M6 (85%) (m685-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: M6 (85%) (m685-il) Reynolds number: 200,000 Max Cl/Cd: 62.89 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m685-il-200000-n5.txt Download as CSV file: xf-m685-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5216 0.08867 0.08490 -0.0240 1.0000 0.0191
-9.750 -0.5333 0.08239 0.07867 -0.0275 1.0000 0.0187
-9.500 -0.5518 0.07493 0.07128 -0.0331 1.0000 0.0187
-9.250 -0.5839 0.06661 0.06293 -0.0377 1.0000 0.0185
-9.000 -0.6239 0.05864 0.05484 -0.0364 1.0000 0.0182
-8.750 -0.6520 0.05117 0.04712 -0.0339 1.0000 0.0183
-8.500 -0.6743 0.04464 0.04024 -0.0299 1.0000 0.0185
-8.250 -0.6849 0.04013 0.03537 -0.0258 1.0000 0.0188
-8.000 -0.6907 0.03623 0.03105 -0.0215 1.0000 0.0196
-7.750 -0.6945 0.03235 0.02662 -0.0170 1.0000 0.0202
-7.500 -0.6920 0.02929 0.02303 -0.0130 1.0000 0.0208
-7.250 -0.6839 0.02719 0.02050 -0.0097 1.0000 0.0214
-7.000 -0.6704 0.02624 0.01948 -0.0074 1.0000 0.0218
-6.750 -0.6480 0.02534 0.01848 -0.0069 0.9973 0.0225
-6.500 -0.6162 0.02419 0.01711 -0.0082 0.9896 0.0236
-6.250 -0.5851 0.02263 0.01526 -0.0093 0.9816 0.0242
-6.000 -0.5528 0.02131 0.01367 -0.0104 0.9733 0.0249
-5.750 -0.5201 0.02032 0.01239 -0.0115 0.9638 0.0259
-5.500 -0.4877 0.01924 0.01130 -0.0128 0.9536 0.0270
-5.250 -0.4536 0.01850 0.01051 -0.0143 0.9429 0.0284
-5.000 -0.4175 0.01762 0.00952 -0.0161 0.9322 0.0297
-4.750 -0.3828 0.01675 0.00853 -0.0175 0.9190 0.0308
-4.500 -0.3480 0.01603 0.00769 -0.0189 0.9047 0.0320
-4.250 -0.3160 0.01520 0.00684 -0.0199 0.8889 0.0338
-4.000 -0.2850 0.01466 0.00623 -0.0206 0.8719 0.0358
-3.750 -0.2561 0.01423 0.00569 -0.0207 0.8550 0.0383
-3.500 -0.2294 0.01382 0.00520 -0.0203 0.8381 0.0409
-3.250 -0.2038 0.01351 0.00483 -0.0198 0.8219 0.0453
-3.000 -0.1789 0.01322 0.00452 -0.0191 0.8066 0.0519
-2.750 -0.1545 0.01296 0.00423 -0.0183 0.7919 0.0610
-2.500 -0.1306 0.01267 0.00396 -0.0173 0.7781 0.0766
-2.250 -0.1072 0.01236 0.00371 -0.0164 0.7651 0.1035
-2.000 -0.0840 0.01208 0.00351 -0.0154 0.7529 0.1433
-1.500 -0.0400 0.01141 0.00318 -0.0131 0.7295 0.2602
-1.250 -0.0239 0.01073 0.00300 -0.0108 0.7187 0.4001
-0.750 0.1074 0.01009 0.00392 -0.0248 0.6972 0.9176
-0.500 0.1454 0.01049 0.00421 -0.0263 0.6864 0.9372
-0.250 0.1890 0.01083 0.00441 -0.0291 0.6759 0.9501
0.000 0.2343 0.01108 0.00455 -0.0325 0.6644 0.9611
0.250 0.2787 0.01122 0.00461 -0.0358 0.6538 0.9704
0.500 0.3123 0.01131 0.00459 -0.0370 0.6439 0.9765
0.750 0.3452 0.01127 0.00450 -0.0382 0.6332 0.9792
1.000 0.3752 0.01127 0.00444 -0.0387 0.6231 0.9821
1.250 0.4034 0.01132 0.00442 -0.0389 0.6133 0.9853
1.500 0.4349 0.01128 0.00436 -0.0398 0.6024 0.9874
1.750 0.4657 0.01127 0.00430 -0.0405 0.5922 0.9898
2.250 0.5250 0.01130 0.00427 -0.0415 0.5671 0.9948
2.500 0.5556 0.01128 0.00422 -0.0422 0.5530 0.9969
2.750 0.5859 0.01128 0.00420 -0.0428 0.5391 0.9991
3.000 0.6118 0.01133 0.00424 -0.0426 0.5267 1.0000
3.250 0.6341 0.01142 0.00431 -0.0415 0.5153 1.0000
3.500 0.6563 0.01151 0.00440 -0.0404 0.5030 1.0000
3.750 0.6783 0.01161 0.00450 -0.0393 0.4881 1.0000
4.000 0.7000 0.01173 0.00459 -0.0381 0.4715 1.0000
4.250 0.7216 0.01186 0.00471 -0.0369 0.4537 1.0000
4.500 0.7429 0.01201 0.00485 -0.0356 0.4339 1.0000
4.750 0.7639 0.01220 0.00501 -0.0343 0.4127 1.0000
5.000 0.7836 0.01246 0.00516 -0.0328 0.3816 1.0000
5.250 0.8023 0.01280 0.00536 -0.0312 0.3441 1.0000
5.500 0.8209 0.01318 0.00562 -0.0296 0.3068 1.0000
5.750 0.8382 0.01368 0.00593 -0.0278 0.2624 1.0000
6.000 0.8542 0.01431 0.00633 -0.0260 0.2153 1.0000
6.250 0.8687 0.01509 0.00685 -0.0239 0.1643 1.0000
6.500 0.8816 0.01600 0.00744 -0.0216 0.1082 1.0000
6.750 0.8950 0.01687 0.00809 -0.0194 0.0766 1.0000
7.000 0.9101 0.01756 0.00871 -0.0173 0.0596 1.0000
7.250 0.9258 0.01818 0.00932 -0.0154 0.0485 1.0000
7.500 0.9407 0.01885 0.00996 -0.0133 0.0405 1.0000
7.750 0.9560 0.01945 0.01062 -0.0112 0.0360 1.0000
8.000 0.9687 0.02024 0.01141 -0.0088 0.0321 1.0000
8.250 0.9825 0.02089 0.01216 -0.0065 0.0302 1.0000
8.500 0.9952 0.02160 0.01294 -0.0041 0.0286 1.0000
8.750 1.0061 0.02238 0.01377 -0.0014 0.0273 1.0000
9.000 1.0145 0.02328 0.01473 0.0015 0.0263 1.0000
9.250 1.0215 0.02424 0.01575 0.0047 0.0253 1.0000
9.500 1.0288 0.02514 0.01674 0.0077 0.0247 1.0000
9.750 1.0331 0.02601 0.01769 0.0113 0.0243 1.0000
10.000 1.0355 0.02691 0.01866 0.0151 0.0238 1.0000
10.250 1.0388 0.02789 0.01973 0.0184 0.0235 1.0000
10.500 1.0426 0.02901 0.02093 0.0214 0.0230 1.0000
10.750 1.0473 0.03019 0.02218 0.0239 0.0225 1.0000
11.000 1.0529 0.03144 0.02351 0.0261 0.0223 1.0000
11.250 1.0584 0.03278 0.02492 0.0281 0.0218 1.0000
11.500 1.0642 0.03418 0.02639 0.0298 0.0214 1.0000
11.750 1.0693 0.03572 0.02797 0.0314 0.0209 1.0000
12.000 1.0749 0.03737 0.02970 0.0328 0.0206 1.0000
12.250 1.0803 0.03917 0.03158 0.0342 0.0202 1.0000
12.500 1.0866 0.04090 0.03344 0.0353 0.0201 1.0000
12.750 1.0920 0.04278 0.03546 0.0364 0.0200 1.0000
13.000 1.0963 0.04480 0.03764 0.0374 0.0198 1.0000
13.250 1.0993 0.04700 0.04000 0.0382 0.0196 1.0000
13.500 1.1011 0.04939 0.04256 0.0388 0.0195 1.0000
13.750 1.1009 0.05202 0.04537 0.0393 0.0194 1.0000
14.000 1.0989 0.05493 0.04847 0.0395 0.0193 1.0000
14.250 1.0944 0.05818 0.05190 0.0394 0.0191 1.0000
14.500 1.0883 0.06171 0.05564 0.0389 0.0190 1.0000
14.750 1.0803 0.06561 0.05972 0.0382 0.0190 1.0000
15.000 1.0695 0.06999 0.06431 0.0369 0.0190 1.0000
15.250 1.0568 0.07485 0.06936 0.0352 0.0189 1.0000
15.500 1.0426 0.08018 0.07489 0.0330 0.0189 1.0000
15.750 1.0234 0.08672 0.08164 0.0299 0.0188 1.0000
16.000 1.0057 0.09339 0.08849 0.0265 0.0190 1.0000
16.250 0.9815 0.10176 0.09706 0.0218 0.0189 1.0000
16.500 0.9568 0.11088 0.10637 0.0166 0.0191 1.0000
16.750 0.9228 0.12289 0.11858 0.0095 0.0193 1.0000
|
Polar data table (+)
Polar graphs
<< Back to M6 (85%) (m685-il)