MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.42 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh18-il-1000000.txt Download as CSV file: xf-mh18-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3927 0.13100 0.12914 0.0077 0.8123 0.0065
-11.500 -0.3886 0.12695 0.12506 0.0056 0.8088 0.0065
-7.000 -0.5450 0.02488 0.02087 -0.0292 0.7498 0.0039
-6.750 -0.5250 0.02332 0.01910 -0.0282 0.7451 0.0038
-6.500 -0.5097 0.02044 0.01584 -0.0263 0.7407 0.0036
-6.000 -0.4741 0.01516 0.00970 -0.0228 0.7324 0.0040
-5.750 -0.4506 0.01414 0.00855 -0.0221 0.7284 0.0045
-5.500 -0.4253 0.01355 0.00785 -0.0217 0.7247 0.0048
-5.250 -0.3997 0.01292 0.00712 -0.0212 0.7209 0.0051
-5.000 -0.3742 0.01227 0.00637 -0.0207 0.7170 0.0053
-4.750 -0.3490 0.01163 0.00562 -0.0202 0.7134 0.0055
-4.500 -0.3233 0.01112 0.00500 -0.0197 0.7101 0.0057
-4.250 -0.2971 0.01066 0.00448 -0.0193 0.7067 0.0060
-4.000 -0.2700 0.01039 0.00417 -0.0191 0.7032 0.0064
-3.750 -0.2445 0.00982 0.00347 -0.0185 0.6999 0.0069
-3.500 -0.2183 0.00941 0.00292 -0.0181 0.6967 0.0079
-3.250 -0.1922 0.00891 0.00245 -0.0176 0.6936 0.0221
-3.000 -0.1658 0.00856 0.00223 -0.0173 0.6901 0.0515
-2.750 -0.1389 0.00832 0.00207 -0.0172 0.6866 0.0756
-2.500 -0.1127 0.00805 0.00192 -0.0170 0.6829 0.1170
-2.250 -0.0864 0.00773 0.00180 -0.0168 0.6794 0.1673
-2.000 -0.0597 0.00748 0.00167 -0.0167 0.6758 0.2146
-1.750 -0.0332 0.00724 0.00157 -0.0165 0.6723 0.2641
-1.500 -0.0079 0.00691 0.00148 -0.0161 0.6687 0.3457
-1.250 0.0166 0.00648 0.00140 -0.0157 0.6654 0.4537
-1.000 0.0397 0.00601 0.00132 -0.0148 0.6618 0.5771
-0.750 0.0606 0.00554 0.00126 -0.0134 0.6584 0.7050
-0.500 0.0803 0.00512 0.00124 -0.0115 0.6550 0.8281
-0.250 0.1534 0.00499 0.00140 -0.0212 0.6515 0.9378
0.250 0.2211 0.00526 0.00159 -0.0235 0.6441 0.9667
0.500 0.2586 0.00539 0.00165 -0.0256 0.6403 0.9724
0.750 0.2964 0.00547 0.00172 -0.0278 0.6362 0.9776
1.000 0.3300 0.00557 0.00179 -0.0290 0.6319 0.9826
1.250 0.3712 0.00564 0.00180 -0.0320 0.6276 0.9848
1.500 0.4119 0.00567 0.00183 -0.0349 0.6231 0.9878
1.750 0.4514 0.00572 0.00186 -0.0375 0.6179 0.9915
2.000 0.4956 0.00575 0.00186 -0.0411 0.6130 0.9952
2.250 0.5411 0.00567 0.00179 -0.0451 0.6067 0.9988
2.500 0.5747 0.00568 0.00176 -0.0465 0.6006 1.0000
2.750 0.6009 0.00567 0.00177 -0.0463 0.5940 1.0000
3.250 0.6531 0.00572 0.00181 -0.0458 0.5779 1.0000
3.500 0.6793 0.00576 0.00184 -0.0456 0.5681 1.0000
3.750 0.7055 0.00581 0.00188 -0.0454 0.5562 1.0000
4.000 0.7317 0.00588 0.00192 -0.0452 0.5420 1.0000
4.250 0.7578 0.00599 0.00200 -0.0451 0.5232 1.0000
4.500 0.7836 0.00615 0.00209 -0.0449 0.5001 1.0000
4.750 0.8092 0.00636 0.00221 -0.0447 0.4744 1.0000
5.000 0.8346 0.00662 0.00238 -0.0445 0.4452 1.0000
5.250 0.8597 0.00690 0.00257 -0.0443 0.4192 1.0000
5.500 0.8844 0.00722 0.00279 -0.0440 0.3889 1.0000
5.750 0.9084 0.00763 0.00304 -0.0437 0.3514 1.0000
6.000 0.9315 0.00811 0.00334 -0.0432 0.3091 1.0000
6.250 0.9536 0.00867 0.00368 -0.0427 0.2632 1.0000
6.500 0.9745 0.00930 0.00408 -0.0419 0.2171 1.0000
6.750 0.9938 0.01003 0.00455 -0.0410 0.1675 1.0000
7.000 1.0119 0.01080 0.00510 -0.0398 0.1236 1.0000
7.250 1.0283 0.01164 0.00569 -0.0383 0.0800 1.0000
7.500 1.0439 0.01246 0.00631 -0.0367 0.0467 1.0000
7.750 1.0611 0.01309 0.00684 -0.0353 0.0297 1.0000
8.000 1.0776 0.01370 0.00739 -0.0337 0.0171 1.0000
8.250 1.0899 0.01455 0.00814 -0.0314 0.0049 1.0000
8.500 1.1039 0.01522 0.00884 -0.0293 0.0027 1.0000
8.750 1.1131 0.01614 0.00987 -0.0264 0.0019 1.0000
9.000 1.1231 0.01690 0.01071 -0.0237 0.0018 1.0000
9.250 1.1297 0.01753 0.01143 -0.0204 0.0017 1.0000
9.500 1.1304 0.01825 0.01223 -0.0163 0.0017 1.0000
9.750 1.1348 0.01908 0.01314 -0.0131 0.0016 1.0000
10.000 1.1386 0.02014 0.01429 -0.0102 0.0016 1.0000
10.250 1.1451 0.02116 0.01539 -0.0078 0.0016 1.0000
10.500 1.1459 0.02267 0.01701 -0.0050 0.0015 1.0000
10.750 1.1503 0.02403 0.01846 -0.0029 0.0015 1.0000
11.000 1.1537 0.02555 0.02008 -0.0009 0.0015 1.0000
11.250 1.1579 0.02708 0.02171 0.0009 0.0016 1.0000
11.500 1.1588 0.02897 0.02370 0.0028 0.0015 1.0000
11.750 1.1587 0.03102 0.02587 0.0046 0.0016 1.0000
12.000 1.1614 0.03290 0.02785 0.0061 0.0016 1.0000
12.250 1.1599 0.03525 0.03033 0.0077 0.0016 1.0000
12.500 1.1587 0.03765 0.03286 0.0092 0.0016 1.0000
12.750 1.1587 0.03999 0.03533 0.0104 0.0016 1.0000
13.000 1.1542 0.04290 0.03841 0.0117 0.0016 1.0000
13.250 1.1477 0.04617 0.04186 0.0130 0.0017 1.0000
13.500 1.1419 0.04945 0.04529 0.0139 0.0017 1.0000
13.750 1.1331 0.05325 0.04927 0.0146 0.0017 1.0000
14.000 1.1271 0.05683 0.05296 0.0151 0.0019 1.0000
14.250 1.1249 0.05999 0.05623 0.0148 0.0019 1.0000
14.500 1.1222 0.06332 0.05967 0.0142 0.0019 1.0000
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Polar data table (+)
Polar graphs
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