0521 0.6015 0.0440
-4.500 0.0432 0.06280 0.05774 -0.0513 0.5984 0.0445
-4.250 0.0595 0.05990 0.05487 -0.0516 0.5942 0.0452
-4.000 0.0791 0.05750 0.05241 -0.0522 0.5904 0.0463
-3.750 0.1010 0.05529 0.05008 -0.0530 0.5872 0.0478
-3.500 0.1260 0.05333 0.04792 -0.0541 0.5845 0.0501
-3.250 0.1693 0.05311 0.04735 -0.0573 0.5807 0.0525
-3.000 0.1823 0.04938 0.04371 -0.0570 0.5770 0.0533
-2.750 0.2006 0.04704 0.04134 -0.0568 0.5736 0.0546
-2.500 0.2234 0.04522 0.03940 -0.0570 0.5706 0.0566
-2.250 0.2496 0.04367 0.03764 -0.0573 0.5680 0.0594
-2.000 0.2904 0.04371 0.03732 -0.0585 0.5639 0.0628
-1.750 0.3074 0.04057 0.03424 -0.0585 0.5602 0.0638
-1.500 0.3286 0.03868 0.03230 -0.0584 0.5570 0.0653
-1.250 0.3530 0.03722 0.03071 -0.0583 0.5543 0.0679
-1.000 0.3940 0.03870 0.03162 -0.0582 0.5518 0.0745
-0.750 0.4112 0.03499 0.02807 -0.0585 0.5480 0.0761
-0.500 0.4335 0.03346 0.02655 -0.0585 0.5441 0.0784
-0.250 0.4597 0.03236 0.02532 -0.0584 0.5409 0.0823
0.000 0.4928 0.03195 0.02450 -0.0581 0.5383 0.0890
0.250 0.5159 0.03020 0.02269 -0.0580 0.5360 0.0911
0.500 0.5411 0.02934 0.02185 -0.0581 0.5323 0.0949
0.750 0.5713 0.02897 0.02123 -0.0580 0.5285 0.1040
1.000 0.5960 0.02764 0.01990 -0.0580 0.5253 0.1072
1.250 0.6255 0.02727 0.01924 -0.0577 0.5226 0.1191
1.500 0.6510 0.02614 0.01806 -0.0578 0.5203 0.1255
1.750 0.6772 0.02569 0.01759 -0.0578 0.5169 0.1390
2.000 0.7036 0.02525 0.01712 -0.0579 0.5132 0.1534
2.250 0.7304 0.02469 0.01650 -0.0579 0.5100 0.1702
2.500 0.7721 0.02209 0.01309 -0.0569 0.5077 0.0703
2.750 0.8015 0.02154 0.01236 -0.0569 0.5053 0.0708
3.000 0.8287 0.02155 0.01227 -0.0569 0.5024 0.0744
3.250 0.8535 0.02128 0.01214 -0.0568 0.4987 0.0774
3.500 0.8788 0.02119 0.01210 -0.0566 0.4955 0.0819
3.750 0.9044 0.02099 0.01188 -0.0562 0.4928 0.0896
4.000 0.9296 0.02076 0.01168 -0.0557 0.4904 0.1129
4.250 0.9549 0.02062 0.01153 -0.0552 0.4883 0.1700
4.500 0.9764 0.02085 0.01213 -0.0548 0.4843 0.2782
4.750 1.1285 0.02048 0.01289 -0.0816 0.4788 1.0000
5.000 1.1529 0.02066 0.01300 -0.0812 0.4763 1.0000
5.250 1.1781 0.02079 0.01304 -0.0809 0.4741 1.0000
5.500 1.2019 0.02114 0.01335 -0.0805 0.4715 1.0000
5.750 1.2217 0.02175 0.01409 -0.0799 0.4676 1.0000
6.000 1.2434 0.02217 0.01455 -0.0794 0.4645 1.0000
6.250 1.2665 0.02245 0.01483 -0.0789 0.4619 1.0000
6.500 1.2907 0.02264 0.01498 -0.0785 0.4597 1.0000
6.750 1.3162 0.02282 0.01508 -0.0783 0.4577 1.0000
7.000 1.3341 0.02354 0.01594 -0.0774 0.4543 1.0000
7.250 1.3512 0.02422 0.01674 -0.0764 0.4506 1.0000
7.500 1.3716 0.02464 0.01721 -0.0756 0.4477 1.0000
7.750 1.3942 0.02491 0.01750 -0.0751 0.4454 1.0000
8.000 1.4204 0.02489 0.01743 -0.0749 0.4431 1.0000
8.250 1.4394 0.02529 0.01789 -0.0739 0.4392 1.0000
8.500 1.4534 0.02561 0.01834 -0.0723 0.4335 1.0000
8.750 1.4826 0.02483 0.01744 -0.0722 0.4286 1.0000
9.000 1.5046 0.02483 0.01746 -0.0714 0.4242 1.0000
9.250 1.5146 0.02544 0.01824 -0.0693 0.4193 1.0000
9.500 1.5372 0.02519 0.01798 -0.0686 0.4145 1.0000
9.750 1.5600 0.02492 0.01766 -0.0678 0.4091 1.0000
10.000 1.5659 0.02551 0.01845 -0.0651 0.4037 1.0000
10.250 1.5864 0.02528 0.01819 -0.0640 0.3983 1.0000
10.500 1.5959 0.02558 0.01856 -0.0616 0.3925 1.0000
10.750 1.5970 0.02608 0.01917 -0.0581 0.3862 1.0000
11.000 1.6021 0.02615 0.01920 -0.0549 0.3787 1.0000
11.250 1.5850 0.02752 0.02071 -0.0497 0.3735 1.0000
11.500 1.5927 0.02791 0.02107 -0.0476 0.3660 1.0000
11.750 1.5790 0.03007 0.02342 -0.0446 0.3598 1.0000
12.000 1.5796 0.03135 0.02466 -0.0428 0.3501 1.0000
12.250 1.5652 0.03427 0.02776 -0.0409 0.3415 1.0000
12.500 1.5578 0.03677 0.03031 -0.0394 0.3312 1.0000
12.750 1.5466 0.03978 0.03334 -0.0381 0.3191 1.0000
13.000 1.5318 0.04332 0.03689 -0.0369 0.3060 1.0000
13.250 1.5150 0.04729 0.04092 -0.0358 0.2927 1.0000
13.500 1.4966 0.05168 0.04531 -0.0350 0.2766 1.0000
13.750 1.4767 0.05646 0.05007 -0.0344 0.2579 1.0000
14.000 1.4554 0.06149 0.05503 -0.0338 0.2373 1.0000
14.250 1.4320 0.06695 0.06040 -0.0334 0.2148 1.0000
14.500 1.4058 0.07289 0.06623 -0.0332 0.1921 1.0000
14.750 1.3785 0.07917 0.07240 -0.0331 0.1695 1.0000
15.000 1.3497 0.08582 0.07893 -0.0333 0.1462 1.0000
15.250 1.3220 0.09253 0.08552 -0.0336 0.1213 1.0000
15.500 1.2950 0.09929 0.09215 -0.0342 0.0931 1.0000
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