MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 100,000 Max Cl/Cd: 54.62 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh120-il-100000-n5.txt Download as CSV file: xf-mh120-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4248 0.08661 0.08179 -0.0478 1.0000 0.0282
-9.250 -0.4319 0.08150 0.07675 -0.0499 1.0000 0.0280
-9.000 -0.4405 0.07660 0.07191 -0.0522 1.0000 0.0278
-8.750 -0.4476 0.07344 0.06883 -0.0525 1.0000 0.0269
-8.500 -0.4694 0.06922 0.06463 -0.0532 1.0000 0.0268
-8.250 -0.4942 0.06609 0.06150 -0.0506 1.0000 0.0270
-8.000 -0.5132 0.06305 0.05842 -0.0479 1.0000 0.0270
-7.750 -0.5306 0.06024 0.05553 -0.0446 1.0000 0.0271
-7.500 -0.5458 0.05752 0.05266 -0.0410 1.0000 0.0274
-7.250 -0.5466 0.05367 0.04857 -0.0402 0.9967 0.0274
-7.000 -0.5312 0.04890 0.04332 -0.0423 0.9879 0.0277
-6.750 -0.5148 0.04458 0.03856 -0.0433 0.9794 0.0276
-6.500 -0.4939 0.04060 0.03407 -0.0444 0.9723 0.0274
-6.250 -0.4748 0.03727 0.03027 -0.0442 0.9635 0.0273
-6.000 -0.4504 0.03418 0.02666 -0.0445 0.9568 0.0274
-5.750 -0.4258 0.03174 0.02377 -0.0444 0.9491 0.0275
-5.500 -0.3960 0.02961 0.02114 -0.0449 0.9433 0.0281
-5.250 -0.3709 0.02736 0.01867 -0.0450 0.9357 0.0300
-5.000 -0.3367 0.02571 0.01682 -0.0465 0.9315 0.0316
-4.750 -0.3091 0.02427 0.01514 -0.0463 0.9234 0.0319
-4.500 -0.2745 0.02284 0.01357 -0.0476 0.9186 0.0326
-4.250 -0.2461 0.02173 0.01236 -0.0476 0.9108 0.0334
-4.000 -0.2136 0.02070 0.01122 -0.0485 0.9050 0.0345
-3.750 -0.1864 0.01992 0.01032 -0.0483 0.8967 0.0357
-3.500 -0.1545 0.01917 0.00938 -0.0490 0.8904 0.0378
-3.250 -0.1288 0.01853 0.00861 -0.0485 0.8813 0.0412
-3.000 -0.0951 0.01792 0.00789 -0.0497 0.8753 0.0494
-2.750 -0.0710 0.01725 0.00729 -0.0488 0.8654 0.0697
-2.500 -0.0498 0.01560 0.00683 -0.0482 0.8575 0.3223
-2.250 -0.0283 0.01452 0.00678 -0.0469 0.8490 0.5643
-2.000 0.0025 0.01410 0.00660 -0.0470 0.8408 0.6647
-1.750 0.0919 0.01369 0.00671 -0.0582 0.8396 0.8648
-1.500 0.1536 0.01367 0.00646 -0.0648 0.8340 0.8995
-1.250 0.2034 0.01372 0.00633 -0.0691 0.8251 0.9232
-1.000 0.2494 0.01375 0.00618 -0.0727 0.8170 0.9442
-0.750 0.2942 0.01380 0.00607 -0.0762 0.8073 0.9611
-0.500 0.3393 0.01382 0.00596 -0.0799 0.7974 0.9765
-0.250 0.3855 0.01381 0.00580 -0.0839 0.7882 0.9896
0.000 0.4309 0.01380 0.00567 -0.0879 0.7782 1.0000
0.250 0.4521 0.01381 0.00559 -0.0868 0.7668 1.0000
0.500 0.4741 0.01384 0.00554 -0.0858 0.7560 1.0000
0.750 0.4972 0.01387 0.00548 -0.0850 0.7460 1.0000
1.000 0.5197 0.01393 0.00546 -0.0840 0.7356 1.0000
1.250 0.5408 0.01402 0.00550 -0.0828 0.7249 1.0000
1.500 0.5631 0.01411 0.00556 -0.0818 0.7148 1.0000
1.750 0.5868 0.01420 0.00558 -0.0809 0.7055 1.0000
2.000 0.6079 0.01433 0.00570 -0.0797 0.6948 1.0000
2.250 0.6295 0.01447 0.00582 -0.0784 0.6843 1.0000
2.500 0.6519 0.01461 0.00595 -0.0774 0.6741 1.0000
2.750 0.6750 0.01473 0.00604 -0.0764 0.6639 1.0000
3.000 0.6957 0.01489 0.00621 -0.0749 0.6519 1.0000
3.250 0.7167 0.01505 0.00637 -0.0735 0.6399 1.0000
3.500 0.7380 0.01521 0.00658 -0.0722 0.6280 1.0000
3.750 0.7595 0.01537 0.00675 -0.0709 0.6165 1.0000
4.000 0.7813 0.01554 0.00694 -0.0696 0.6050 1.0000
4.250 0.8032 0.01572 0.00713 -0.0684 0.5935 1.0000
4.500 0.8235 0.01591 0.00738 -0.0669 0.5805 1.0000
4.750 0.8439 0.01611 0.00767 -0.0653 0.5669 1.0000
5.000 0.8641 0.01632 0.00793 -0.0637 0.5531 1.0000
5.250 0.8840 0.01653 0.00819 -0.0621 0.5383 1.0000
5.500 0.9036 0.01675 0.00845 -0.0604 0.5228 1.0000
5.750 0.9221 0.01700 0.00878 -0.0585 0.5057 1.0000
6.000 0.9402 0.01726 0.00910 -0.0566 0.4873 1.0000
6.250 0.9580 0.01754 0.00947 -0.0546 0.4683 1.0000
6.500 0.9746 0.01786 0.00985 -0.0524 0.4464 1.0000
6.750 0.9906 0.01821 0.01022 -0.0501 0.4239 1.0000
7.000 1.0056 0.01862 0.01066 -0.0476 0.3989 1.0000
7.250 1.0194 0.01909 0.01113 -0.0450 0.3720 1.0000
7.500 1.0303 0.01966 0.01164 -0.0420 0.3394 1.0000
7.750 1.0366 0.02044 0.01221 -0.0383 0.2979 1.0000
8.000 1.0416 0.02134 0.01297 -0.0345 0.2585 1.0000
8.250 1.0459 0.02235 0.01379 -0.0308 0.2202 1.0000
8.500 1.0444 0.02355 0.01468 -0.0264 0.1754 1.0000
8.750 1.0440 0.02478 0.01564 -0.0223 0.1353 1.0000
9.000 1.0443 0.02612 0.01673 -0.0186 0.0976 1.0000
9.250 1.0462 0.02750 0.01795 -0.0153 0.0680 1.0000
9.500 1.0447 0.02923 0.01949 -0.0118 0.0405 1.0000
9.750 1.0445 0.03100 0.02120 -0.0087 0.0293 1.0000
10.000 1.0447 0.03285 0.02311 -0.0058 0.0245 1.0000
10.250 1.0480 0.03450 0.02492 -0.0035 0.0223 1.0000
10.500 1.0495 0.03638 0.02693 -0.0014 0.0202 1.0000
10.750 1.0482 0.03857 0.02922 0.0005 0.0188 1.0000
11.000 1.0500 0.04059 0.03145 0.0021 0.0174 1.0000
11.250 1.0505 0.04282 0.03385 0.0035 0.0165 1.0000
11.500 1.0515 0.04509 0.03628 0.0047 0.0157 1.0000
11.750 1.0517 0.04753 0.03886 0.0056 0.0151 1.0000
12.000 1.0496 0.05033 0.04179 0.0065 0.0144 1.0000
12.250 1.0492 0.05301 0.04461 0.0071 0.0142 1.0000
12.500 1.0506 0.05557 0.04733 0.0077 0.0142 1.0000
12.750 1.0473 0.05876 0.05062 0.0082 0.0136 1.0000
13.000 1.0460 0.06182 0.05379 0.0086 0.0133 1.0000
13.250 1.0465 0.06473 0.05685 0.0089 0.0132 1.0000
13.500 1.0463 0.06794 0.06019 0.0094 0.0130 1.0000
13.750 1.0465 0.07109 0.06351 0.0094 0.0130 1.0000
14.000 1.0443 0.07474 0.06739 0.0093 0.0129 1.0000
14.250 1.0403 0.07869 0.07155 0.0088 0.0128 1.0000
14.500 1.0339 0.08310 0.07617 0.0078 0.0127 1.0000
14.750 1.0251 0.08805 0.08135 0.0065 0.0127 1.0000
15.000 1.0161 0.09310 0.08661 0.0046 0.0127 1.0000
15.250 1.0035 0.09907 0.09279 0.0022 0.0127 1.0000
15.500 0.9919 0.10502 0.09893 -0.0006 0.0127 1.0000
15.750 0.9764 0.11212 0.10622 -0.0042 0.0127 1.0000
16.000 0.9627 0.11919 0.11346 -0.0080 0.0127 1.0000
16.250 0.9505 0.12619 0.12059 -0.0118 0.0129 1.0000
16.500 0.9352 0.13441 0.12894 -0.0166 0.0129 1.0000
16.750 0.9185 0.14355 0.13821 -0.0218 0.0130 1.0000
17.000 0.9052 0.15236 0.14714 -0.0269 0.0132 1.0000
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Polar data table (+)
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