MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 100,000 Max Cl/Cd: 37.8 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh102-il-100000.txt Download as CSV file: xf-mh102-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5865 0.09527 0.08977 -0.0542 1.0000 0.0567
-14.000 -0.6242 0.08492 0.07932 -0.0606 1.0000 0.0558
-13.750 -0.6669 0.07477 0.06898 -0.0675 1.0000 0.0547
-13.500 -0.7020 0.06671 0.06069 -0.0731 1.0000 0.0540
-13.250 -0.7287 0.06047 0.05423 -0.0770 1.0000 0.0537
-13.000 -0.7470 0.05574 0.04930 -0.0794 1.0000 0.0536
-12.750 -0.7607 0.05188 0.04525 -0.0805 1.0000 0.0542
-12.500 -0.7715 0.04863 0.04182 -0.0808 1.0000 0.0548
-12.250 -0.7830 0.04572 0.03871 -0.0802 1.0000 0.0557
-12.000 -0.7938 0.04330 0.03607 -0.0786 1.0000 0.0564
-11.750 -0.7839 0.04148 0.03437 -0.0772 1.0000 0.0587
-11.500 -0.7872 0.03987 0.03274 -0.0747 1.0000 0.0608
-11.250 -0.7964 0.03834 0.03107 -0.0711 1.0000 0.0626
-11.000 -0.7947 0.03678 0.02958 -0.0684 1.0000 0.0653
-10.750 -0.7959 0.03543 0.02826 -0.0653 1.0000 0.0689
-10.500 -0.7980 0.03397 0.02675 -0.0618 1.0000 0.0722
-10.250 -0.8005 0.03283 0.02574 -0.0582 1.0000 0.0765
-10.000 -0.8062 0.03167 0.02455 -0.0541 1.0000 0.0809
-9.750 -0.8125 0.03075 0.02370 -0.0499 1.0000 0.0863
-9.500 -0.8183 0.02978 0.02279 -0.0458 1.0000 0.0924
-9.250 -0.8221 0.02882 0.02186 -0.0421 1.0000 0.1010
-9.000 -0.8232 0.02800 0.02112 -0.0388 1.0000 0.1126
-8.750 -0.8167 0.02730 0.02043 -0.0369 0.9987 0.1321
-8.500 -0.7719 0.02753 0.02084 -0.0414 0.9871 0.1661
-8.250 -0.7279 0.02813 0.02134 -0.0452 0.9759 0.1921
-8.000 -0.6798 0.02898 0.02229 -0.0490 0.9661 0.2117
-7.750 -0.6372 0.02937 0.02265 -0.0519 0.9552 0.2280
-7.500 -0.5975 0.02947 0.02268 -0.0542 0.9439 0.2427
-7.250 -0.5505 0.02940 0.02249 -0.0579 0.9361 0.2580
-7.000 -0.5106 0.02940 0.02248 -0.0599 0.9249 0.2705
-6.750 -0.4636 0.02907 0.02217 -0.0632 0.9173 0.2817
-6.500 -0.4264 0.02817 0.02097 -0.0653 0.9071 0.2928
-6.250 -0.3852 0.02776 0.02060 -0.0674 0.8976 0.3018
-6.000 -0.3483 0.02677 0.01934 -0.0693 0.8879 0.3113
-5.750 -0.3151 0.02633 0.01891 -0.0699 0.8760 0.3189
-5.500 -0.2783 0.02542 0.01766 -0.0715 0.8673 0.3283
-5.250 -0.2509 0.02500 0.01730 -0.0711 0.8535 0.3348
-5.000 -0.2224 0.02448 0.01657 -0.0711 0.8418 0.3432
-4.750 -0.1917 0.02386 0.01585 -0.0712 0.8310 0.3505
-4.500 -0.1671 0.02356 0.01548 -0.0704 0.8176 0.3583
-4.250 -0.1394 0.02305 0.01478 -0.0701 0.8070 0.3666
-4.000 -0.1128 0.02272 0.01444 -0.0695 0.7948 0.3742
-3.750 -0.0889 0.02245 0.01396 -0.0687 0.7825 0.3837
-3.500 -0.0593 0.02204 0.01356 -0.0684 0.7731 0.3919
-3.250 -0.0365 0.02188 0.01324 -0.0675 0.7603 0.4019
-3.000 -0.0088 0.02157 0.01297 -0.0670 0.7507 0.4111
-2.750 0.0159 0.02137 0.01264 -0.0663 0.7392 0.4225
-2.500 0.0417 0.02117 0.01249 -0.0657 0.7289 0.4329
-2.250 0.0682 0.02095 0.01221 -0.0651 0.7192 0.4453
-2.000 0.0928 0.02090 0.01209 -0.0644 0.7092 0.4595
-1.750 0.1197 0.02067 0.01191 -0.0639 0.7001 0.4731
-1.500 0.1441 0.02060 0.01189 -0.0631 0.6902 0.4881
-1.250 0.1706 0.02045 0.01174 -0.0625 0.6817 0.5057
-1.000 0.1951 0.02044 0.01179 -0.0618 0.6730 0.5245
-0.750 0.2204 0.02035 0.01175 -0.0610 0.6643 0.5455
-0.500 0.2461 0.02029 0.01175 -0.0603 0.6568 0.5697
-0.250 0.2692 0.02032 0.01189 -0.0593 0.6477 0.5964
0.000 0.2967 0.02017 0.01181 -0.0586 0.6418 0.6270
0.250 0.3164 0.02034 0.01220 -0.0571 0.6323 0.6599
0.500 0.3419 0.02024 0.01222 -0.0559 0.6256 0.7005
0.750 0.3639 0.02037 0.01251 -0.0543 0.6184 0.7464
1.000 0.3856 0.02047 0.01281 -0.0524 0.6106 0.7963
1.250 0.4162 0.02044 0.01281 -0.0514 0.6051 0.8515
1.500 0.4502 0.02086 0.01336 -0.0522 0.5959 0.9035
1.750 0.5103 0.02097 0.01335 -0.0574 0.5885 0.9430
2.000 0.5755 0.02135 0.01368 -0.0646 0.5790 0.9714
2.250 0.6471 0.02135 0.01353 -0.0730 0.5707 0.9951
2.500 0.6684 0.02163 0.01375 -0.0729 0.5640 1.0000
2.750 0.6768 0.02203 0.01413 -0.0703 0.5569 1.0000
3.000 0.6966 0.02216 0.01412 -0.0689 0.5515 1.0000
3.250 0.7089 0.02272 0.01469 -0.0667 0.5447 1.0000
3.500 0.7253 0.02313 0.01506 -0.0650 0.5377 1.0000
3.750 0.7517 0.02323 0.01501 -0.0644 0.5325 1.0000
4.000 0.7629 0.02399 0.01585 -0.0621 0.5248 1.0000
4.250 0.7843 0.02430 0.01611 -0.0610 0.5182 1.0000
4.500 0.8150 0.02436 0.01600 -0.0610 0.5133 1.0000
4.750 0.8228 0.02530 0.01710 -0.0583 0.5046 1.0000
5.000 0.8495 0.02544 0.01715 -0.0578 0.4985 1.0000
5.250 0.8699 0.02598 0.01769 -0.0567 0.4919 1.0000
5.500 0.8871 0.02655 0.01832 -0.0551 0.4840 1.0000
5.750 0.9197 0.02649 0.01812 -0.0554 0.4786 1.0000
6.000 0.9296 0.02750 0.01926 -0.0530 0.4702 1.0000
6.250 0.9561 0.02764 0.01937 -0.0526 0.4635 1.0000
6.500 0.9805 0.02802 0.01972 -0.0519 0.4571 1.0000
6.750 0.9943 0.02878 0.02058 -0.0500 0.4487 1.0000
7.000 1.0299 0.02856 0.02022 -0.0507 0.4430 1.0000
7.250 1.0363 0.02972 0.02155 -0.0480 0.4343 1.0000
7.500 1.0654 0.02973 0.02151 -0.0478 0.4276 1.0000
7.750 1.0836 0.03038 0.02221 -0.0465 0.4203 1.0000
8.000 1.1013 0.03091 0.02280 -0.0451 0.4124 1.0000
8.250 1.1409 0.03060 0.02232 -0.0462 0.4066 1.0000
8.500 1.1384 0.03200 0.02398 -0.0425 0.3975 1.0000
8.750 1.1757 0.03166 0.02351 -0.0433 0.3911 1.0000
9.000 1.1782 0.03293 0.02497 -0.0402 0.3829 1.0000
9.250 1.2065 0.03291 0.02491 -0.0400 0.3757 1.0000
9.500 1.2226 0.03360 0.02565 -0.0385 0.3685 1.0000
9.750 1.2350 0.03426 0.02640 -0.0365 0.3607 1.0000
10.000 1.2705 0.03407 0.02610 -0.0371 0.3539 1.0000
10.250 1.2628 0.03556 0.02782 -0.0330 0.3460 1.0000
10.500 1.3128 0.03473 0.02677 -0.0352 0.3391 1.0000
10.750 1.2918 0.03673 0.02907 -0.0296 0.3318 1.0000
11.000 1.3244 0.03649 0.02876 -0.0299 0.3246 1.0000
11.250 1.3247 0.03769 0.03007 -0.0267 0.3180 1.0000
11.500 1.3242 0.03867 0.03113 -0.0234 0.3112 1.0000
11.750 1.3619 0.03845 0.03082 -0.0243 0.3040 1.0000
12.000 1.3306 0.04087 0.03347 -0.0184 0.2984 1.0000
12.250 1.4010 0.03924 0.03155 -0.0222 0.2897 1.0000
12.500 1.3534 0.04249 0.03514 -0.0154 0.2854 1.0000
12.750 1.3446 0.04441 0.03716 -0.0128 0.2794 1.0000
13.000 1.3871 0.04370 0.03634 -0.0134 0.2719 1.0000
13.250 1.3374 0.04835 0.04126 -0.0094 0.2675 1.0000
13.500 1.4268 0.04481 0.03739 -0.0120 0.2580 1.0000
13.750 1.3653 0.05020 0.04314 -0.0077 0.2549 1.0000
14.000 0.8085 0.13491 0.12820 -0.0367 0.2302 1.0000
14.250 0.8758 0.12689 0.12025 -0.0314 0.2273 1.0000
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Polar data table (+)
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