MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 100,000 Max Cl/Cd: 37.44 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh95-il-100000-n5.txt Download as CSV file: xf-mh95-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5604 0.10287 0.09685 -0.0565 1.0000 0.0295
-13.750 -0.5949 0.09231 0.08619 -0.0625 1.0000 0.0292
-13.500 -0.6281 0.08370 0.07744 -0.0672 1.0000 0.0289
-13.250 -0.6571 0.07704 0.07063 -0.0701 1.0000 0.0287
-13.000 -0.6840 0.07158 0.06501 -0.0716 1.0000 0.0286
-12.750 -0.7104 0.06691 0.06015 -0.0718 1.0000 0.0285
-12.500 -0.7319 0.06321 0.05629 -0.0709 1.0000 0.0284
-12.250 -0.7543 0.05983 0.05271 -0.0691 1.0000 0.0284
-12.000 -0.7731 0.05705 0.04976 -0.0666 1.0000 0.0284
-11.750 -0.7914 0.05456 0.04708 -0.0635 1.0000 0.0285
-11.500 -0.8071 0.05241 0.04475 -0.0598 1.0000 0.0285
-11.250 -0.8220 0.05050 0.04267 -0.0557 1.0000 0.0286
-11.000 -0.8362 0.04879 0.04078 -0.0512 1.0000 0.0286
-10.750 -0.8499 0.04731 0.03912 -0.0462 1.0000 0.0288
-10.500 -0.8622 0.04590 0.03752 -0.0410 1.0000 0.0290
-10.250 -0.8693 0.04434 0.03571 -0.0365 1.0000 0.0293
-10.000 -0.8722 0.04277 0.03386 -0.0325 1.0000 0.0297
-9.750 -0.8668 0.04157 0.03267 -0.0297 1.0000 0.0303
-9.500 -0.8617 0.04045 0.03150 -0.0268 1.0000 0.0308
-9.250 -0.8551 0.03925 0.03021 -0.0240 1.0000 0.0313
-9.000 -0.8472 0.03804 0.02887 -0.0213 1.0000 0.0320
-8.750 -0.8374 0.03680 0.02750 -0.0188 1.0000 0.0326
-8.500 -0.8261 0.03561 0.02616 -0.0164 1.0000 0.0330
-8.250 -0.8007 0.03425 0.02463 -0.0165 0.9975 0.0338
-8.000 -0.7725 0.03303 0.02334 -0.0173 0.9943 0.0346
-7.750 -0.7459 0.03195 0.02226 -0.0179 0.9907 0.0355
-7.500 -0.7198 0.03094 0.02123 -0.0184 0.9866 0.0367
-7.250 -0.6917 0.03004 0.02024 -0.0192 0.9828 0.0385
-7.000 -0.6683 0.02916 0.01936 -0.0192 0.9779 0.0405
-6.750 -0.6434 0.02835 0.01853 -0.0194 0.9730 0.0429
-6.500 -0.6149 0.02753 0.01764 -0.0203 0.9691 0.0456
-6.250 -0.5963 0.02673 0.01683 -0.0193 0.9624 0.0483
-6.000 -0.5698 0.02594 0.01599 -0.0197 0.9575 0.0526
-5.750 -0.5454 0.02519 0.01525 -0.0196 0.9522 0.0597
-5.500 -0.5242 0.02439 0.01453 -0.0190 0.9455 0.0709
-5.250 -0.4971 0.02341 0.01377 -0.0195 0.9410 0.1014
-5.000 -0.4813 0.02240 0.01319 -0.0180 0.9335 0.1609
-4.750 -0.4595 0.02139 0.01269 -0.0178 0.9275 0.2528
-4.500 -0.4377 0.02043 0.01228 -0.0174 0.9220 0.3512
-4.250 -0.4230 0.01969 0.01203 -0.0152 0.9136 0.4402
-4.000 -0.3961 0.01921 0.01212 -0.0146 0.9090 0.5413
-3.750 -0.3768 0.01922 0.01239 -0.0122 0.9009 0.6095
-3.500 -0.3481 0.01939 0.01265 -0.0114 0.8949 0.6583
-3.250 -0.3120 0.01957 0.01278 -0.0122 0.8912 0.6885
-3.000 -0.2939 0.01967 0.01283 -0.0099 0.8810 0.7069
-2.750 -0.2591 0.01972 0.01278 -0.0106 0.8763 0.7234
-2.500 -0.2361 0.01977 0.01276 -0.0093 0.8677 0.7377
-2.250 -0.2061 0.01972 0.01260 -0.0093 0.8611 0.7520
-2.000 -0.1663 0.01980 0.01261 -0.0106 0.8576 0.7621
-1.750 -0.1485 0.01983 0.01259 -0.0083 0.8463 0.7736
-1.500 -0.1116 0.01976 0.01244 -0.0093 0.8417 0.7840
-1.250 -0.0894 0.01978 0.01242 -0.0077 0.8315 0.7932
-1.000 -0.0539 0.01965 0.01222 -0.0085 0.8256 0.8019
-0.750 -0.0285 0.01957 0.01209 -0.0076 0.8159 0.8103
-0.500 0.0078 0.01946 0.01192 -0.0084 0.8086 0.8172
-0.250 0.0316 0.01928 0.01169 -0.0074 0.7979 0.8265
0.000 0.0726 0.01917 0.01153 -0.0091 0.7902 0.8316
0.250 0.0974 0.01904 0.01136 -0.0081 0.7778 0.8396
0.500 0.1354 0.01880 0.01106 -0.0096 0.7681 0.8455
0.750 0.1704 0.01869 0.01091 -0.0104 0.7551 0.8501
1.000 0.1991 0.01855 0.01073 -0.0102 0.7407 0.8564
1.250 0.2275 0.01836 0.01047 -0.0101 0.7262 0.8628
1.500 0.2649 0.01826 0.01032 -0.0115 0.7106 0.8662
1.750 0.2992 0.01817 0.01017 -0.0124 0.6940 0.8706
2.000 0.3263 0.01805 0.00998 -0.0121 0.6765 0.8767
2.250 0.3553 0.01799 0.00985 -0.0121 0.6579 0.8814
2.500 0.3866 0.01799 0.00978 -0.0126 0.6373 0.8850
2.750 0.4140 0.01800 0.00971 -0.0123 0.6168 0.8899
3.000 0.4332 0.01796 0.00959 -0.0106 0.5963 0.8967
3.250 0.4639 0.01805 0.00958 -0.0111 0.5739 0.8999
3.500 0.4890 0.01815 0.00960 -0.0105 0.5505 0.9046
3.750 0.5068 0.01821 0.00957 -0.0086 0.5283 0.9114
4.000 0.5315 0.01835 0.00962 -0.0080 0.5042 0.9157
4.250 0.5558 0.01854 0.00970 -0.0074 0.4796 0.9204
4.500 0.5720 0.01868 0.00974 -0.0054 0.4563 0.9276
4.750 0.5966 0.01894 0.00988 -0.0050 0.4312 0.9320
5.000 0.6190 0.01920 0.01004 -0.0042 0.4076 0.9373
5.250 0.6372 0.01943 0.01019 -0.0027 0.3862 0.9443
5.500 0.6639 0.01979 0.01044 -0.0030 0.3638 0.9488
5.750 0.6854 0.02011 0.01069 -0.0022 0.3445 0.9551
6.000 0.7105 0.02048 0.01099 -0.0023 0.3256 0.9602
6.250 0.7369 0.02089 0.01132 -0.0026 0.3076 0.9656
6.500 0.7620 0.02130 0.01170 -0.0028 0.2907 0.9715
6.750 0.7908 0.02176 0.01211 -0.0038 0.2740 0.9761
7.000 0.8156 0.02221 0.01253 -0.0040 0.2587 0.9823
7.250 0.8441 0.02271 0.01302 -0.0051 0.2435 0.9874
7.500 0.8698 0.02323 0.01352 -0.0056 0.2295 0.9944
7.750 0.8852 0.02370 0.01395 -0.0043 0.2188 1.0000
8.000 0.8804 0.02388 0.01415 0.0010 0.2115 1.0000
8.250 0.8767 0.02418 0.01438 0.0060 0.2051 1.0000
8.500 0.8830 0.02455 0.01478 0.0091 0.1963 1.0000
8.750 0.8907 0.02513 0.01526 0.0118 0.1890 1.0000
9.000 0.9039 0.02568 0.01587 0.0136 0.1806 1.0000
9.250 0.9149 0.02640 0.01651 0.0155 0.1741 1.0000
9.500 0.9297 0.02706 0.01723 0.0169 0.1671 1.0000
9.750 0.9422 0.02783 0.01797 0.0185 0.1611 1.0000
10.000 0.9559 0.02863 0.01878 0.0199 0.1558 1.0000
10.250 0.9701 0.02944 0.01963 0.0212 0.1505 1.0000
10.500 0.9827 0.03033 0.02050 0.0225 0.1462 1.0000
10.750 0.9969 0.03125 0.02143 0.0237 0.1425 1.0000
11.000 1.0112 0.03217 0.02244 0.0248 0.1383 1.0000
11.250 1.0245 0.03313 0.02345 0.0259 0.1348 1.0000
11.500 1.0371 0.03415 0.02444 0.0270 0.1318 1.0000
11.750 1.0511 0.03523 0.02557 0.0279 0.1289 1.0000
12.000 1.0644 0.03633 0.02680 0.0289 0.1259 1.0000
12.250 1.0773 0.03748 0.02803 0.0298 0.1233 1.0000
12.500 1.0893 0.03864 0.02923 0.0307 0.1209 1.0000
12.750 1.1024 0.03982 0.03042 0.0315 0.1188 1.0000
13.000 1.1150 0.04113 0.03178 0.0323 0.1166 1.0000
13.250 1.1233 0.04263 0.03347 0.0332 0.1144 1.0000
13.500 1.1322 0.04418 0.03516 0.0341 0.1124 1.0000
13.750 1.1407 0.04576 0.03686 0.0348 0.1105 1.0000
14.000 1.1496 0.04733 0.03852 0.0355 0.1088 1.0000
14.250 1.1597 0.04883 0.04006 0.0360 0.1071 1.0000
14.500 1.1733 0.05024 0.04145 0.0363 0.1056 1.0000
14.750 1.1735 0.05255 0.04397 0.0370 0.1041 1.0000
15.000 1.1700 0.05521 0.04687 0.0375 0.1027 1.0000
15.250 1.1662 0.05806 0.04995 0.0377 0.1014 1.0000
15.500 1.1609 0.06111 0.05319 0.0377 0.1001 1.0000
15.750 1.1553 0.06433 0.05658 0.0374 0.0988 1.0000
16.000 1.1500 0.06763 0.06004 0.0369 0.0976 1.0000
16.250 1.1473 0.07074 0.06326 0.0363 0.0964 1.0000
16.500 1.1511 0.07321 0.06578 0.0358 0.0952 1.0000
16.750 1.1636 0.07488 0.06742 0.0356 0.0939 1.0000
17.000 1.1311 0.08193 0.07478 0.0329 0.0933 1.0000
17.250 1.0781 0.09272 0.08595 0.0275 0.0927 1.0000
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