MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 100,000 Max Cl/Cd: 52.26 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh70-il-100000-n5.txt Download as CSV file: xf-mh70-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 70 11.08%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3798 0.09083 0.08603 -0.0287 1.0000 0.0259
-8.750 -0.3799 0.08656 0.08182 -0.0309 1.0000 0.0251
-8.500 -0.3985 0.07694 0.07231 -0.0379 1.0000 0.0226
-8.250 -0.4002 0.07306 0.06851 -0.0401 1.0000 0.0224
-8.000 -0.4059 0.06881 0.06434 -0.0431 1.0000 0.0222
-7.750 -0.4136 0.06331 0.05888 -0.0471 1.0000 0.0219
-7.500 -0.4247 0.05892 0.05448 -0.0483 1.0000 0.0216
-7.250 -0.4269 0.05371 0.04911 -0.0514 0.9891 0.0212
-7.000 -0.4103 0.04641 0.04134 -0.0582 0.9729 0.0208
-6.750 -0.3908 0.04047 0.03481 -0.0624 0.9595 0.0204
-6.500 -0.3683 0.03593 0.02966 -0.0647 0.9478 0.0203
-6.250 -0.3430 0.03228 0.02541 -0.0661 0.9376 0.0205
-6.000 -0.3157 0.02940 0.02199 -0.0670 0.9283 0.0208
-5.750 -0.2897 0.02711 0.01923 -0.0671 0.9180 0.0213
-5.500 -0.2614 0.02514 0.01680 -0.0671 0.9094 0.0223
-5.250 -0.2353 0.02382 0.01534 -0.0670 0.8996 0.0237
-5.000 -0.2091 0.02277 0.01412 -0.0667 0.8902 0.0262
-4.750 -0.1826 0.02156 0.01270 -0.0662 0.8817 0.0281
-4.500 -0.1585 0.02058 0.01168 -0.0655 0.8718 0.0302
-4.250 -0.1328 0.01970 0.01067 -0.0649 0.8637 0.0345
-4.000 -0.1082 0.01899 0.00986 -0.0642 0.8540 0.0405
-3.750 -0.0833 0.01818 0.00903 -0.0635 0.8455 0.0503
-3.500 -0.0586 0.01741 0.00828 -0.0628 0.8367 0.0706
-3.250 -0.0348 0.01649 0.00770 -0.0622 0.8280 0.1285
-3.000 -0.0105 0.01578 0.00735 -0.0616 0.8197 0.2219
-2.750 0.0135 0.01529 0.00715 -0.0609 0.8107 0.3117
-2.500 0.0378 0.01483 0.00697 -0.0600 0.8029 0.4014
-2.250 0.0615 0.01446 0.00684 -0.0590 0.7936 0.4833
-2.000 0.0860 0.01410 0.00667 -0.0578 0.7862 0.5653
-1.750 0.1090 0.01381 0.00662 -0.0563 0.7766 0.6512
-1.500 0.1329 0.01354 0.00652 -0.0544 0.7692 0.7418
-1.250 0.1608 0.01340 0.00649 -0.0533 0.7596 0.8289
-1.000 0.2000 0.01330 0.00631 -0.0546 0.7516 0.9015
-0.750 0.2447 0.01324 0.00610 -0.0575 0.7419 0.9528
-0.500 0.2927 0.01317 0.00585 -0.0613 0.7323 0.9883
-0.250 0.3251 0.01316 0.00565 -0.0622 0.7229 1.0000
0.000 0.3478 0.01324 0.00560 -0.0613 0.7118 1.0000
0.250 0.3711 0.01330 0.00553 -0.0603 0.7018 1.0000
0.500 0.3948 0.01336 0.00545 -0.0593 0.6916 1.0000
0.750 0.4185 0.01346 0.00544 -0.0584 0.6800 1.0000
1.000 0.4426 0.01354 0.00542 -0.0576 0.6689 1.0000
1.250 0.4672 0.01362 0.00537 -0.0567 0.6583 1.0000
1.500 0.4917 0.01372 0.00539 -0.0560 0.6459 1.0000
1.750 0.5163 0.01383 0.00543 -0.0552 0.6332 1.0000
2.000 0.5412 0.01394 0.00546 -0.0545 0.6206 1.0000
2.250 0.5662 0.01405 0.00549 -0.0538 0.6078 1.0000
2.500 0.5912 0.01417 0.00553 -0.0531 0.5945 1.0000
2.750 0.6163 0.01430 0.00558 -0.0524 0.5808 1.0000
3.000 0.6413 0.01445 0.00568 -0.0517 0.5662 1.0000
3.250 0.6662 0.01461 0.00579 -0.0511 0.5512 1.0000
3.500 0.6911 0.01479 0.00591 -0.0504 0.5359 1.0000
3.750 0.7159 0.01499 0.00605 -0.0497 0.5202 1.0000
4.000 0.7406 0.01521 0.00622 -0.0491 0.5042 1.0000
4.250 0.7651 0.01545 0.00642 -0.0484 0.4876 1.0000
4.500 0.7894 0.01572 0.00664 -0.0478 0.4707 1.0000
4.750 0.8136 0.01601 0.00688 -0.0471 0.4538 1.0000
5.000 0.8375 0.01632 0.00717 -0.0464 0.4366 1.0000
5.250 0.8613 0.01665 0.00747 -0.0457 0.4196 1.0000
5.500 0.8847 0.01701 0.00779 -0.0450 0.4025 1.0000
5.750 0.9079 0.01740 0.00816 -0.0443 0.3856 1.0000
6.000 0.9308 0.01781 0.00854 -0.0435 0.3691 1.0000
6.250 0.9534 0.01825 0.00894 -0.0428 0.3528 1.0000
6.500 0.9757 0.01872 0.00940 -0.0420 0.3372 1.0000
6.750 0.9976 0.01921 0.00988 -0.0412 0.3217 1.0000
7.000 1.0193 0.01972 0.01039 -0.0404 0.3069 1.0000
7.250 1.0406 0.02026 0.01095 -0.0395 0.2927 1.0000
7.500 1.0615 0.02083 0.01153 -0.0387 0.2789 1.0000
7.750 1.0821 0.02142 0.01214 -0.0378 0.2660 1.0000
8.000 1.1020 0.02204 0.01280 -0.0368 0.2537 1.0000
8.250 1.1213 0.02270 0.01347 -0.0358 0.2421 1.0000
8.500 1.1399 0.02339 0.01418 -0.0347 0.2310 1.0000
8.750 1.1585 0.02408 0.01494 -0.0337 0.2197 1.0000
9.000 1.1763 0.02482 0.01575 -0.0325 0.2097 1.0000
9.250 1.1924 0.02563 0.01655 -0.0312 0.2005 1.0000
9.500 1.2088 0.02640 0.01744 -0.0300 0.1904 1.0000
9.750 1.2239 0.02726 0.01836 -0.0286 0.1819 1.0000
10.000 1.2369 0.02816 0.01931 -0.0271 0.1736 1.0000
10.250 1.2493 0.02905 0.02033 -0.0254 0.1654 1.0000
10.500 1.2583 0.03007 0.02135 -0.0234 0.1587 1.0000
10.750 1.2690 0.03109 0.02253 -0.0218 0.1508 1.0000
11.000 1.2763 0.03229 0.02374 -0.0201 0.1448 1.0000
11.250 1.2856 0.03350 0.02512 -0.0186 0.1376 1.0000
11.500 1.2912 0.03491 0.02657 -0.0171 0.1317 1.0000
11.750 1.2988 0.03635 0.02818 -0.0159 0.1254 1.0000
12.000 1.3034 0.03798 0.02988 -0.0147 0.1198 1.0000
12.250 1.3083 0.03973 0.03175 -0.0137 0.1143 1.0000
12.500 1.3122 0.04160 0.03376 -0.0128 0.1090 1.0000
12.750 1.3139 0.04370 0.03588 -0.0121 0.1046 1.0000
13.000 1.3167 0.04589 0.03831 -0.0115 0.0994 1.0000
13.250 1.3170 0.04830 0.04081 -0.0112 0.0952 1.0000
13.500 1.3168 0.05090 0.04351 -0.0110 0.0913 1.0000
13.750 1.3159 0.05372 0.04652 -0.0110 0.0869 1.0000
14.000 1.3131 0.05675 0.04964 -0.0112 0.0835 1.0000
14.250 1.3103 0.05993 0.05289 -0.0116 0.0804 1.0000
14.500 1.3061 0.06349 0.05668 -0.0122 0.0769 1.0000
14.750 1.3007 0.06726 0.06059 -0.0132 0.0739 1.0000
15.000 1.2951 0.07112 0.06450 -0.0143 0.0713 1.0000
15.250 1.2884 0.07543 0.06897 -0.0157 0.0688 1.0000
15.500 1.2798 0.08025 0.07401 -0.0175 0.0662 1.0000
15.750 1.2717 0.08511 0.07904 -0.0195 0.0640 1.0000
16.000 1.2640 0.08998 0.08399 -0.0216 0.0619 1.0000
16.250 1.2576 0.09468 0.08873 -0.0236 0.0600 1.0000
16.500 1.2431 0.10129 0.09560 -0.0268 0.0583 1.0000
16.750 1.2286 0.10808 0.10260 -0.0303 0.0568 1.0000
17.000 1.2136 0.11518 0.10987 -0.0341 0.0552 1.0000
17.250 1.2009 0.12192 0.11673 -0.0378 0.0538 1.0000
17.500 1.1976 0.12658 0.12141 -0.0403 0.0519 1.0000
17.750 1.1852 0.13351 0.12844 -0.0443 0.0507 1.0000
18.000 1.1541 0.14538 0.14052 -0.0515 0.0502 1.0000
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Polar data table (+)
Polar graphs
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