NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M8 AIRFOIL (m8-il) Reynolds number: 200,000 Max Cl/Cd: 60.24 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m8-il-200000.txt Download as CSV file: xf-m8-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M8 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1762 0.10383 0.09982 -0.0105 0.7229 0.0491
-8.500 -0.1699 0.10147 0.09748 -0.0121 0.7142 0.0512
-8.250 -0.1828 0.10144 0.09745 -0.0163 0.7076 0.0522
-8.000 -0.1722 0.09731 0.09332 -0.0168 0.7005 0.0527
-7.750 -0.1529 0.09350 0.08946 -0.0159 0.6926 0.0534
-7.500 -0.1413 0.09103 0.08693 -0.0158 0.6861 0.0546
-7.250 -0.1325 0.08872 0.08465 -0.0165 0.6783 0.0559
-7.000 -0.1271 0.08655 0.08246 -0.0172 0.6721 0.0576
-6.750 -0.1321 0.08630 0.08219 -0.0260 0.6673 0.0602
-6.500 -0.1194 0.08188 0.07780 -0.0250 0.6603 0.0610
-6.250 -0.1039 0.07896 0.07484 -0.0232 0.6543 0.0620
-6.000 -0.0895 0.07661 0.07245 -0.0237 0.6487 0.0635
-5.750 -0.0746 0.07419 0.07004 -0.0255 0.6421 0.0656
-5.500 -0.0488 0.07167 0.06737 -0.0394 0.6372 0.0699
-5.250 -0.0386 0.06812 0.06379 -0.0362 0.6324 0.0707
-5.000 -0.0230 0.06576 0.06148 -0.0344 0.6254 0.0721
-4.750 -0.0041 0.06360 0.05927 -0.0351 0.6194 0.0745
-4.500 0.0352 0.06027 0.05567 -0.0472 0.6151 0.0809
-4.250 0.0488 0.05739 0.05285 -0.0454 0.6084 0.0818
-4.000 0.0668 0.05527 0.05071 -0.0445 0.6023 0.0832
-3.750 0.0884 0.05341 0.04874 -0.0449 0.5972 0.0864
-3.500 0.1261 0.05005 0.04523 -0.0522 0.5906 0.0938
-3.250 0.1450 0.04812 0.04327 -0.0511 0.5842 0.0954
-3.000 0.1682 0.04641 0.04144 -0.0513 0.5787 0.0984
-2.750 0.2047 0.04360 0.03847 -0.0562 0.5713 0.1069
-2.500 0.2458 0.03251 0.02673 -0.0639 0.5672 0.0815
-2.250 0.2751 0.02101 0.01381 -0.0679 0.5638 0.0749
-2.000 0.3027 0.01977 0.01220 -0.0676 0.5569 0.0774
-1.750 0.3307 0.01885 0.01093 -0.0673 0.5495 0.0793
-1.500 0.3582 0.01801 0.00980 -0.0668 0.5435 0.0817
-1.250 0.3856 0.01744 0.00931 -0.0664 0.5351 0.0857
-1.000 0.4134 0.01705 0.00875 -0.0659 0.5278 0.0909
-0.750 0.4409 0.01666 0.00835 -0.0654 0.5197 0.0965
-0.500 0.4687 0.01638 0.00799 -0.0649 0.5116 0.1044
-0.250 0.4963 0.01636 0.00798 -0.0644 0.5044 0.1169
0.000 0.5238 0.01715 0.00905 -0.0637 0.4958 0.1300
0.250 0.5511 0.01822 0.01017 -0.0629 0.4892 0.1412
0.500 0.5797 0.01883 0.01080 -0.0624 0.4810 0.1631
0.750 0.6078 0.01956 0.01139 -0.0618 0.4742 0.1837
1.000 0.6344 0.01996 0.01182 -0.0613 0.4676 0.1966
1.250 0.6611 0.02020 0.01202 -0.0609 0.4605 0.2180
1.500 0.6864 0.02010 0.01194 -0.0604 0.4551 0.2350
1.750 0.7115 0.02006 0.01195 -0.0600 0.4491 0.2623
2.000 0.7357 0.01996 0.01193 -0.0594 0.4429 0.2999
2.250 0.7581 0.01990 0.01186 -0.0585 0.4378 0.3706
2.500 0.7808 0.01880 0.01083 -0.0579 0.4323 0.4128
2.750 0.8119 0.01918 0.01104 -0.0581 0.4263 0.3873
3.000 0.8386 0.01877 0.01056 -0.0578 0.4213 0.3926
3.250 0.8672 0.01897 0.01066 -0.0577 0.4163 0.3836
3.500 0.8947 0.01897 0.01064 -0.0575 0.4104 0.3845
3.750 0.9220 0.01885 0.01045 -0.0573 0.4052 0.3816
4.000 0.9504 0.01920 0.01065 -0.0571 0.3998 0.3699
4.250 0.9773 0.01902 0.01052 -0.0570 0.3934 0.3609
4.500 1.0049 0.01913 0.01051 -0.0567 0.3874 0.3487
4.750 1.0322 0.01939 0.01069 -0.0565 0.3811 0.3364
5.000 1.0585 0.01932 0.01065 -0.0562 0.3743 0.3307
5.250 1.0857 0.01969 0.01080 -0.0558 0.3683 0.3209
5.500 1.1109 0.01966 0.01090 -0.0555 0.3608 0.3183
5.750 1.1366 0.01974 0.01092 -0.0552 0.3538 0.3152
6.000 1.1617 0.01995 0.01113 -0.0548 0.3461 0.3099
6.250 1.1867 0.02029 0.01140 -0.0542 0.3380 0.3044
6.500 1.2109 0.02049 0.01159 -0.0538 0.3300 0.3021
6.750 1.2347 0.02067 0.01181 -0.0533 0.3215 0.2996
7.000 1.2582 0.02100 0.01211 -0.0527 0.3137 0.2967
7.250 1.2812 0.02127 0.01241 -0.0521 0.3056 0.2939
7.500 1.3045 0.02171 0.01274 -0.0515 0.2990 0.2910
7.750 1.3264 0.02209 0.01322 -0.0508 0.2919 0.2889
8.000 1.3490 0.02245 0.01355 -0.0502 0.2863 0.2877
8.250 1.3711 0.02287 0.01399 -0.0495 0.2813 0.2867
8.500 1.3923 0.02324 0.01448 -0.0488 0.2760 0.2858
8.750 1.4139 0.02362 0.01488 -0.0481 0.2717 0.2848
9.000 1.4365 0.02410 0.01529 -0.0476 0.2681 0.2840
9.250 1.4570 0.02463 0.01597 -0.0469 0.2643 0.2832
9.500 1.4775 0.02514 0.01657 -0.0462 0.2607 0.2825
9.750 1.4979 0.02564 0.01712 -0.0454 0.2576 0.2820
10.000 1.5186 0.02615 0.01762 -0.0447 0.2548 0.2821
10.250 1.5409 0.02679 0.01822 -0.0442 0.2520 0.2825
10.500 1.5564 0.02747 0.01906 -0.0429 0.2494 0.2830
10.750 1.5726 0.02816 0.01986 -0.0418 0.2468 0.2835
11.000 1.5895 0.02885 0.02063 -0.0407 0.2445 0.2838
11.250 1.6070 0.02954 0.02137 -0.0398 0.2424 0.2838
11.500 1.6256 0.03023 0.02209 -0.0389 0.2405 0.2840
11.750 1.6490 0.03098 0.02281 -0.0387 0.2384 0.2842
12.000 1.6664 0.03193 0.02383 -0.0379 0.2363 0.2847
12.250 1.6690 0.03296 0.02504 -0.0353 0.2344 0.2849
12.500 1.6725 0.03408 0.02630 -0.0333 0.2321 0.2853
12.750 1.6795 0.03516 0.02747 -0.0318 0.2296 0.2861
13.000 1.6908 0.03606 0.02841 -0.0307 0.2270 0.2870
13.250 1.7104 0.03672 0.02903 -0.0302 0.2241 0.2881
13.500 1.7286 0.03780 0.03014 -0.0297 0.2212 0.2902
13.750 1.7201 0.03973 0.03229 -0.0279 0.2193 0.2907
14.000 1.7147 0.04178 0.03451 -0.0267 0.2171 0.2921
14.250 1.7145 0.04369 0.03655 -0.0259 0.2147 0.2934
14.500 1.7206 0.04519 0.03813 -0.0253 0.2122 0.2959
14.750 1.7417 0.04561 0.03851 -0.0249 0.2089 0.3005
15.000 1.7559 0.04692 0.03985 -0.0244 0.2058 0.3072
15.250 1.7360 0.05041 0.04359 -0.0239 0.2040 0.3089
15.500 1.7185 0.05412 0.04751 -0.0238 0.2019 0.3104
15.750 1.7055 0.05762 0.05118 -0.0241 0.1992 0.3167
16.000 1.7458 0.05750 0.05173 -0.0282 0.1937 1.0000
16.250 1.7549 0.05898 0.05321 -0.0278 0.1903 1.0000
16.500 1.7269 0.06438 0.05888 -0.0288 0.1887 1.0000
16.750 1.6988 0.07034 0.06507 -0.0303 0.1870 1.0000
17.000 1.6662 0.07743 0.07240 -0.0324 0.1853 1.0000
17.750 1.5699 0.10101 0.09650 -0.0410 0.1790 1.0000
18.000 1.4993 0.11634 0.11202 -0.0474 0.1766 1.0000
18.250 1.1531 0.19447 0.18937 -0.0857 0.1494 0.2828
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