MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 500,000 Max Cl/Cd: 54.69 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh27-il-500000-n5.txt Download as CSV file: xf-mh27-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3669 0.10152 0.09899 -0.0757 0.9816 0.0042
-11.500 -0.3688 0.09722 0.09470 -0.0774 0.9802 0.0042
-11.250 -0.3734 0.09209 0.08959 -0.0798 0.9789 0.0040
-11.000 -0.3769 0.08678 0.08430 -0.0828 0.9776 0.0039
-10.750 -0.3842 0.07998 0.07753 -0.0872 0.9763 0.0039
-10.500 -0.3894 0.07308 0.07065 -0.0929 0.9750 0.0038
-10.250 -0.4036 0.06277 0.06026 -0.1035 0.9736 0.0038
-10.000 -0.4206 0.05604 0.05340 -0.1075 0.9723 0.0037
-9.750 -0.4329 0.05083 0.04800 -0.1086 0.9712 0.0036
-9.500 -0.4604 0.04821 0.04527 -0.1024 0.9652 0.0036
-9.250 -0.4714 0.04503 0.04191 -0.0991 0.9623 0.0035
-9.000 -0.4851 0.04046 0.03706 -0.0950 0.9598 0.0034
-8.750 -0.4937 0.03542 0.03163 -0.0910 0.9581 0.0032
-8.500 -0.5215 0.03302 0.02897 -0.0808 0.9511 0.0031
-8.250 -0.5335 0.02750 0.02276 -0.0741 0.9481 0.0028
-8.000 -0.5224 0.02456 0.01937 -0.0714 0.9467 0.0028
-7.750 -0.5048 0.02258 0.01704 -0.0699 0.9458 0.0027
-7.500 -0.4846 0.02082 0.01496 -0.0688 0.9451 0.0028
-7.250 -0.4886 0.02048 0.01451 -0.0622 0.9400 0.0027
-7.000 -0.4766 0.01946 0.01331 -0.0591 0.9374 0.0028
-6.750 -0.4557 0.01849 0.01219 -0.0580 0.9359 0.0028
-6.500 -0.4332 0.01759 0.01116 -0.0572 0.9349 0.0029
-6.250 -0.4093 0.01678 0.01024 -0.0567 0.9339 0.0029
-6.000 -0.3849 0.01607 0.00943 -0.0563 0.9331 0.0031
-5.750 -0.3603 0.01541 0.00868 -0.0558 0.9323 0.0033
-5.500 -0.3345 0.01486 0.00804 -0.0557 0.9316 0.0034
-5.250 -0.3465 0.01483 0.00795 -0.0471 0.9241 0.0036
-5.000 -0.3238 0.01444 0.00750 -0.0461 0.9225 0.0038
-4.750 -0.2979 0.01404 0.00703 -0.0459 0.9213 0.0044
-4.500 -0.2713 0.01355 0.00648 -0.0458 0.9204 0.0055
-4.250 -0.2427 0.01322 0.00611 -0.0462 0.9196 0.0065
-4.000 -0.2149 0.01279 0.00574 -0.0464 0.9188 0.0172
-3.750 -0.2177 0.01270 0.00569 -0.0398 0.9119 0.0307
-3.500 -0.1963 0.01224 0.00540 -0.0387 0.9095 0.0702
-3.250 -0.1728 0.01154 0.00510 -0.0382 0.9079 0.1603
-3.000 -0.1468 0.01093 0.00480 -0.0382 0.9067 0.2465
-2.500 -0.1262 0.01006 0.00449 -0.0311 0.8980 0.4055
-2.250 -0.1160 0.00925 0.00419 -0.0275 0.8947 0.5429
-1.750 -0.0764 0.00791 0.00375 -0.0238 0.8916 0.7718
-1.250 -0.0145 0.00812 0.00420 -0.0247 0.8840 0.8739
-1.000 0.0191 0.00815 0.00421 -0.0258 0.8818 0.8903
-0.750 0.0529 0.00820 0.00422 -0.0269 0.8799 0.9033
-0.500 0.1021 0.00829 0.00428 -0.0315 0.8789 0.9073
-0.250 0.0939 0.00834 0.00432 -0.0233 0.8690 0.9171
0.000 0.1361 0.00835 0.00430 -0.0264 0.8665 0.9188
0.500 0.1729 0.00838 0.00430 -0.0220 0.8523 0.9301
0.750 0.2109 0.00857 0.00449 -0.0242 0.8438 0.9319
1.000 0.2607 0.00852 0.00442 -0.0291 0.8379 0.9326
1.250 0.2981 0.00855 0.00443 -0.0312 0.8272 0.9340
1.500 0.3456 0.00840 0.00424 -0.0356 0.8124 0.9339
1.750 0.3944 0.00829 0.00403 -0.0404 0.7896 0.9334
2.000 0.4344 0.00830 0.00388 -0.0431 0.7561 0.9336
2.250 0.4621 0.00849 0.00390 -0.0432 0.7159 0.9350
2.500 0.4785 0.00875 0.00398 -0.0407 0.6749 0.9382
2.750 0.4782 0.00894 0.00403 -0.0346 0.6408 0.9443
3.000 0.4985 0.00928 0.00419 -0.0331 0.5968 0.9459
3.250 0.5155 0.00959 0.00434 -0.0310 0.5572 0.9481
3.500 0.5275 0.00986 0.00448 -0.0278 0.5217 0.9515
3.750 0.5248 0.01004 0.00454 -0.0212 0.4915 0.9576
4.000 0.5474 0.01036 0.00472 -0.0205 0.4512 0.9587
4.250 0.5695 0.01069 0.00489 -0.0197 0.4119 0.9601
4.500 0.5900 0.01102 0.00507 -0.0186 0.3741 0.9618
4.750 0.6094 0.01135 0.00528 -0.0173 0.3381 0.9638
5.000 0.6263 0.01165 0.00547 -0.0153 0.3063 0.9666
5.250 0.6338 0.01190 0.00562 -0.0113 0.2789 0.9705
5.500 0.6588 0.01224 0.00585 -0.0113 0.2467 0.9713
5.750 0.6831 0.01267 0.00611 -0.0112 0.2082 0.9723
6.000 0.7073 0.01307 0.00641 -0.0110 0.1765 0.9734
6.250 0.7297 0.01350 0.00671 -0.0105 0.1455 0.9746
6.500 0.7512 0.01391 0.00702 -0.0098 0.1193 0.9761
6.750 0.7712 0.01434 0.00735 -0.0088 0.0945 0.9778
7.000 0.7899 0.01473 0.00767 -0.0075 0.0782 0.9798
7.250 0.8043 0.01509 0.00801 -0.0051 0.0656 0.9826
7.500 0.8281 0.01551 0.00840 -0.0049 0.0522 0.9836
7.750 0.8519 0.01598 0.00886 -0.0048 0.0392 0.9844
8.000 0.8748 0.01645 0.00932 -0.0045 0.0303 0.9854
8.250 0.8974 0.01691 0.00979 -0.0041 0.0250 0.9864
8.500 0.9187 0.01741 0.01032 -0.0035 0.0206 0.9876
8.750 0.9398 0.01788 0.01083 -0.0028 0.0175 0.9890
9.000 0.9582 0.01853 0.01150 -0.0017 0.0139 0.9905
9.250 0.9790 0.01892 0.01196 -0.0010 0.0122 0.9919
9.500 0.9977 0.01949 0.01254 0.0000 0.0099 0.9934
9.750 1.0164 0.02017 0.01332 0.0009 0.0084 0.9946
10.000 1.0373 0.02071 0.01394 0.0014 0.0073 0.9955
10.250 1.0563 0.02138 0.01466 0.0021 0.0057 0.9967
10.500 1.0733 0.02220 0.01556 0.0032 0.0045 0.9978
10.750 1.0911 0.02294 0.01635 0.0040 0.0034 0.9989
11.000 1.1073 0.02383 0.01732 0.0050 0.0029 0.9999
11.250 1.1154 0.02450 0.01806 0.0079 0.0025 1.0000
11.500 1.1196 0.02530 0.01896 0.0114 0.0022 1.0000
11.750 1.1241 0.02609 0.01985 0.0148 0.0021 1.0000
12.000 1.1269 0.02701 0.02088 0.0183 0.0020 1.0000
12.250 1.1303 0.02792 0.02190 0.0215 0.0017 1.0000
12.500 1.1308 0.02905 0.02315 0.0251 0.0017 1.0000
12.750 1.1325 0.03012 0.02433 0.0284 0.0016 1.0000
13.000 1.1317 0.03143 0.02576 0.0317 0.0015 1.0000
13.250 1.1322 0.03269 0.02712 0.0348 0.0015 1.0000
13.500 1.1248 0.03461 0.02921 0.0383 0.0013 1.0000
13.750 1.1233 0.03618 0.03089 0.0410 0.0013 1.0000
14.000 1.1192 0.03806 0.03292 0.0436 0.0013 1.0000
14.250 1.1158 0.04002 0.03502 0.0459 0.0012 1.0000
14.500 1.1063 0.04269 0.03784 0.0480 0.0013 1.0000
14.750 1.1016 0.04512 0.04040 0.0495 0.0013 1.0000
15.000 1.0994 0.04748 0.04290 0.0505 0.0012 1.0000
15.250 1.0880 0.05108 0.04667 0.0512 0.0012 1.0000
15.500 1.0780 0.05481 0.05055 0.0513 0.0012 1.0000
15.750 1.0622 0.05964 0.05555 0.0506 0.0012 1.0000
16.000 1.0492 0.06446 0.06054 0.0493 0.0012 1.0000
16.250 1.0416 0.06883 0.06504 0.0479 0.0011 1.0000
16.500 1.0157 0.07650 0.07290 0.0447 0.0012 1.0000
16.750 1.0053 0.08188 0.07841 0.0423 0.0012 1.0000
17.000 0.9768 0.09093 0.08763 0.0380 0.0012 1.0000
17.250 0.9627 0.09750 0.09433 0.0349 0.0011 1.0000
17.500 0.9372 0.10651 0.10347 0.0307 0.0012 1.0000
17.750 0.9076 0.11660 0.11369 0.0260 0.0012 1.0000
18.000 0.8918 0.12400 0.12118 0.0227 0.0012 1.0000
18.250 0.8610 0.13493 0.13222 0.0177 0.0013 1.0000
18.500 0.8301 0.14651 0.14390 0.0126 0.0013 1.0000
18.750 0.8111 0.15554 0.15299 0.0086 0.0013 1.0000
19.000 0.7911 0.16544 0.16295 0.0043 0.0013 1.0000
19.250 0.7702 0.17634 0.17392 -0.0002 0.0014 1.0000
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Polar data table (+)
Polar graphs
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