MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.82 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh26-il-1000000.txt Download as CSV file: xf-mh26-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 26 10.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2817 0.08464 0.08300 -0.0726 0.9857 0.0072
-10.500 -0.2845 0.07918 0.07755 -0.0750 0.9853 0.0075
-10.250 -0.2876 0.07367 0.07205 -0.0775 0.9849 0.0075
-10.000 -0.2916 0.06798 0.06637 -0.0805 0.9845 0.0075
-9.750 -0.2984 0.06170 0.06009 -0.0842 0.9841 0.0073
-9.500 -0.3122 0.05273 0.05114 -0.0921 0.9835 0.0071
-9.250 -0.3392 0.04534 0.04366 -0.0976 0.9811 0.0068
-9.000 -0.3590 0.04109 0.03933 -0.0978 0.9780 0.0068
-8.750 -0.3738 0.03654 0.03464 -0.0975 0.9755 0.0068
-8.500 -0.3825 0.03274 0.03070 -0.0959 0.9732 0.0068
-8.250 -0.3860 0.02869 0.02648 -0.0943 0.9715 0.0070
-8.000 -0.3969 0.02597 0.02360 -0.0895 0.9673 0.0071
-7.750 -0.3999 0.02341 0.02088 -0.0857 0.9637 0.0072
-7.500 -0.3932 0.02053 0.01780 -0.0831 0.9615 0.0080
-7.250 -0.3768 0.01890 0.01599 -0.0816 0.9601 0.0085
-7.000 -0.3604 0.01770 0.01459 -0.0800 0.9587 0.0089
-6.750 -0.3566 0.01607 0.01275 -0.0761 0.9557 0.0089
-5.500 -0.3186 0.01540 0.01022 -0.0612 0.9457 0.0054
-5.250 -0.2901 0.01509 0.00984 -0.0614 0.9450 0.0051
-5.000 -0.2666 0.01331 0.00793 -0.0604 0.9441 0.0045
-4.750 -0.2647 0.01278 0.00732 -0.0548 0.9382 0.0043
-4.500 -0.2421 0.01203 0.00647 -0.0537 0.9362 0.0042
-4.250 -0.2171 0.01138 0.00571 -0.0531 0.9346 0.0043
-4.000 -0.1898 0.01087 0.00512 -0.0529 0.9334 0.0044
-3.750 -0.1613 0.01046 0.00464 -0.0531 0.9323 0.0048
-3.500 -0.1350 0.00989 0.00407 -0.0526 0.9311 0.0207
-3.250 -0.1218 0.00961 0.00394 -0.0496 0.9263 0.0592
-3.000 -0.1011 0.00912 0.00372 -0.0483 0.9234 0.1266
-2.750 -0.0793 0.00844 0.00343 -0.0473 0.9212 0.2384
-2.500 -0.0643 0.00739 0.00313 -0.0450 0.9190 0.4440
-2.250 -0.0523 0.00667 0.00293 -0.0417 0.9161 0.5937
-2.000 -0.0523 0.00606 0.00283 -0.0356 0.9100 0.7287
-1.750 -0.0327 0.00563 0.00282 -0.0334 0.9076 0.8491
-1.500 -0.0019 0.00554 0.00275 -0.0338 0.9061 0.8778
-1.250 0.0304 0.00547 0.00265 -0.0346 0.9045 0.8914
-1.000 0.0519 0.00549 0.00267 -0.0331 0.9003 0.9030
-0.750 0.0810 0.00550 0.00267 -0.0332 0.8968 0.9107
-0.500 0.1102 0.00546 0.00260 -0.0333 0.8939 0.9177
-0.250 0.1465 0.00553 0.00265 -0.0349 0.8917 0.9237
0.000 0.1686 0.00559 0.00271 -0.0335 0.8867 0.9304
0.250 0.2032 0.00566 0.00277 -0.0348 0.8823 0.9328
0.500 0.2384 0.00566 0.00275 -0.0364 0.8785 0.9345
0.750 0.2660 0.00570 0.00279 -0.0362 0.8718 0.9375
1.000 0.2848 0.00562 0.00269 -0.0341 0.8643 0.9429
1.250 0.3172 0.00569 0.00276 -0.0351 0.8544 0.9442
1.500 0.3550 0.00576 0.00282 -0.0373 0.8423 0.9453
1.750 0.3949 0.00585 0.00285 -0.0399 0.8245 0.9462
2.000 0.4327 0.00598 0.00287 -0.0421 0.7928 0.9471
2.250 0.4635 0.00621 0.00293 -0.0428 0.7540 0.9487
2.500 0.4856 0.00649 0.00305 -0.0416 0.7104 0.9516
2.750 0.4911 0.00672 0.00312 -0.0366 0.6705 0.9574
3.000 0.5171 0.00702 0.00324 -0.0365 0.6234 0.9585
3.250 0.5414 0.00736 0.00339 -0.0360 0.5749 0.9599
3.500 0.5649 0.00770 0.00355 -0.0353 0.5262 0.9617
3.750 0.5863 0.00804 0.00371 -0.0343 0.4796 0.9640
4.000 0.5877 0.00824 0.00381 -0.0286 0.4484 0.9700
4.250 0.6149 0.00858 0.00395 -0.0289 0.3986 0.9709
4.500 0.6423 0.00891 0.00411 -0.0293 0.3546 0.9717
4.750 0.6683 0.00927 0.00430 -0.0294 0.3089 0.9727
5.000 0.6935 0.00964 0.00449 -0.0293 0.2650 0.9739
5.500 0.7406 0.01042 0.00493 -0.0285 0.1842 0.9771
5.750 0.7590 0.01081 0.00516 -0.0270 0.1500 0.9795
6.000 0.7718 0.01108 0.00536 -0.0240 0.1295 0.9829
6.250 0.7986 0.01147 0.00564 -0.0244 0.1005 0.9836
6.500 0.8253 0.01184 0.00591 -0.0247 0.0783 0.9844
6.750 0.8511 0.01223 0.00622 -0.0249 0.0586 0.9853
7.000 0.8763 0.01264 0.00655 -0.0249 0.0422 0.9864
7.250 0.9003 0.01314 0.00697 -0.0246 0.0274 0.9877
7.500 0.9244 0.01356 0.00734 -0.0244 0.0200 0.9892
7.750 0.9469 0.01397 0.00779 -0.0238 0.0164 0.9908
8.000 0.9690 0.01423 0.00809 -0.0231 0.0145 0.9925
8.250 0.9891 0.01463 0.00851 -0.0220 0.0121 0.9941
8.500 1.0151 0.01501 0.00892 -0.0223 0.0096 0.9949
8.750 1.0407 0.01535 0.00926 -0.0225 0.0075 0.9958
9.000 1.0641 0.01593 0.00983 -0.0223 0.0042 0.9970
9.250 1.0852 0.01678 0.01076 -0.0216 0.0029 0.9983
9.500 1.1088 0.01729 0.01134 -0.0214 0.0027 0.9994
9.750 1.1254 0.01782 0.01194 -0.0199 0.0023 1.0000
10.000 1.1264 0.01847 0.01271 -0.0150 0.0022 1.0000
10.250 1.1324 0.01885 0.01313 -0.0112 0.0021 1.0000
10.500 1.1364 0.01940 0.01374 -0.0071 0.0017 1.0000
10.750 1.1265 0.02073 0.01527 -0.0005 0.0014 1.0000
11.000 1.1267 0.02152 0.01617 0.0041 0.0014 1.0000
11.250 1.1312 0.02211 0.01684 0.0078 0.0014 1.0000
11.500 1.1391 0.02256 0.01733 0.0109 0.0013 1.0000
11.750 1.1400 0.02348 0.01837 0.0150 0.0012 1.0000
12.000 1.1424 0.02440 0.01939 0.0187 0.0012 1.0000
12.250 1.1422 0.02560 0.02073 0.0226 0.0011 1.0000
12.500 1.1447 0.02673 0.02196 0.0258 0.0011 1.0000
12.750 1.1429 0.02826 0.02365 0.0293 0.0010 1.0000
13.000 1.1441 0.02966 0.02517 0.0322 0.0010 1.0000
13.250 1.1396 0.03158 0.02725 0.0354 0.0009 1.0000
13.500 1.1355 0.03357 0.02940 0.0382 0.0010 1.0000
13.750 1.1301 0.03578 0.03176 0.0406 0.0009 1.0000
14.000 1.1209 0.03850 0.03466 0.0429 0.0009 1.0000
14.250 1.1103 0.04157 0.03790 0.0446 0.0009 1.0000
14.500 1.0985 0.04506 0.04158 0.0457 0.0009 1.0000
14.750 1.0925 0.04820 0.04484 0.0460 0.0009 1.0000
15.000 1.0715 0.05359 0.05045 0.0454 0.0009 1.0000
15.250 1.0583 0.05853 0.05554 0.0439 0.0009 1.0000
15.500 1.0387 0.06492 0.06211 0.0414 0.0009 1.0000
15.750 1.0070 0.07415 0.07156 0.0369 0.0009 1.0000
16.000 0.9952 0.08029 0.07781 0.0337 0.0009 1.0000
16.250 0.9697 0.08936 0.08704 0.0289 0.0009 1.0000
16.500 0.9509 0.09741 0.09519 0.0249 0.0009 1.0000
16.750 0.9313 0.10569 0.10357 0.0209 0.0010 1.0000
17.000 0.9033 0.11596 0.11395 0.0161 0.0010 1.0000
17.250 0.8776 0.12604 0.12412 0.0115 0.0010 1.0000
17.500 0.8604 0.13427 0.13241 0.0078 0.0011 1.0000
17.750 0.8239 0.14806 0.14630 0.0018 0.0011 1.0000
18.000 0.8118 0.15584 0.15412 -0.0016 0.0012 1.0000
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Polar data table (+)
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