NACA M6 (nacam6-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 200,000 Max Cl/Cd: 64.79 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam6-il-200000-n5.txt Download as CSV file: xf-nacam6-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5255 0.08614 0.08224 -0.0345 1.0000 0.0325
-10.500 -0.5453 0.07790 0.07404 -0.0399 1.0000 0.0324
-10.250 -0.5910 0.06494 0.06100 -0.0495 1.0000 0.0322
-10.000 -0.6328 0.05754 0.05341 -0.0493 1.0000 0.0321
-9.750 -0.6684 0.05269 0.04836 -0.0450 1.0000 0.0321
-9.500 -0.7001 0.04858 0.04399 -0.0390 1.0000 0.0322
-9.250 -0.7246 0.04453 0.03958 -0.0332 1.0000 0.0325
-9.000 -0.7376 0.04145 0.03618 -0.0281 1.0000 0.0327
-8.750 -0.7460 0.03877 0.03317 -0.0231 1.0000 0.0328
-8.500 -0.7504 0.03654 0.03062 -0.0183 1.0000 0.0330
-8.250 -0.7440 0.03431 0.02805 -0.0154 0.9927 0.0331
-8.000 -0.7231 0.03161 0.02498 -0.0155 0.9794 0.0335
-7.750 -0.6964 0.02950 0.02265 -0.0164 0.9684 0.0339
-7.500 -0.6666 0.02788 0.02087 -0.0176 0.9575 0.0345
-7.250 -0.6363 0.02654 0.01933 -0.0187 0.9454 0.0352
-7.000 -0.6050 0.02510 0.01766 -0.0199 0.9329 0.0357
-6.750 -0.5726 0.02371 0.01603 -0.0212 0.9202 0.0361
-6.500 -0.5401 0.02247 0.01458 -0.0223 0.9071 0.0366
-6.250 -0.5086 0.02138 0.01329 -0.0232 0.8931 0.0371
-6.000 -0.4787 0.02044 0.01218 -0.0237 0.8786 0.0375
-5.750 -0.4505 0.01961 0.01120 -0.0237 0.8638 0.0381
-5.500 -0.4236 0.01888 0.01033 -0.0235 0.8489 0.0386
-5.250 -0.3977 0.01831 0.00962 -0.0230 0.8342 0.0394
-5.000 -0.3724 0.01779 0.00898 -0.0224 0.8203 0.0400
-4.750 -0.3478 0.01704 0.00820 -0.0218 0.8071 0.0409
-4.500 -0.3239 0.01650 0.00761 -0.0209 0.7945 0.0416
-4.250 -0.3004 0.01606 0.00709 -0.0200 0.7823 0.0423
-4.000 -0.2772 0.01566 0.00663 -0.0190 0.7702 0.0431
-3.750 -0.2539 0.01530 0.00621 -0.0179 0.7593 0.0440
-3.500 -0.2306 0.01499 0.00581 -0.0169 0.7487 0.0452
-3.250 -0.2072 0.01470 0.00545 -0.0159 0.7382 0.0465
-3.000 -0.1836 0.01445 0.00512 -0.0149 0.7287 0.0478
-2.750 -0.1603 0.01417 0.00483 -0.0139 0.7188 0.0506
-2.500 -0.1366 0.01394 0.00457 -0.0129 0.7099 0.0550
-2.250 -0.1131 0.01370 0.00433 -0.0120 0.7009 0.0621
-2.000 -0.0898 0.01344 0.00411 -0.0110 0.6923 0.0777
-1.750 -0.0672 0.01314 0.00391 -0.0098 0.6840 0.1082
-1.500 -0.0445 0.01289 0.00378 -0.0088 0.6757 0.1462
-1.250 -0.0224 0.01261 0.00364 -0.0076 0.6678 0.1895
-1.000 -0.0020 0.01225 0.00351 -0.0062 0.6598 0.2587
-0.750 0.0893 0.01038 0.00392 -0.0196 0.6509 0.8508
-0.500 0.1332 0.01088 0.00436 -0.0221 0.6425 0.8923
-0.250 0.1840 0.01165 0.00503 -0.0257 0.6339 0.9180
0.000 0.2260 0.01206 0.00536 -0.0281 0.6252 0.9315
0.250 0.2641 0.01237 0.00556 -0.0299 0.6172 0.9422
0.500 0.3011 0.01264 0.00577 -0.0315 0.6087 0.9526
0.750 0.3450 0.01281 0.00585 -0.0347 0.6006 0.9595
1.000 0.3737 0.01289 0.00589 -0.0349 0.5922 0.9645
1.250 0.4053 0.01288 0.00580 -0.0358 0.5843 0.9666
1.500 0.4350 0.01287 0.00578 -0.0363 0.5759 0.9691
1.750 0.4623 0.01292 0.00576 -0.0362 0.5680 0.9723
2.000 0.4893 0.01295 0.00578 -0.0362 0.5595 0.9751
2.250 0.5202 0.01294 0.00572 -0.0369 0.5514 0.9770
2.500 0.5497 0.01293 0.00571 -0.0374 0.5413 0.9793
2.750 0.5776 0.01297 0.00571 -0.0375 0.5311 0.9819
3.000 0.6039 0.01305 0.00575 -0.0373 0.5199 0.9847
3.250 0.6342 0.01302 0.00572 -0.0380 0.5083 0.9864
3.500 0.6640 0.01302 0.00572 -0.0385 0.4979 0.9884
3.750 0.6928 0.01306 0.00574 -0.0389 0.4880 0.9906
4.000 0.7209 0.01311 0.00581 -0.0391 0.4777 0.9927
4.250 0.7497 0.01317 0.00587 -0.0395 0.4676 0.9947
4.500 0.7793 0.01319 0.00590 -0.0401 0.4564 0.9965
4.750 0.8077 0.01325 0.00595 -0.0404 0.4417 0.9984
5.000 0.8360 0.01333 0.00603 -0.0408 0.4264 1.0000
5.250 0.8569 0.01348 0.00618 -0.0395 0.4131 1.0000
5.500 0.8774 0.01365 0.00635 -0.0382 0.3990 1.0000
5.750 0.8969 0.01386 0.00653 -0.0367 0.3799 1.0000
6.000 0.9155 0.01413 0.00673 -0.0351 0.3557 1.0000
6.250 0.9333 0.01447 0.00696 -0.0334 0.3292 1.0000
6.500 0.9513 0.01480 0.00724 -0.0318 0.3049 1.0000
6.750 0.9685 0.01520 0.00756 -0.0300 0.2806 1.0000
7.000 0.9853 0.01563 0.00792 -0.0282 0.2553 1.0000
7.250 1.0012 0.01612 0.00833 -0.0263 0.2311 1.0000
7.750 1.0296 0.01732 0.00934 -0.0220 0.1809 1.0000
8.000 1.0422 0.01801 0.00992 -0.0196 0.1538 1.0000
8.250 1.0527 0.01882 0.01058 -0.0170 0.1233 1.0000
8.500 1.0614 0.01972 0.01133 -0.0141 0.0984 1.0000
8.750 1.0702 0.02057 0.01209 -0.0112 0.0846 1.0000
9.000 1.0793 0.02134 0.01286 -0.0083 0.0752 1.0000
9.250 1.0865 0.02218 0.01370 -0.0052 0.0680 1.0000
9.500 1.0947 0.02288 0.01446 -0.0022 0.0621 1.0000
9.750 1.0979 0.02373 0.01530 0.0015 0.0577 1.0000
10.000 1.1001 0.02439 0.01603 0.0056 0.0543 1.0000
10.250 1.1002 0.02521 0.01688 0.0096 0.0513 1.0000
10.500 1.0988 0.02625 0.01794 0.0134 0.0490 1.0000
10.750 1.1017 0.02725 0.01903 0.0163 0.0468 1.0000
11.000 1.1044 0.02840 0.02026 0.0189 0.0447 1.0000
11.250 1.1060 0.02974 0.02165 0.0213 0.0428 1.0000
11.500 1.1064 0.03131 0.02325 0.0235 0.0413 1.0000
11.750 1.1081 0.03291 0.02492 0.0253 0.0397 1.0000
12.000 1.1110 0.03454 0.02665 0.0269 0.0384 1.0000
12.250 1.1138 0.03626 0.02845 0.0282 0.0369 1.0000
12.500 1.1156 0.03814 0.03041 0.0294 0.0355 1.0000
12.750 1.1152 0.04031 0.03262 0.0304 0.0344 1.0000
13.000 1.1155 0.04249 0.03486 0.0313 0.0333 1.0000
13.250 1.1182 0.04451 0.03699 0.0321 0.0324 1.0000
13.500 1.1202 0.04665 0.03923 0.0327 0.0312 1.0000
13.750 1.1217 0.04890 0.04155 0.0332 0.0302 1.0000
14.000 1.1224 0.05128 0.04401 0.0336 0.0292 1.0000
14.250 1.1213 0.05389 0.04666 0.0338 0.0285 1.0000
14.500 1.1201 0.05653 0.04935 0.0341 0.0278 1.0000
14.750 1.1220 0.05898 0.05194 0.0343 0.0271 1.0000
15.000 1.1227 0.06162 0.05470 0.0344 0.0262 1.0000
15.250 1.1228 0.06438 0.05758 0.0342 0.0254 1.0000
15.500 1.1228 0.06720 0.06049 0.0341 0.0249 1.0000
15.750 1.1220 0.07023 0.06361 0.0336 0.0242 1.0000
16.000 1.1203 0.07345 0.06688 0.0329 0.0236 1.0000
16.250 1.1184 0.07668 0.07017 0.0323 0.0231 1.0000
16.500 1.1168 0.07996 0.07355 0.0318 0.0227 1.0000
16.750 1.1135 0.08368 0.07746 0.0308 0.0220 1.0000
17.000 1.1105 0.08734 0.08126 0.0299 0.0217 1.0000
17.250 1.1058 0.09142 0.08548 0.0286 0.0211 1.0000
17.500 1.1011 0.09549 0.08968 0.0274 0.0208 1.0000
17.750 1.0956 0.09980 0.09412 0.0259 0.0204 1.0000
18.000 1.0894 0.10430 0.09874 0.0242 0.0202 1.0000
18.250 1.0824 0.10905 0.10360 0.0222 0.0198 1.0000
18.500 1.0757 0.11386 0.10851 0.0202 0.0195 1.0000
18.750 1.0685 0.11878 0.11353 0.0180 0.0192 1.0000
19.000 1.0617 0.12369 0.11853 0.0158 0.0190 1.0000
19.250 1.0541 0.12881 0.12374 0.0135 0.0188 1.0000
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