MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 50,000 Max Cl/Cd: 23.64 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh102-il-50000-n5.txt Download as CSV file: xf-mh102-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 102 16.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4751 0.10254 0.09504 -0.0453 1.0000 0.0787
-12.750 -0.4588 0.10274 0.09526 -0.0444 1.0000 0.0831
-12.500 -0.4945 0.09174 0.08435 -0.0497 1.0000 0.0863
-12.000 -0.5464 0.07594 0.06863 -0.0572 1.0000 0.0930
-11.750 -0.5875 0.06625 0.05886 -0.0623 1.0000 0.0947
-11.500 -0.6186 0.05895 0.05141 -0.0660 1.0000 0.0969
-11.250 -0.6290 0.05539 0.04792 -0.0671 1.0000 0.1014
-11.000 -0.6457 0.05148 0.04399 -0.0681 1.0000 0.1054
-10.750 -0.6716 0.04738 0.03974 -0.0681 1.0000 0.1088
-10.500 -0.6827 0.04586 0.03839 -0.0658 1.0000 0.1134
-10.250 -0.7026 0.04379 0.03630 -0.0625 1.0000 0.1182
-10.000 -0.7121 0.04245 0.03505 -0.0594 1.0000 0.1248
-9.750 -0.7257 0.04072 0.03321 -0.0560 1.0000 0.1326
-9.500 -0.7284 0.04028 0.03291 -0.0526 1.0000 0.1409
-9.250 -0.7348 0.03940 0.03201 -0.0490 1.0000 0.1496
-9.000 -0.7421 0.03837 0.03081 -0.0455 1.0000 0.1591
-8.750 -0.7399 0.03843 0.03095 -0.0422 1.0000 0.1681
-8.500 -0.7130 0.03811 0.03048 -0.0438 0.9903 0.1844
-8.250 -0.6782 0.03788 0.03007 -0.0465 0.9775 0.2011
-8.000 -0.6427 0.03777 0.02983 -0.0487 0.9649 0.2158
-7.750 -0.6068 0.03746 0.02937 -0.0509 0.9531 0.2293
-7.500 -0.5763 0.03660 0.02825 -0.0526 0.9398 0.2416
-7.250 -0.5442 0.03593 0.02735 -0.0541 0.9272 0.2529
-7.000 -0.5066 0.03538 0.02670 -0.0561 0.9169 0.2624
-6.750 -0.4747 0.03412 0.02503 -0.0582 0.9054 0.2736
-6.500 -0.4403 0.03375 0.02466 -0.0592 0.8936 0.2806
-6.250 -0.4075 0.03258 0.02308 -0.0610 0.8832 0.2911
-6.000 -0.3752 0.03215 0.02266 -0.0616 0.8709 0.2974
-5.750 -0.3465 0.03139 0.02166 -0.0621 0.8585 0.3063
-5.500 -0.3116 0.03070 0.02083 -0.0633 0.8486 0.3138
-5.250 -0.2860 0.03020 0.02018 -0.0630 0.8350 0.3216
-5.000 -0.2578 0.02957 0.01934 -0.0632 0.8233 0.3298
-4.750 -0.2273 0.02911 0.01880 -0.0634 0.8124 0.3374
-4.500 -0.2033 0.02862 0.01806 -0.0630 0.7995 0.3464
-4.250 -0.1725 0.02822 0.01763 -0.0631 0.7895 0.3540
-4.000 -0.1482 0.02784 0.01705 -0.0625 0.7771 0.3634
-3.750 -0.1218 0.02754 0.01673 -0.0621 0.7659 0.3713
-3.500 -0.0938 0.02717 0.01618 -0.0619 0.7557 0.3820
-3.250 -0.0694 0.02698 0.01598 -0.0612 0.7440 0.3907
-3.000 -0.0396 0.02663 0.01544 -0.0613 0.7352 0.4027
-2.750 -0.0164 0.02651 0.01537 -0.0604 0.7232 0.4124
-2.500 0.0130 0.02623 0.01497 -0.0604 0.7148 0.4251
-2.250 0.0366 0.02616 0.01486 -0.0597 0.7034 0.4377
-2.000 0.0651 0.02595 0.01463 -0.0595 0.6952 0.4512
-1.750 0.0885 0.02591 0.01459 -0.0587 0.6845 0.4656
-1.500 0.1163 0.02575 0.01437 -0.0584 0.6766 0.4822
-1.250 0.1390 0.02578 0.01442 -0.0575 0.6664 0.4994
-1.000 0.1678 0.02558 0.01422 -0.0572 0.6596 0.5193
-0.750 0.1880 0.02572 0.01445 -0.0560 0.6491 0.5389
-0.500 0.2156 0.02557 0.01434 -0.0554 0.6423 0.5625
-0.250 0.2357 0.02574 0.01463 -0.0541 0.6328 0.5873
0.000 0.2611 0.02568 0.01463 -0.0532 0.6257 0.6168
0.250 0.2827 0.02579 0.01487 -0.0518 0.6177 0.6488
0.500 0.3048 0.02587 0.01509 -0.0504 0.6098 0.6851
0.750 0.3327 0.02576 0.01505 -0.0494 0.6043 0.7283
1.000 0.3509 0.02615 0.01565 -0.0476 0.5949 0.7726
1.250 0.3839 0.02617 0.01572 -0.0476 0.5885 0.8252
1.500 0.4219 0.02649 0.01611 -0.0492 0.5803 0.8780
1.750 0.4724 0.02672 0.01631 -0.0533 0.5724 0.9276
2.000 0.5291 0.02687 0.01634 -0.0587 0.5652 0.9704
2.250 0.5679 0.02734 0.01676 -0.0618 0.5563 1.0000
2.500 0.5874 0.02749 0.01675 -0.0605 0.5509 1.0000
2.750 0.5959 0.02819 0.01741 -0.0581 0.5431 1.0000
3.000 0.6126 0.02862 0.01775 -0.0565 0.5364 1.0000
3.250 0.6390 0.02872 0.01770 -0.0560 0.5316 1.0000
3.500 0.6446 0.02975 0.01876 -0.0534 0.5227 1.0000
3.750 0.6670 0.03006 0.01900 -0.0524 0.5167 1.0000
4.000 0.6872 0.03055 0.01942 -0.0513 0.5107 1.0000
4.250 0.6980 0.03146 0.02035 -0.0493 0.5025 1.0000
4.500 0.7253 0.03161 0.02042 -0.0489 0.4972 1.0000
4.750 0.7350 0.03266 0.02151 -0.0469 0.4895 1.0000
5.000 0.7528 0.03329 0.02212 -0.0456 0.4826 1.0000
5.250 0.7853 0.03322 0.02197 -0.0457 0.4779 1.0000
5.500 0.7824 0.03493 0.02380 -0.0426 0.4686 1.0000
5.750 0.8079 0.03519 0.02402 -0.0421 0.4628 1.0000
6.000 0.8227 0.03603 0.02487 -0.0406 0.4560 1.0000
6.250 0.8287 0.03732 0.02623 -0.0384 0.4480 1.0000
6.500 0.8630 0.03713 0.02598 -0.0386 0.4433 1.0000
6.750 0.8497 0.03945 0.02842 -0.0349 0.4337 1.0000
7.000 0.8742 0.03975 0.02872 -0.0343 0.4279 1.0000
7.250 0.8886 0.04062 0.02962 -0.0329 0.4215 1.0000
7.500 0.8738 0.04295 0.03201 -0.0292 0.4124 1.0000
7.750 0.9179 0.04217 0.03121 -0.0300 0.4081 1.0000
8.000 0.8635 0.04730 0.03645 -0.0247 0.3962 1.0000
8.250 0.9019 0.04649 0.03564 -0.0245 0.3920 1.0000
8.500 0.8513 0.05277 0.04201 -0.0222 0.3787 1.0000
8.750 0.8860 0.05196 0.04121 -0.0214 0.3749 1.0000
9.000 0.9364 0.04994 0.03920 -0.0211 0.3724 1.0000
9.250 0.8747 0.05800 0.04735 -0.0200 0.3575 1.0000
9.750 0.8657 0.06457 0.05400 -0.0196 0.3403 1.0000
10.750 0.8548 0.07825 0.06787 -0.0203 0.3072 1.0000
11.250 0.8486 0.08569 0.07541 -0.0214 0.2914 1.0000
11.750 0.8420 0.09344 0.08326 -0.0228 0.2761 1.0000
12.250 0.8332 0.10183 0.09176 -0.0248 0.2614 1.0000
12.500 0.8601 0.10120 0.09119 -0.0236 0.2587 1.0000
13.000 0.8475 0.11055 0.10064 -0.0263 0.2441 1.0000
13.500 0.8352 0.12014 0.11035 -0.0295 0.2303 1.0000
13.750 0.8595 0.11991 0.11019 -0.0285 0.2276 1.0000
14.250 0.8442 0.13033 0.12072 -0.0325 0.2141 1.0000
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Polar data table (+)
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