M6 (85%) (m685-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 50,000 Max Cl/Cd: 34.25 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m685-il-50000-n5.txt Download as CSV file: xf-m685-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: M6 (85%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4998 0.11777 0.11043 -0.0162 1.0000 0.1253
-9.750 -0.5028 0.10126 0.09390 -0.0248 1.0000 0.0684
-9.500 -0.5011 0.09710 0.08978 -0.0260 1.0000 0.0679
-9.250 -0.5012 0.09284 0.08556 -0.0274 1.0000 0.0671
-9.000 -0.5034 0.08849 0.08127 -0.0293 1.0000 0.0660
-8.750 -0.5105 0.08401 0.07684 -0.0311 1.0000 0.0647
-8.500 -0.5212 0.07980 0.07266 -0.0318 1.0000 0.0635
-8.250 -0.5338 0.07561 0.06847 -0.0318 1.0000 0.0624
-8.000 -0.5457 0.07110 0.06390 -0.0315 1.0000 0.0612
-7.750 -0.5576 0.06643 0.05909 -0.0306 1.0000 0.0600
-7.500 -0.5691 0.06170 0.05408 -0.0288 1.0000 0.0589
-7.000 -0.5780 0.05394 0.04559 -0.0234 1.0000 0.0578
-6.750 -0.5750 0.05079 0.04216 -0.0207 1.0000 0.0578
-6.500 -0.5696 0.04788 0.03906 -0.0181 1.0000 0.0582
-6.250 -0.5601 0.04569 0.03678 -0.0159 1.0000 0.0593
-6.000 -0.5508 0.04366 0.03461 -0.0135 1.0000 0.0607
-5.750 -0.5421 0.04153 0.03224 -0.0108 1.0000 0.0622
-5.500 -0.5330 0.03936 0.02976 -0.0080 1.0000 0.0636
-5.250 -0.5229 0.03723 0.02730 -0.0052 1.0000 0.0647
-5.000 -0.5116 0.03532 0.02501 -0.0025 1.0000 0.0664
-4.750 -0.4991 0.03360 0.02282 0.0003 1.0000 0.0686
-4.500 -0.4855 0.03211 0.02121 0.0023 1.0000 0.0708
-4.250 -0.4716 0.03100 0.02002 0.0044 1.0000 0.0738
-4.000 -0.4563 0.02992 0.01875 0.0063 1.0000 0.0773
-3.750 -0.4170 0.02837 0.01675 0.0042 0.9917 0.0819
-3.500 -0.3757 0.02704 0.01544 0.0012 0.9823 0.0888
-3.250 -0.3299 0.02585 0.01402 -0.0021 0.9741 0.0975
-3.000 -0.2856 0.02487 0.01294 -0.0054 0.9645 0.1108
-2.750 -0.2446 0.02386 0.01200 -0.0082 0.9542 0.1298
-2.500 -0.2050 0.02280 0.01111 -0.0108 0.9438 0.1708
-2.250 -0.1074 0.01970 0.01131 -0.0218 0.9561 0.8907
-2.000 0.0056 0.02016 0.01108 -0.0368 0.9682 1.0000
-1.750 0.0499 0.02004 0.01065 -0.0407 0.9517 1.0000
-1.500 0.0943 0.01991 0.01025 -0.0445 0.9361 1.0000
-1.250 0.1364 0.01979 0.00991 -0.0477 0.9202 1.0000
-1.000 0.1764 0.01968 0.00961 -0.0504 0.9042 1.0000
-0.750 0.2138 0.01959 0.00935 -0.0525 0.8879 1.0000
-0.500 0.2480 0.01955 0.00915 -0.0539 0.8717 1.0000
-0.250 0.2790 0.01954 0.00901 -0.0546 0.8554 1.0000
0.000 0.3072 0.01957 0.00893 -0.0547 0.8395 1.0000
0.250 0.3332 0.01965 0.00891 -0.0543 0.8238 1.0000
0.500 0.3576 0.01975 0.00893 -0.0536 0.8086 1.0000
0.750 0.3810 0.01988 0.00899 -0.0527 0.7937 1.0000
1.000 0.4038 0.02003 0.00909 -0.0517 0.7794 1.0000
1.250 0.4263 0.02020 0.00921 -0.0506 0.7656 1.0000
1.500 0.4487 0.02037 0.00935 -0.0495 0.7523 1.0000
1.750 0.4716 0.02053 0.00948 -0.0483 0.7397 1.0000
2.000 0.4929 0.02076 0.00971 -0.0470 0.7263 1.0000
2.250 0.5142 0.02102 0.00998 -0.0458 0.7130 1.0000
2.500 0.5361 0.02127 0.01027 -0.0446 0.7000 1.0000
2.750 0.5583 0.02151 0.01054 -0.0434 0.6876 1.0000
3.000 0.5812 0.02172 0.01075 -0.0422 0.6757 1.0000
3.250 0.6022 0.02200 0.01112 -0.0408 0.6622 1.0000
3.500 0.6227 0.02231 0.01148 -0.0394 0.6484 1.0000
3.750 0.6434 0.02259 0.01183 -0.0379 0.6346 1.0000
4.000 0.6641 0.02285 0.01216 -0.0363 0.6205 1.0000
4.250 0.6848 0.02311 0.01251 -0.0347 0.6062 1.0000
4.500 0.7054 0.02336 0.01284 -0.0331 0.5918 1.0000
4.750 0.7260 0.02362 0.01318 -0.0315 0.5773 1.0000
5.000 0.7464 0.02388 0.01356 -0.0298 0.5624 1.0000
5.250 0.7666 0.02415 0.01394 -0.0281 0.5472 1.0000
5.500 0.7863 0.02444 0.01436 -0.0263 0.5314 1.0000
5.750 0.8049 0.02474 0.01481 -0.0244 0.5138 1.0000
6.000 0.8225 0.02491 0.01508 -0.0221 0.4921 1.0000
6.250 0.8388 0.02496 0.01518 -0.0194 0.4654 1.0000
6.500 0.8532 0.02506 0.01531 -0.0165 0.4344 1.0000
6.750 0.8668 0.02531 0.01558 -0.0136 0.4019 1.0000
7.000 0.8785 0.02567 0.01587 -0.0105 0.3642 1.0000
7.250 0.8870 0.02627 0.01634 -0.0072 0.3186 1.0000
7.500 0.8929 0.02717 0.01705 -0.0038 0.2663 1.0000
7.750 0.8947 0.02850 0.01802 -0.0002 0.2132 1.0000
8.000 0.8939 0.03019 0.01936 0.0035 0.1685 1.0000
8.250 0.8924 0.03200 0.02088 0.0070 0.1378 1.0000
8.500 0.8927 0.03373 0.02249 0.0103 0.1179 1.0000
8.750 0.8922 0.03546 0.02410 0.0136 0.1050 1.0000
9.000 0.8899 0.03715 0.02570 0.0171 0.0965 1.0000
9.250 0.8915 0.03879 0.02738 0.0200 0.0886 1.0000
9.500 0.8940 0.04056 0.02911 0.0226 0.0828 1.0000
9.750 0.9009 0.04221 0.03088 0.0247 0.0767 1.0000
10.000 0.9091 0.04394 0.03255 0.0265 0.0724 1.0000
10.250 0.9256 0.04556 0.03438 0.0281 0.0684 1.0000
10.500 0.9388 0.04732 0.03634 0.0296 0.0644 1.0000
10.750 0.9514 0.04912 0.03815 0.0309 0.0611 1.0000
11.000 0.9661 0.05120 0.04037 0.0321 0.0587 1.0000
11.250 0.9765 0.05362 0.04312 0.0334 0.0572 1.0000
11.500 0.9821 0.05626 0.04606 0.0347 0.0559 1.0000
11.750 0.9826 0.05908 0.04915 0.0359 0.0547 1.0000
12.000 0.9802 0.06210 0.05240 0.0369 0.0539 1.0000
12.250 0.9743 0.06536 0.05587 0.0375 0.0529 1.0000
12.500 0.9662 0.06893 0.05964 0.0377 0.0523 1.0000
12.750 0.9549 0.07300 0.06391 0.0373 0.0519 1.0000
13.000 0.9414 0.07746 0.06855 0.0364 0.0515 1.0000
13.250 0.9196 0.08335 0.07468 0.0342 0.0517 1.0000
13.500 0.8884 0.09124 0.08281 0.0301 0.0523 1.0000
13.750 0.8393 0.10392 0.09570 0.0223 0.0543 1.0000
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Polar data table (+)
Polar graphs
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