M6 (85%) (m685-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 500,000 Max Cl/Cd: 84.84 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m685-il-500000.txt Download as CSV file: xf-m685-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4167 0.08553 0.08329 -0.0280 1.0000 0.0259
-10.000 -0.4239 0.07986 0.07763 -0.0301 1.0000 0.0259
-9.750 -0.4329 0.07387 0.07166 -0.0326 1.0000 0.0259
-9.500 -0.6411 0.05525 0.05275 -0.0416 1.0000 0.0175
-9.250 -0.6443 0.05504 0.05253 -0.0384 1.0000 0.0174
-9.000 -0.6726 0.04836 0.04564 -0.0351 1.0000 0.0172
-8.750 -0.7082 0.04059 0.03746 -0.0295 1.0000 0.0169
-8.500 -0.7473 0.03227 0.02839 -0.0212 1.0000 0.0169
-8.250 -0.7624 0.02722 0.02266 -0.0146 1.0000 0.0172
-8.000 -0.7625 0.02434 0.01932 -0.0099 1.0000 0.0179
-7.750 -0.7486 0.02363 0.01858 -0.0076 1.0000 0.0183
-7.500 -0.7355 0.02291 0.01777 -0.0050 1.0000 0.0187
-7.250 -0.7226 0.02235 0.01715 -0.0024 1.0000 0.0192
-7.000 -0.6906 0.02127 0.01583 -0.0036 0.9971 0.0206
-6.750 -0.6563 0.02013 0.01436 -0.0052 0.9930 0.0214
-6.500 -0.6230 0.01885 0.01304 -0.0069 0.9884 0.0223
-6.250 -0.5874 0.01780 0.01187 -0.0088 0.9844 0.0227
-6.000 -0.5537 0.01698 0.01095 -0.0102 0.9780 0.0232
-5.750 -0.5184 0.01614 0.01000 -0.0119 0.9724 0.0236
-5.500 -0.4839 0.01534 0.00912 -0.0134 0.9648 0.0241
-5.250 -0.4475 0.01468 0.00838 -0.0152 0.9562 0.0248
-5.000 -0.4085 0.01389 0.00750 -0.0177 0.9478 0.0252
-4.750 -0.3709 0.01319 0.00672 -0.0197 0.9341 0.0255
-4.500 -0.3343 0.01260 0.00605 -0.0216 0.9171 0.0258
-4.250 -0.3047 0.01191 0.00526 -0.0219 0.8956 0.0264
-4.000 -0.2793 0.01140 0.00466 -0.0213 0.8731 0.0270
-3.750 -0.2549 0.01108 0.00425 -0.0205 0.8527 0.0280
-3.500 -0.2309 0.01087 0.00398 -0.0195 0.8334 0.0298
-3.250 -0.2069 0.01068 0.00368 -0.0185 0.8159 0.0317
-3.000 -0.1847 0.01028 0.00323 -0.0172 0.7999 0.0370
-2.750 -0.1610 0.01005 0.00292 -0.0162 0.7851 0.0416
-2.500 -0.1370 0.00988 0.00270 -0.0153 0.7713 0.0475
-2.250 -0.1134 0.00966 0.00251 -0.0143 0.7582 0.0618
-2.000 -0.0901 0.00940 0.00235 -0.0133 0.7456 0.0950
-1.750 -0.0669 0.00916 0.00224 -0.0123 0.7339 0.1403
-1.500 -0.0437 0.00895 0.00212 -0.0113 0.7230 0.1827
-1.250 -0.0211 0.00868 0.00203 -0.0103 0.7119 0.2459
-1.000 -0.0036 0.00806 0.00191 -0.0083 0.7018 0.3936
-0.750 -0.0080 0.00670 0.00175 -0.0015 0.6930 0.7259
-0.500 0.0632 0.00648 0.00207 -0.0103 0.6824 0.9060
-0.250 0.1070 0.00671 0.00223 -0.0135 0.6726 0.9239
0.000 0.1456 0.00705 0.00248 -0.0153 0.6628 0.9364
0.250 0.1929 0.00751 0.00288 -0.0190 0.6527 0.9463
0.500 0.2557 0.00829 0.00357 -0.0256 0.6423 0.9628
0.750 0.3103 0.00856 0.00376 -0.0311 0.6315 0.9690
1.000 0.3462 0.00873 0.00389 -0.0327 0.6214 0.9757
1.250 0.3912 0.00873 0.00382 -0.0363 0.6099 0.9786
1.750 0.4563 0.00880 0.00379 -0.0384 0.5839 0.9857
2.000 0.4900 0.00872 0.00368 -0.0397 0.5724 0.9872
2.250 0.5226 0.00869 0.00361 -0.0409 0.5621 0.9891
2.500 0.5540 0.00867 0.00356 -0.0417 0.5504 0.9913
2.750 0.5843 0.00868 0.00354 -0.0424 0.5367 0.9937
3.000 0.6161 0.00865 0.00349 -0.0433 0.5231 0.9955
3.250 0.6483 0.00860 0.00342 -0.0444 0.5094 0.9974
3.500 0.6799 0.00859 0.00337 -0.0453 0.4932 0.9992
3.750 0.7066 0.00863 0.00339 -0.0453 0.4764 1.0000
4.000 0.7276 0.00877 0.00342 -0.0440 0.4474 1.0000
4.250 0.7493 0.00889 0.00349 -0.0429 0.4279 1.0000
4.500 0.7702 0.00908 0.00359 -0.0416 0.3987 1.0000
4.750 0.7907 0.00932 0.00370 -0.0403 0.3662 1.0000
5.000 0.8106 0.00961 0.00385 -0.0389 0.3312 1.0000
5.250 0.8301 0.00996 0.00405 -0.0374 0.2909 1.0000
5.500 0.8489 0.01038 0.00429 -0.0359 0.2489 1.0000
5.750 0.8666 0.01091 0.00459 -0.0343 0.2039 1.0000
6.000 0.8841 0.01145 0.00495 -0.0325 0.1629 1.0000
6.250 0.8989 0.01223 0.00541 -0.0305 0.1041 1.0000
6.500 0.9143 0.01293 0.00592 -0.0284 0.0711 1.0000
6.750 0.9302 0.01357 0.00642 -0.0264 0.0465 1.0000
7.000 0.9457 0.01424 0.00701 -0.0242 0.0341 1.0000
7.250 0.9625 0.01478 0.00759 -0.0222 0.0301 1.0000
7.500 0.9785 0.01535 0.00817 -0.0202 0.0273 1.0000
7.750 0.9920 0.01609 0.00897 -0.0177 0.0256 1.0000
8.000 1.0082 0.01659 0.00953 -0.0157 0.0244 1.0000
8.250 1.0234 0.01715 0.01014 -0.0135 0.0237 1.0000
8.500 1.0374 0.01776 0.01081 -0.0112 0.0232 1.0000
8.750 1.0503 0.01842 0.01153 -0.0086 0.0227 1.0000
9.000 1.0626 0.01910 0.01225 -0.0061 0.0223 1.0000
9.250 1.0729 0.01987 0.01307 -0.0032 0.0219 1.0000
9.500 1.0817 0.02070 0.01394 -0.0002 0.0214 1.0000
9.750 1.0896 0.02156 0.01486 0.0030 0.0213 1.0000
10.000 1.0950 0.02254 0.01590 0.0065 0.0210 1.0000
10.250 1.0970 0.02343 0.01684 0.0107 0.0209 1.0000
10.500 1.0969 0.02459 0.01807 0.0149 0.0207 1.0000
10.750 1.0997 0.02618 0.01973 0.0184 0.0204 1.0000
11.000 1.1078 0.02727 0.02089 0.0210 0.0203 1.0000
11.250 1.1162 0.02835 0.02206 0.0234 0.0203 1.0000
11.500 1.1246 0.02949 0.02330 0.0256 0.0202 1.0000
11.750 1.1326 0.03070 0.02461 0.0278 0.0200 1.0000
12.000 1.1410 0.03209 0.02611 0.0297 0.0200 1.0000
12.250 1.1478 0.03355 0.02769 0.0316 0.0198 1.0000
12.500 1.1550 0.03527 0.02954 0.0333 0.0198 1.0000
12.750 1.1599 0.03712 0.03154 0.0350 0.0198 1.0000
13.000 1.1629 0.03913 0.03370 0.0367 0.0198 1.0000
13.250 1.1635 0.04137 0.03611 0.0382 0.0197 1.0000
13.500 1.1629 0.04393 0.03883 0.0395 0.0198 1.0000
13.750 1.1588 0.04671 0.04179 0.0406 0.0198 1.0000
14.000 1.1522 0.04993 0.04519 0.0415 0.0199 1.0000
14.250 1.1420 0.05358 0.04903 0.0419 0.0200 1.0000
14.500 1.1321 0.05703 0.05265 0.0419 0.0199 1.0000
14.750 1.1177 0.06177 0.05756 0.0416 0.0202 1.0000
15.000 1.1089 0.06630 0.06223 0.0414 0.0205 1.0000
15.250 1.0860 0.07103 0.06717 0.0388 0.0201 1.0000
15.500 1.0711 0.07581 0.07209 0.0367 0.0200 1.0000
15.750 1.0537 0.08210 0.07852 0.0353 0.0205 1.0000
16.000 1.0316 0.08872 0.08529 0.0318 0.0204 1.0000
16.250 1.0307 0.09214 0.08880 0.0297 0.0207 1.0000
16.500 1.0020 0.10083 0.09765 0.0247 0.0206 1.0000
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