MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 200,000 Max Cl/Cd: 65.21 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh102-il-200000-n5.txt Download as CSV file: xf-mh102-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6894 0.09126 0.08588 -0.0475 1.0000 0.0165
-15.250 -0.6913 0.08754 0.08211 -0.0491 1.0000 0.0167
-15.000 -0.6960 0.08341 0.07789 -0.0509 1.0000 0.0172
-14.750 -0.7019 0.07921 0.07367 -0.0529 1.0000 0.0175
-14.500 -0.7069 0.07527 0.06967 -0.0546 1.0000 0.0176
-14.250 -0.7172 0.07076 0.06511 -0.0567 1.0000 0.0179
-14.000 -0.7270 0.06639 0.06069 -0.0587 1.0000 0.0181
-13.750 -0.7391 0.06175 0.05599 -0.0608 1.0000 0.0185
-13.500 -0.7508 0.05723 0.05139 -0.0629 1.0000 0.0187
-13.250 -0.7633 0.05265 0.04673 -0.0650 1.0000 0.0189
-13.000 -0.7754 0.04815 0.04214 -0.0671 1.0000 0.0190
-12.750 -0.7880 0.04363 0.03752 -0.0693 1.0000 0.0194
-12.500 -0.7985 0.03953 0.03331 -0.0712 1.0000 0.0196
-12.250 -0.8081 0.03596 0.02961 -0.0725 1.0000 0.0202
-12.000 -0.8188 0.03303 0.02660 -0.0728 1.0000 0.0207
-11.750 -0.8312 0.03083 0.02431 -0.0711 1.0000 0.0210
-11.500 -0.8437 0.02939 0.02282 -0.0677 1.0000 0.0216
-11.250 -0.8560 0.02836 0.02174 -0.0630 1.0000 0.0220
-11.000 -0.8573 0.02730 0.02062 -0.0598 0.9990 0.0228
-10.750 -0.8305 0.02577 0.01901 -0.0621 0.9880 0.0254
-10.500 -0.8041 0.02446 0.01761 -0.0637 0.9757 0.0280
-10.250 -0.7784 0.02325 0.01632 -0.0649 0.9618 0.0317
-10.000 -0.7504 0.02210 0.01511 -0.0663 0.9482 0.0365
-9.750 -0.7209 0.02098 0.01395 -0.0678 0.9349 0.0439
-9.500 -0.6904 0.01988 0.01282 -0.0694 0.9211 0.0543
-9.250 -0.6616 0.01884 0.01180 -0.0705 0.9054 0.0699
-9.000 -0.6344 0.01793 0.01093 -0.0712 0.8891 0.0900
-8.750 -0.6082 0.01723 0.01028 -0.0714 0.8724 0.1121
-8.500 -0.5820 0.01677 0.00980 -0.0713 0.8560 0.1314
-8.250 -0.5562 0.01645 0.00942 -0.0710 0.8403 0.1470
-8.000 -0.5306 0.01622 0.00909 -0.0706 0.8251 0.1600
-7.750 -0.5056 0.01601 0.00881 -0.0700 0.8106 0.1708
-7.500 -0.4807 0.01583 0.00854 -0.0693 0.7961 0.1796
-7.250 -0.4551 0.01570 0.00826 -0.0688 0.7827 0.1887
-7.000 -0.4302 0.01554 0.00804 -0.0682 0.7700 0.1968
-6.750 -0.4043 0.01545 0.00778 -0.0676 0.7571 0.2055
-6.500 -0.3793 0.01527 0.00759 -0.0670 0.7450 0.2124
-6.250 -0.3533 0.01516 0.00732 -0.0665 0.7336 0.2190
-6.000 -0.3276 0.01498 0.00706 -0.0660 0.7214 0.2243
-5.750 -0.3018 0.01481 0.00684 -0.0654 0.7102 0.2296
-5.500 -0.2755 0.01469 0.00658 -0.0650 0.6991 0.2351
-5.250 -0.2492 0.01454 0.00634 -0.0645 0.6885 0.2401
-5.000 -0.2233 0.01439 0.00613 -0.0640 0.6783 0.2452
-4.750 -0.1969 0.01426 0.00593 -0.0636 0.6672 0.2507
-4.500 -0.1703 0.01416 0.00571 -0.0632 0.6572 0.2562
-4.250 -0.1442 0.01401 0.00555 -0.0627 0.6469 0.2616
-4.000 -0.1176 0.01391 0.00537 -0.0623 0.6378 0.2675
-3.750 -0.0908 0.01383 0.00520 -0.0620 0.6278 0.2735
-3.500 -0.0646 0.01371 0.00507 -0.0615 0.6186 0.2797
-3.250 -0.0380 0.01364 0.00493 -0.0612 0.6089 0.2866
-3.000 -0.0112 0.01357 0.00480 -0.0608 0.6001 0.2931
-2.750 0.0153 0.01348 0.00470 -0.0604 0.5914 0.3004
-2.500 0.0422 0.01345 0.00459 -0.0601 0.5834 0.3087
-2.250 0.0686 0.01336 0.00452 -0.0597 0.5744 0.3166
-2.000 0.0953 0.01334 0.00443 -0.0593 0.5666 0.3253
-1.750 0.1219 0.01327 0.00438 -0.0590 0.5582 0.3342
-1.500 0.1487 0.01326 0.00431 -0.0587 0.5510 0.3448
-1.250 0.1753 0.01321 0.00429 -0.0583 0.5437 0.3554
-1.000 0.2020 0.01320 0.00426 -0.0580 0.5360 0.3667
-0.750 0.2284 0.01318 0.00424 -0.0576 0.5292 0.3788
-0.500 0.2551 0.01315 0.00424 -0.0573 0.5220 0.3920
-0.250 0.2815 0.01315 0.00424 -0.0569 0.5156 0.4066
0.000 0.3082 0.01315 0.00426 -0.0566 0.5091 0.4221
0.250 0.3345 0.01314 0.00429 -0.0562 0.5023 0.4384
0.500 0.3606 0.01315 0.00431 -0.0558 0.4965 0.4568
0.750 0.3869 0.01314 0.00437 -0.0554 0.4903 0.4775
1.000 0.4129 0.01313 0.00444 -0.0549 0.4839 0.5001
1.250 0.4385 0.01314 0.00449 -0.0544 0.4784 0.5248
1.500 0.4643 0.01313 0.00459 -0.0539 0.4725 0.5540
1.750 0.4896 0.01311 0.00470 -0.0533 0.4665 0.5863
2.000 0.5145 0.01312 0.00479 -0.0526 0.4613 0.6219
2.250 0.5393 0.01311 0.00493 -0.0519 0.4559 0.6611
2.500 0.5638 0.01310 0.00507 -0.0510 0.4501 0.7031
2.750 0.5878 0.01312 0.00521 -0.0500 0.4449 0.7485
3.000 0.6122 0.01315 0.00536 -0.0490 0.4399 0.7957
3.250 0.6389 0.01319 0.00554 -0.0484 0.4341 0.8434
3.500 0.6711 0.01329 0.00571 -0.0490 0.4285 0.8903
3.750 0.7099 0.01346 0.00587 -0.0511 0.4230 0.9308
4.000 0.7517 0.01361 0.00606 -0.0539 0.4165 0.9626
4.250 0.7923 0.01379 0.00621 -0.0567 0.4103 0.9874
4.500 0.8260 0.01401 0.00638 -0.0580 0.4049 1.0000
4.750 0.8474 0.01417 0.00656 -0.0569 0.3992 1.0000
5.000 0.8689 0.01436 0.00672 -0.0557 0.3938 1.0000
5.250 0.8907 0.01458 0.00688 -0.0546 0.3890 1.0000
5.500 0.9129 0.01476 0.00710 -0.0536 0.3829 1.0000
5.750 0.9350 0.01497 0.00730 -0.0526 0.3771 1.0000
6.000 0.9569 0.01521 0.00749 -0.0516 0.3720 1.0000
6.250 0.9794 0.01541 0.00775 -0.0507 0.3657 1.0000
6.500 1.0012 0.01565 0.00797 -0.0496 0.3596 1.0000
6.750 1.0228 0.01591 0.00821 -0.0486 0.3539 1.0000
7.000 1.0446 0.01614 0.00849 -0.0476 0.3472 1.0000
7.250 1.0654 0.01641 0.00875 -0.0464 0.3410 1.0000
7.500 1.0864 0.01668 0.00905 -0.0454 0.3346 1.0000
7.750 1.1066 0.01697 0.00935 -0.0441 0.3274 1.0000
8.000 1.1257 0.01729 0.00965 -0.0428 0.3212 1.0000
8.250 1.1453 0.01759 0.01001 -0.0415 0.3139 1.0000
8.500 1.1627 0.01795 0.01035 -0.0399 0.3071 1.0000
8.750 1.1807 0.01829 0.01074 -0.0384 0.2999 1.0000
9.000 1.1953 0.01868 0.01113 -0.0364 0.2928 1.0000
9.250 1.2092 0.01909 0.01155 -0.0343 0.2860 1.0000
9.500 1.2224 0.01954 0.01202 -0.0321 0.2789 1.0000
9.750 1.2342 0.02006 0.01254 -0.0299 0.2725 1.0000
10.000 1.2473 0.02059 0.01312 -0.0280 0.2653 1.0000
10.250 1.2574 0.02125 0.01375 -0.0258 0.2590 1.0000
10.500 1.2698 0.02188 0.01444 -0.0240 0.2522 1.0000
10.750 1.2795 0.02265 0.01522 -0.0221 0.2457 1.0000
11.000 1.2892 0.02347 0.01607 -0.0203 0.2396 1.0000
11.250 1.2989 0.02435 0.01700 -0.0186 0.2331 1.0000
11.750 1.3153 0.02642 0.01914 -0.0154 0.2214 1.0000
12.000 1.3218 0.02765 0.02040 -0.0140 0.2153 1.0000
12.250 1.3279 0.02897 0.02174 -0.0126 0.2100 1.0000
12.500 1.3353 0.03028 0.02312 -0.0115 0.2043 1.0000
12.750 1.3391 0.03188 0.02474 -0.0104 0.1989 1.0000
13.000 1.3447 0.03344 0.02637 -0.0095 0.1938 1.0000
13.250 1.3496 0.03511 0.02811 -0.0087 0.1885 1.0000
13.500 1.3510 0.03711 0.03011 -0.0079 0.1835 1.0000
13.750 1.3552 0.03897 0.03205 -0.0073 0.1786 1.0000
14.000 1.3579 0.04101 0.03417 -0.0068 0.1737 1.0000
14.250 1.3574 0.04337 0.03654 -0.0064 0.1692 1.0000
14.500 1.3599 0.04558 0.03884 -0.0061 0.1647 1.0000
14.750 1.3607 0.04801 0.04135 -0.0060 0.1599 1.0000
15.000 1.3593 0.05070 0.04406 -0.0060 0.1559 1.0000
15.250 1.3600 0.05329 0.04673 -0.0061 0.1517 1.0000
15.500 1.3601 0.05603 0.04956 -0.0063 0.1474 1.0000
15.750 1.3578 0.05906 0.05262 -0.0066 0.1433 1.0000
16.000 1.3568 0.06201 0.05562 -0.0070 0.1398 1.0000
16.250 1.3561 0.06506 0.05878 -0.0076 0.1355 1.0000
16.500 1.3537 0.06833 0.06211 -0.0082 0.1318 1.0000
16.750 1.3503 0.07173 0.06552 -0.0090 0.1285 1.0000
17.000 1.3495 0.07498 0.06890 -0.0098 0.1246 1.0000
17.250 1.3466 0.07853 0.07253 -0.0108 0.1210 1.0000
17.500 1.3426 0.08221 0.07623 -0.0118 0.1177 1.0000
17.750 1.3404 0.08575 0.07987 -0.0129 0.1144 1.0000
18.000 1.3369 0.08958 0.08380 -0.0141 0.1109 1.0000
18.250 1.3323 0.09355 0.08782 -0.0155 0.1076 1.0000
18.500 1.3291 0.09731 0.09161 -0.0169 0.1047 1.0000
18.750 1.3249 0.10140 0.09583 -0.0184 0.1014 1.0000
19.000 1.3203 0.10554 0.10005 -0.0201 0.0982 1.0000
19.250 1.3159 0.10962 0.10414 -0.0218 0.0954 1.0000
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