MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 500,000 Max Cl/Cd: 71.26 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh93-il-500000-n5.txt Download as CSV file: xf-mh93-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9165 0.12443 0.12133 0.0197 1.0000 0.0068
-17.250 -0.9504 0.11195 0.10863 0.0120 1.0000 0.0066
-17.000 -0.9743 0.10224 0.09873 0.0060 1.0000 0.0067
-16.750 -0.9966 0.09332 0.08962 0.0006 1.0000 0.0066
-16.500 -1.0133 0.08586 0.08199 -0.0038 1.0000 0.0066
-16.250 -1.0278 0.07915 0.07512 -0.0077 1.0000 0.0067
-16.000 -1.0405 0.07303 0.06884 -0.0111 1.0000 0.0067
-15.750 -1.0505 0.06764 0.06331 -0.0138 1.0000 0.0067
-15.500 -1.0581 0.06291 0.05843 -0.0160 1.0000 0.0067
-15.250 -1.0639 0.05866 0.05405 -0.0178 1.0000 0.0067
-15.000 -1.0693 0.05469 0.04993 -0.0191 1.0000 0.0068
-14.750 -1.0728 0.05118 0.04630 -0.0201 1.0000 0.0068
-14.500 -1.0756 0.04792 0.04292 -0.0206 1.0000 0.0069
-14.250 -1.0766 0.04506 0.03993 -0.0208 1.0000 0.0069
-14.000 -1.0759 0.04250 0.03726 -0.0207 1.0000 0.0069
-13.750 -1.0749 0.04008 0.03473 -0.0203 1.0000 0.0070
-13.500 -1.0721 0.03795 0.03249 -0.0197 1.0000 0.0070
-13.250 -1.0678 0.03603 0.03047 -0.0189 1.0000 0.0070
-13.000 -1.0631 0.03422 0.02855 -0.0179 1.0000 0.0072
-12.750 -1.0567 0.03261 0.02685 -0.0168 1.0000 0.0073
-12.500 -1.0492 0.03114 0.02528 -0.0156 1.0000 0.0074
-12.250 -1.0409 0.02978 0.02384 -0.0142 1.0000 0.0075
-12.000 -1.0327 0.02844 0.02242 -0.0128 1.0000 0.0075
-11.750 -1.0224 0.02730 0.02120 -0.0113 1.0000 0.0076
-11.500 -1.0116 0.02621 0.02004 -0.0098 1.0000 0.0077
-11.250 -1.0002 0.02519 0.01895 -0.0083 1.0000 0.0078
-11.000 -0.9888 0.02418 0.01789 -0.0066 1.0000 0.0079
-10.750 -0.9781 0.02315 0.01681 -0.0048 1.0000 0.0079
-10.500 -0.9588 0.02222 0.01579 -0.0045 0.9199 0.0081
-10.000 -0.9377 0.02106 0.01435 0.0008 0.8527 0.0084
-9.750 -0.9250 0.02046 0.01364 0.0031 0.8327 0.0085
-9.500 -0.9112 0.01989 0.01297 0.0053 0.8150 0.0086
-9.250 -0.8962 0.01937 0.01236 0.0073 0.7993 0.0088
-9.000 -0.8807 0.01889 0.01178 0.0094 0.7850 0.0090
-8.750 -0.8648 0.01840 0.01119 0.0114 0.7710 0.0093
-8.500 -0.8462 0.01793 0.01063 0.0129 0.7581 0.0096
-8.250 -0.8266 0.01746 0.01009 0.0143 0.7456 0.0098
-8.000 -0.8059 0.01706 0.00958 0.0155 0.7337 0.0100
-7.750 -0.7859 0.01655 0.00903 0.0168 0.7215 0.0105
-7.500 -0.7640 0.01617 0.00859 0.0178 0.7104 0.0110
-7.250 -0.7417 0.01581 0.00815 0.0188 0.6988 0.0117
-7.000 -0.7187 0.01546 0.00774 0.0197 0.6876 0.0125
-6.750 -0.6962 0.01507 0.00731 0.0206 0.6769 0.0133
-6.500 -0.6726 0.01474 0.00693 0.0214 0.6656 0.0145
-6.250 -0.6490 0.01441 0.00654 0.0222 0.6550 0.0160
-6.000 -0.6248 0.01411 0.00619 0.0229 0.6438 0.0178
-5.750 -0.6006 0.01379 0.00586 0.0236 0.6336 0.0205
-5.500 -0.5762 0.01351 0.00552 0.0243 0.6227 0.0247
-5.250 -0.5516 0.01320 0.00522 0.0249 0.6122 0.0305
-5.000 -0.5272 0.01289 0.00492 0.0256 0.6017 0.0408
-4.750 -0.5031 0.01254 0.00462 0.0262 0.5910 0.0577
-4.500 -0.4797 0.01211 0.00431 0.0270 0.5811 0.0862
-4.250 -0.4572 0.01162 0.00399 0.0278 0.5708 0.1287
-4.000 -0.4349 0.01109 0.00369 0.0287 0.5610 0.1839
-3.750 -0.4130 0.01056 0.00340 0.0296 0.5509 0.2473
-3.500 -0.3903 0.01009 0.00318 0.0304 0.5415 0.3085
-3.250 -0.3668 0.00973 0.00298 0.0312 0.5316 0.3612
-3.000 -0.3431 0.00937 0.00281 0.0319 0.5217 0.4121
-2.750 -0.3196 0.00905 0.00266 0.0327 0.5125 0.4660
-2.500 -0.2955 0.00876 0.00254 0.0335 0.5026 0.5164
-2.250 -0.2700 0.00859 0.00244 0.0340 0.4930 0.5500
-2.000 -0.2438 0.00846 0.00235 0.0344 0.4830 0.5763
-1.750 -0.2173 0.00835 0.00228 0.0348 0.4741 0.6024
-1.500 -0.1907 0.00826 0.00223 0.0352 0.4641 0.6280
-1.250 -0.1641 0.00817 0.00220 0.0355 0.4547 0.6547
-1.000 -0.1371 0.00813 0.00218 0.0359 0.4451 0.6787
-0.750 -0.1097 0.00811 0.00218 0.0361 0.4363 0.6991
-0.500 -0.0820 0.00812 0.00218 0.0363 0.4265 0.7161
-0.250 -0.0540 0.00814 0.00219 0.0364 0.4173 0.7312
0.000 -0.0261 0.00819 0.00221 0.0365 0.4083 0.7449
0.250 0.0021 0.00822 0.00224 0.0366 0.3995 0.7563
0.500 0.0302 0.00830 0.00226 0.0366 0.3903 0.7671
0.750 0.0585 0.00835 0.00230 0.0367 0.3821 0.7768
1.250 0.1149 0.00850 0.00240 0.0368 0.3652 0.7940
1.500 0.1430 0.00860 0.00244 0.0368 0.3568 0.8021
1.750 0.1712 0.00867 0.00252 0.0368 0.3496 0.8098
2.000 0.1991 0.00878 0.00258 0.0368 0.3414 0.8184
2.250 0.2271 0.00887 0.00268 0.0369 0.3342 0.8256
2.500 0.2550 0.00898 0.00276 0.0370 0.3269 0.8332
2.750 0.2829 0.00910 0.00284 0.0370 0.3202 0.8389
3.000 0.3109 0.00920 0.00294 0.0370 0.3131 0.8441
3.250 0.3385 0.00934 0.00304 0.0371 0.3063 0.8497
3.500 0.3666 0.00944 0.00313 0.0370 0.3009 0.8549
3.750 0.3943 0.00956 0.00325 0.0371 0.2947 0.8591
4.000 0.4216 0.00971 0.00338 0.0371 0.2884 0.8638
4.250 0.4494 0.00982 0.00349 0.0371 0.2827 0.8687
4.500 0.4768 0.00996 0.00360 0.0371 0.2769 0.8734
4.750 0.5038 0.01012 0.00376 0.0373 0.2719 0.8775
5.000 0.5311 0.01024 0.00390 0.0374 0.2669 0.8822
5.250 0.5579 0.01040 0.00405 0.0375 0.2612 0.8874
5.500 0.5843 0.01058 0.00421 0.0377 0.2558 0.8924
5.750 0.6111 0.01071 0.00438 0.0379 0.2513 0.8968
6.000 0.6374 0.01088 0.00455 0.0381 0.2464 0.9015
6.250 0.6632 0.01109 0.00473 0.0383 0.2411 0.9063
6.500 0.6898 0.01123 0.00491 0.0384 0.2365 0.9101
6.750 0.7158 0.01140 0.00510 0.0387 0.2318 0.9138
7.000 0.7411 0.01162 0.00531 0.0390 0.2270 0.9180
7.250 0.7666 0.01180 0.00551 0.0392 0.2225 0.9225
7.500 0.7921 0.01198 0.00571 0.0395 0.2179 0.9266
7.750 0.8170 0.01221 0.00595 0.0398 0.2131 0.9305
8.000 0.8415 0.01244 0.00619 0.0402 0.2086 0.9349
8.250 0.8660 0.01264 0.00642 0.0406 0.2039 0.9400
8.500 0.8905 0.01290 0.00668 0.0409 0.1985 0.9443
8.750 0.9151 0.01317 0.00697 0.0411 0.1937 0.9488
9.000 0.9396 0.01340 0.00723 0.0414 0.1891 0.9539
9.250 0.9647 0.01370 0.00754 0.0415 0.1845 0.9586
9.500 0.9913 0.01405 0.00790 0.0411 0.1800 0.9631
9.750 1.0176 0.01433 0.00823 0.0409 0.1759 0.9682
10.000 1.0456 0.01468 0.00860 0.0402 0.1712 0.9721
10.250 1.0742 0.01513 0.00905 0.0392 0.1665 0.9758
10.500 1.1031 0.01548 0.00946 0.0383 0.1623 0.9802
10.750 1.1321 0.01591 0.00991 0.0372 0.1577 0.9841
11.000 1.1611 0.01646 0.01047 0.0358 0.1530 0.9877
11.250 1.1901 0.01689 0.01096 0.0346 0.1486 0.9916
11.500 1.2170 0.01745 0.01154 0.0336 0.1439 0.9980
11.750 1.2183 0.01798 0.01207 0.0371 0.1407 1.0000
12.000 1.2238 0.01849 0.01263 0.0399 0.1381 1.0000
12.250 1.2323 0.01915 0.01333 0.0418 0.1343 1.0000
12.500 1.2402 0.02002 0.01421 0.0433 0.1303 1.0000
12.750 1.2485 0.02098 0.01521 0.0446 0.1271 1.0000
13.000 1.2589 0.02192 0.01619 0.0455 0.1233 1.0000
13.250 1.2669 0.02310 0.01740 0.0464 0.1192 1.0000
13.500 1.2727 0.02451 0.01884 0.0472 0.1156 1.0000
13.750 1.2816 0.02578 0.02017 0.0477 0.1121 1.0000
14.000 1.2871 0.02737 0.02179 0.0481 0.1082 1.0000
14.250 1.2891 0.02932 0.02377 0.0484 0.1045 1.0000
14.500 1.2944 0.03106 0.02557 0.0486 0.1009 1.0000
14.750 1.2964 0.03317 0.02773 0.0486 0.0975 1.0000
15.000 1.2942 0.03574 0.03033 0.0485 0.0941 1.0000
15.250 1.2959 0.03800 0.03266 0.0483 0.0911 1.0000
15.500 1.2940 0.04068 0.03540 0.0479 0.0880 1.0000
15.750 1.2879 0.04386 0.03861 0.0473 0.0851 1.0000
16.000 1.2853 0.04678 0.04161 0.0466 0.0829 1.0000
16.250 1.2822 0.04986 0.04477 0.0458 0.0805 1.0000
16.500 1.2757 0.05344 0.04841 0.0447 0.0781 1.0000
16.750 1.2667 0.05740 0.05242 0.0434 0.0760 1.0000
17.000 1.2604 0.06114 0.05624 0.0421 0.0742 1.0000
17.250 1.2553 0.06480 0.05999 0.0408 0.0724 1.0000
17.500 1.2482 0.06878 0.06404 0.0393 0.0706 1.0000
17.750 1.2380 0.07328 0.06861 0.0375 0.0688 1.0000
18.000 1.2270 0.07797 0.07336 0.0355 0.0671 1.0000
18.250 1.2201 0.08215 0.07762 0.0337 0.0653 1.0000
18.500 1.2140 0.08632 0.08186 0.0319 0.0637 1.0000
18.750 1.2054 0.09091 0.08653 0.0298 0.0620 1.0000
19.000 1.1951 0.09582 0.09151 0.0275 0.0605 1.0000
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