MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 200,000 Max Cl/Cd: 53.24 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh93-il-200000-n5.txt Download as CSV file: xf-mh93-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7798 0.11606 0.11199 0.0117 1.0000 0.0125
-15.250 -0.8019 0.10595 0.10176 0.0051 1.0000 0.0123
-15.000 -0.8306 0.09512 0.09072 -0.0021 1.0000 0.0122
-14.750 -0.8544 0.08618 0.08157 -0.0080 1.0000 0.0122
-14.500 -0.8764 0.07837 0.07354 -0.0128 1.0000 0.0122
-14.250 -0.8949 0.07181 0.06675 -0.0166 1.0000 0.0121
-14.000 -0.9092 0.06641 0.06114 -0.0192 1.0000 0.0121
-13.750 -0.9218 0.06157 0.05610 -0.0210 1.0000 0.0121
-13.500 -0.9329 0.05724 0.05155 -0.0222 1.0000 0.0122
-13.250 -0.9400 0.05362 0.04772 -0.0227 1.0000 0.0122
-13.000 -0.9469 0.05016 0.04402 -0.0227 1.0000 0.0123
-12.750 -0.9522 0.04700 0.04059 -0.0222 1.0000 0.0124
-12.500 -0.9523 0.04444 0.03781 -0.0214 1.0000 0.0125
-12.250 -0.9486 0.04226 0.03552 -0.0206 1.0000 0.0126
-12.000 -0.9429 0.04028 0.03343 -0.0196 1.0000 0.0127
-11.750 -0.9359 0.03853 0.03160 -0.0186 1.0000 0.0128
-11.500 -0.9274 0.03693 0.02990 -0.0175 1.0000 0.0130
-11.250 -0.9181 0.03547 0.02837 -0.0163 1.0000 0.0132
-11.000 -0.9076 0.03414 0.02696 -0.0151 1.0000 0.0136
-10.750 -0.8957 0.03277 0.02549 -0.0139 1.0000 0.0138
-10.500 -0.8829 0.03152 0.02413 -0.0126 1.0000 0.0143
-10.250 -0.8687 0.03030 0.02279 -0.0114 1.0000 0.0147
-10.000 -0.8536 0.02913 0.02149 -0.0102 1.0000 0.0152
-9.750 -0.8390 0.02794 0.02028 -0.0090 1.0000 0.0155
-9.500 -0.8239 0.02690 0.01924 -0.0078 1.0000 0.0158
-9.250 -0.8083 0.02591 0.01824 -0.0066 1.0000 0.0162
-9.000 -0.7894 0.02495 0.01724 -0.0060 0.9536 0.0166
-8.750 -0.7687 0.02404 0.01619 -0.0054 0.9070 0.0173
-8.250 -0.7442 0.02262 0.01451 -0.0003 0.8555 0.0183
-8.000 -0.7326 0.02197 0.01378 0.0023 0.8368 0.0188
-7.750 -0.7187 0.02135 0.01308 0.0047 0.8201 0.0197
-7.500 -0.7028 0.02077 0.01238 0.0066 0.8050 0.0206
-7.250 -0.6860 0.02017 0.01168 0.0085 0.7907 0.0219
-7.000 -0.6675 0.01962 0.01107 0.0101 0.7769 0.0238
-6.750 -0.6486 0.01908 0.01045 0.0116 0.7641 0.0261
-6.500 -0.6290 0.01859 0.00986 0.0131 0.7519 0.0295
-6.250 -0.6089 0.01804 0.00928 0.0144 0.7393 0.0340
-6.000 -0.5887 0.01750 0.00872 0.0157 0.7274 0.0405
-5.500 -0.5486 0.01634 0.00765 0.0183 0.7042 0.0752
-5.250 -0.5298 0.01564 0.00714 0.0197 0.6933 0.1146
-5.000 -0.5120 0.01486 0.00665 0.0212 0.6821 0.1758
-4.750 -0.4945 0.01409 0.00622 0.0228 0.6712 0.2494
-4.500 -0.4761 0.01349 0.00587 0.0243 0.6609 0.3167
-4.250 -0.4561 0.01299 0.00559 0.0257 0.6496 0.3744
-4.000 -0.4359 0.01256 0.00534 0.0271 0.6394 0.4282
-3.750 -0.4147 0.01219 0.00514 0.0285 0.6284 0.4803
-3.500 -0.3930 0.01187 0.00498 0.0298 0.6180 0.5301
-3.250 -0.3701 0.01161 0.00485 0.0310 0.6075 0.5751
-3.000 -0.3454 0.01144 0.00476 0.0319 0.5967 0.6098
-2.500 -0.2934 0.01127 0.00463 0.0333 0.5755 0.6637
-2.250 -0.2667 0.01126 0.00461 0.0339 0.5653 0.6875
-2.000 -0.2398 0.01127 0.00459 0.0344 0.5545 0.7092
-1.750 -0.2126 0.01130 0.00458 0.0349 0.5442 0.7276
-1.500 -0.1851 0.01135 0.00457 0.0353 0.5338 0.7430
-1.250 -0.1573 0.01141 0.00458 0.0356 0.5233 0.7565
-1.000 -0.1301 0.01148 0.00457 0.0360 0.5134 0.7691
-0.750 -0.1028 0.01154 0.00457 0.0363 0.5028 0.7812
-0.500 -0.0746 0.01165 0.00461 0.0366 0.4931 0.7908
-0.250 -0.0479 0.01171 0.00460 0.0370 0.4828 0.8017
0.000 -0.0194 0.01183 0.00467 0.0371 0.4729 0.8098
0.250 0.0070 0.01192 0.00467 0.0376 0.4630 0.8197
0.500 0.0357 0.01205 0.00477 0.0377 0.4533 0.8269
0.750 0.0611 0.01215 0.00476 0.0383 0.4439 0.8368
1.000 0.0903 0.01230 0.00490 0.0383 0.4341 0.8431
1.500 0.1443 0.01256 0.00505 0.0390 0.4158 0.8584
1.750 0.1722 0.01273 0.00514 0.0392 0.4071 0.8644
2.000 0.1972 0.01281 0.00519 0.0398 0.3982 0.8722
2.250 0.2259 0.01298 0.00529 0.0398 0.3900 0.8766
2.500 0.2545 0.01311 0.00542 0.0398 0.3811 0.8816
3.000 0.3071 0.01337 0.00560 0.0404 0.3653 0.8931
3.250 0.3360 0.01355 0.00573 0.0402 0.3575 0.8972
3.500 0.3633 0.01370 0.00586 0.0403 0.3498 0.9024
3.750 0.3871 0.01382 0.00595 0.0410 0.3428 0.9090
4.000 0.4176 0.01402 0.00612 0.0405 0.3358 0.9123
4.250 0.4468 0.01419 0.00629 0.0402 0.3282 0.9166
4.500 0.4719 0.01438 0.00642 0.0406 0.3219 0.9226
4.750 0.4998 0.01454 0.00660 0.0405 0.3155 0.9273
5.000 0.5309 0.01475 0.00680 0.0397 0.3088 0.9306
5.250 0.5600 0.01496 0.00700 0.0393 0.3027 0.9349
5.500 0.5833 0.01512 0.00717 0.0400 0.2964 0.9411
5.750 0.6150 0.01536 0.00739 0.0389 0.2905 0.9437
6.000 0.6467 0.01559 0.00764 0.0379 0.2848 0.9465
6.250 0.6768 0.01581 0.00789 0.0371 0.2786 0.9502
6.500 0.7011 0.01606 0.00810 0.0375 0.2733 0.9555
6.750 0.7327 0.01629 0.00839 0.0364 0.2676 0.9581
7.000 0.7651 0.01656 0.00869 0.0350 0.2618 0.9606
7.250 0.7956 0.01689 0.00897 0.0340 0.2567 0.9638
7.500 0.8242 0.01714 0.00930 0.0334 0.2510 0.9677
7.750 0.8532 0.01743 0.00963 0.0327 0.2457 0.9711
8.250 0.9168 0.01811 0.01038 0.0299 0.2351 0.9765
8.500 0.9450 0.01845 0.01076 0.0292 0.2298 0.9804
8.750 0.9734 0.01887 0.01115 0.0283 0.2250 0.9837
9.000 1.0052 0.01921 0.01162 0.0268 0.2192 0.9866
9.250 1.0345 0.01962 0.01206 0.0256 0.2137 0.9904
9.500 1.0624 0.02009 0.01255 0.0247 0.2088 0.9942
9.750 1.0920 0.02051 0.01308 0.0234 0.2032 0.9978
10.000 1.1114 0.02097 0.01356 0.0240 0.1985 1.0000
10.250 1.1151 0.02140 0.01398 0.0274 0.1955 1.0000
10.500 1.1203 0.02177 0.01445 0.0307 0.1919 1.0000
10.750 1.1243 0.02218 0.01492 0.0340 0.1883 1.0000
11.000 1.1252 0.02265 0.01541 0.0377 0.1850 1.0000
11.250 1.1251 0.02324 0.01599 0.0412 0.1820 1.0000
11.500 1.1313 0.02392 0.01673 0.0435 0.1787 1.0000
11.750 1.1396 0.02468 0.01758 0.0451 0.1747 1.0000
12.000 1.1470 0.02558 0.01852 0.0466 0.1709 1.0000
12.250 1.1533 0.02665 0.01959 0.0478 0.1676 1.0000
12.500 1.1623 0.02771 0.02075 0.0487 0.1638 1.0000
12.750 1.1703 0.02888 0.02202 0.0494 0.1600 1.0000
13.000 1.1762 0.03025 0.02343 0.0501 0.1563 1.0000
13.250 1.1808 0.03180 0.02499 0.0506 0.1529 1.0000
13.500 1.1876 0.03331 0.02663 0.0509 0.1489 1.0000
13.750 1.1920 0.03504 0.02845 0.0511 0.1452 1.0000
14.000 1.1939 0.03703 0.03045 0.0512 0.1418 1.0000
14.250 1.1967 0.03905 0.03257 0.0511 0.1383 1.0000
14.500 1.1991 0.04120 0.03483 0.0509 0.1346 1.0000
14.750 1.1986 0.04366 0.03735 0.0505 0.1311 1.0000
15.000 1.1961 0.04634 0.04004 0.0500 0.1280 1.0000
15.250 1.1961 0.04897 0.04281 0.0493 0.1245 1.0000
15.500 1.1938 0.05190 0.04584 0.0485 0.1212 1.0000
15.750 1.1895 0.05515 0.04913 0.0474 0.1180 1.0000
16.000 1.1857 0.05842 0.05245 0.0463 0.1153 1.0000
16.250 1.1814 0.06194 0.05611 0.0450 0.1120 1.0000
16.500 1.1756 0.06572 0.05997 0.0435 0.1089 1.0000
16.750 1.1694 0.06960 0.06388 0.0418 0.1062 1.0000
17.000 1.1634 0.07355 0.06790 0.0402 0.1035 1.0000
17.250 1.1556 0.07791 0.07239 0.0382 0.1006 1.0000
17.500 1.1475 0.08238 0.07695 0.0362 0.0979 1.0000
17.750 1.1414 0.08656 0.08115 0.0342 0.0953 1.0000
18.000 1.1336 0.09112 0.08578 0.0321 0.0927 1.0000
18.250 1.1237 0.09614 0.09093 0.0296 0.0902 1.0000
18.500 1.1143 0.10115 0.09602 0.0271 0.0877 1.0000
18.750 1.1102 0.10525 0.10013 0.0250 0.0853 1.0000
19.000 1.1029 0.11000 0.10495 0.0226 0.0830 1.0000
19.250 1.0905 0.11579 0.11088 0.0196 0.0806 1.0000
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Polar data table (+)
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