MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 200,000 Max Cl/Cd: 62.83 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh104-il-200000.txt Download as CSV file: xf-mh104-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5581 0.08295 0.07966 -0.0248 1.0000 0.0275
-12.250 -0.5889 0.07337 0.06997 -0.0306 1.0000 0.0272
-12.000 -0.7061 0.06886 0.06492 -0.0393 1.0000 0.0280
-11.750 -0.7207 0.06396 0.05993 -0.0418 1.0000 0.0277
-11.500 -0.7384 0.05918 0.05502 -0.0436 1.0000 0.0271
-11.250 -0.7566 0.05508 0.05076 -0.0441 1.0000 0.0267
-11.000 -0.7761 0.05124 0.04671 -0.0432 1.0000 0.0259
-10.750 -0.8216 0.04632 0.04120 -0.0382 1.0000 0.0241
-10.500 -0.8362 0.04515 0.03952 -0.0336 1.0000 0.0232
-10.250 -0.8277 0.04162 0.03584 -0.0324 1.0000 0.0228
-10.000 -0.8208 0.03870 0.03270 -0.0307 1.0000 0.0226
-9.750 -0.8125 0.03606 0.02980 -0.0288 1.0000 0.0225
-9.500 -0.7998 0.03371 0.02724 -0.0272 1.0000 0.0224
-9.250 -0.7851 0.03162 0.02490 -0.0257 1.0000 0.0225
-9.000 -0.7683 0.02977 0.02285 -0.0243 1.0000 0.0227
-8.750 -0.7502 0.02822 0.02110 -0.0230 1.0000 0.0230
-8.500 -0.7300 0.02606 0.01892 -0.0222 1.0000 0.0236
-8.250 -0.7124 0.02457 0.01749 -0.0211 1.0000 0.0244
-8.000 -0.6781 0.02307 0.01600 -0.0232 0.9715 0.0258
-7.750 -0.6367 0.02201 0.01474 -0.0262 0.9344 0.0286
-7.500 -0.6142 0.02048 0.01323 -0.0258 0.8988 0.0315
-7.250 -0.5962 0.01974 0.01233 -0.0238 0.8694 0.0348
-7.000 -0.5843 0.01868 0.01119 -0.0209 0.8457 0.0384
-6.750 -0.5695 0.01780 0.01021 -0.0185 0.8243 0.0465
-6.500 -0.5547 0.01675 0.00913 -0.0161 0.8060 0.0652
-6.250 -0.5453 0.01502 0.00800 -0.0134 0.7896 0.1579
-6.000 -0.5264 0.01447 0.00766 -0.0119 0.7737 0.2297
-5.750 -0.5044 0.01424 0.00745 -0.0107 0.7585 0.2666
-5.500 -0.4813 0.01410 0.00725 -0.0096 0.7439 0.2952
-5.250 -0.4576 0.01398 0.00705 -0.0087 0.7301 0.3183
-5.000 -0.4334 0.01388 0.00684 -0.0078 0.7173 0.3398
-4.750 -0.4096 0.01376 0.00668 -0.0069 0.7054 0.3615
-4.500 -0.3853 0.01368 0.00652 -0.0060 0.6927 0.3846
-4.250 -0.3606 0.01353 0.00635 -0.0053 0.6804 0.4044
-4.000 -0.3355 0.01337 0.00616 -0.0046 0.6692 0.4225
-3.750 -0.3102 0.01323 0.00595 -0.0039 0.6592 0.4406
-3.500 -0.2845 0.01307 0.00577 -0.0034 0.6480 0.4594
-3.250 -0.2589 0.01294 0.00560 -0.0028 0.6382 0.4796
-3.000 -0.2334 0.01277 0.00542 -0.0022 0.6289 0.4998
-2.750 -0.2079 0.01261 0.00530 -0.0016 0.6188 0.5222
-2.500 -0.1826 0.01249 0.00516 -0.0009 0.6107 0.5464
-2.250 -0.1573 0.01234 0.00508 -0.0002 0.6014 0.5730
-2.000 -0.1321 0.01223 0.00500 0.0005 0.5942 0.6015
-1.750 -0.1070 0.01209 0.00497 0.0012 0.5858 0.6331
-1.500 -0.0820 0.01201 0.00493 0.0021 0.5791 0.6673
-1.250 -0.0567 0.01190 0.00494 0.0029 0.5710 0.7039
-1.000 -0.0309 0.01186 0.00494 0.0037 0.5650 0.7412
-0.750 -0.0042 0.01183 0.00505 0.0043 0.5578 0.7790
-0.500 0.0244 0.01187 0.00512 0.0047 0.5518 0.8149
-0.250 0.0558 0.01199 0.00527 0.0045 0.5457 0.8470
0.000 0.0909 0.01215 0.00543 0.0035 0.5389 0.8741
0.250 0.1290 0.01240 0.00557 0.0020 0.5336 0.8955
0.500 0.1691 0.01264 0.00583 -0.0001 0.5270 0.9125
0.750 0.2092 0.01291 0.00600 -0.0022 0.5215 0.9267
1.000 0.2505 0.01320 0.00621 -0.0046 0.5162 0.9388
1.250 0.2987 0.01345 0.00643 -0.0086 0.5098 0.9461
1.500 0.3406 0.01367 0.00656 -0.0113 0.5048 0.9565
1.750 0.3856 0.01390 0.00674 -0.0147 0.4996 0.9653
2.000 0.4307 0.01404 0.00687 -0.0183 0.4937 0.9737
2.250 0.4740 0.01418 0.00692 -0.0215 0.4889 0.9827
2.500 0.5211 0.01427 0.00702 -0.0256 0.4836 0.9900
2.750 0.5675 0.01430 0.00705 -0.0297 0.4779 0.9974
3.000 0.5988 0.01433 0.00702 -0.0308 0.4736 1.0000
3.250 0.6204 0.01447 0.00714 -0.0300 0.4697 1.0000
3.500 0.6418 0.01457 0.00731 -0.0291 0.4647 1.0000
3.750 0.6638 0.01467 0.00740 -0.0283 0.4604 1.0000
4.000 0.6864 0.01483 0.00748 -0.0275 0.4567 1.0000
4.250 0.7079 0.01503 0.00776 -0.0266 0.4520 1.0000
4.500 0.7299 0.01518 0.00797 -0.0258 0.4471 1.0000
4.750 0.7528 0.01533 0.00807 -0.0250 0.4430 1.0000
5.000 0.7754 0.01557 0.00832 -0.0242 0.4388 1.0000
5.250 0.7969 0.01577 0.00862 -0.0232 0.4333 1.0000
5.500 0.8199 0.01592 0.00876 -0.0224 0.4287 1.0000
5.750 0.8434 0.01615 0.00894 -0.0217 0.4245 1.0000
6.000 0.8644 0.01637 0.00931 -0.0206 0.4185 1.0000
6.250 0.8875 0.01650 0.00944 -0.0198 0.4134 1.0000
6.500 0.9108 0.01673 0.00965 -0.0190 0.4085 1.0000
6.750 0.9317 0.01693 0.00998 -0.0180 0.4020 1.0000
7.000 0.9556 0.01704 0.01007 -0.0172 0.3967 1.0000
7.250 0.9769 0.01729 0.01041 -0.0162 0.3906 1.0000
7.500 0.9990 0.01744 0.01061 -0.0152 0.3841 1.0000
7.750 1.0227 0.01760 0.01074 -0.0145 0.3785 1.0000
8.000 1.0426 0.01780 0.01111 -0.0132 0.3710 1.0000
8.250 1.0666 0.01790 0.01114 -0.0125 0.3650 1.0000
8.500 1.0855 0.01813 0.01155 -0.0111 0.3569 1.0000
8.750 1.1085 0.01821 0.01160 -0.0102 0.3501 1.0000
9.000 1.1270 0.01844 0.01200 -0.0088 0.3413 1.0000
9.250 1.1487 0.01855 0.01208 -0.0078 0.3337 1.0000
9.500 1.1663 0.01875 0.01244 -0.0062 0.3239 1.0000
9.750 1.1846 0.01896 0.01272 -0.0048 0.3143 1.0000
10.000 1.2031 0.01915 0.01290 -0.0033 0.3046 1.0000
10.250 1.2182 0.01944 0.01331 -0.0015 0.2929 1.0000
10.500 1.2326 0.01981 0.01375 0.0004 0.2808 1.0000
10.750 1.2451 0.02025 0.01423 0.0025 0.2683 1.0000
11.000 1.2554 0.02079 0.01479 0.0049 0.2556 1.0000
11.250 1.2626 0.02146 0.01545 0.0075 0.2431 1.0000
11.500 1.2650 0.02225 0.01622 0.0108 0.2316 1.0000
11.750 1.2635 0.02315 0.01714 0.0144 0.2207 1.0000
12.000 1.2624 0.02429 0.01831 0.0172 0.2097 1.0000
12.250 1.2606 0.02571 0.01975 0.0194 0.1992 1.0000
12.500 1.2572 0.02746 0.02146 0.0212 0.1894 1.0000
12.750 1.2552 0.02938 0.02344 0.0224 0.1790 1.0000
13.000 1.2524 0.03155 0.02566 0.0232 0.1693 1.0000
13.250 1.2475 0.03402 0.02811 0.0238 0.1608 1.0000
13.500 1.2433 0.03664 0.03077 0.0241 0.1517 1.0000
13.750 1.2385 0.03940 0.03359 0.0242 0.1435 1.0000
14.000 1.2309 0.04249 0.03664 0.0241 0.1360 1.0000
14.250 1.2264 0.04545 0.03972 0.0239 0.1282 1.0000
14.500 1.2172 0.04885 0.04306 0.0236 0.1215 1.0000
14.750 1.2117 0.05211 0.04644 0.0231 0.1140 1.0000
15.000 1.2031 0.05570 0.04998 0.0225 0.1077 1.0000
15.250 1.1973 0.05925 0.05364 0.0216 0.1009 1.0000
15.500 1.1891 0.06302 0.05736 0.0208 0.0950 1.0000
15.750 1.1823 0.06691 0.06136 0.0197 0.0884 1.0000
16.000 1.1740 0.07090 0.06530 0.0187 0.0827 1.0000
16.250 1.1669 0.07502 0.06951 0.0173 0.0767 1.0000
16.500 1.1590 0.07906 0.07349 0.0162 0.0716 1.0000
16.750 1.1525 0.08330 0.07785 0.0147 0.0664 1.0000
17.000 1.1449 0.08741 0.08188 0.0135 0.0618 1.0000
17.250 1.1394 0.09161 0.08621 0.0120 0.0577 1.0000
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Polar data table (+)
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