MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 200,000 Max Cl/Cd: 48.4 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh95-il-200000.txt Download as CSV file: xf-mh95-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4151 0.09326 0.08990 -0.0437 1.0000 0.0904
-10.750 -0.4303 0.08793 0.08461 -0.0447 1.0000 0.0922
-10.250 -0.8928 0.05354 0.04816 -0.0335 1.0000 0.0459
-10.000 -0.9406 0.04861 0.04227 -0.0233 1.0000 0.0392
-9.750 -0.9348 0.04573 0.03930 -0.0209 1.0000 0.0390
-9.500 -0.9315 0.04337 0.03677 -0.0179 1.0000 0.0387
-9.250 -0.9256 0.04109 0.03434 -0.0151 1.0000 0.0383
-9.000 -0.9192 0.03890 0.03194 -0.0123 1.0000 0.0379
-8.750 -0.9112 0.03686 0.02968 -0.0095 1.0000 0.0375
-8.500 -0.9012 0.03502 0.02761 -0.0070 1.0000 0.0372
-8.250 -0.8890 0.03333 0.02569 -0.0046 1.0000 0.0371
-8.000 -0.8708 0.03181 0.02397 -0.0033 0.9993 0.0372
-7.750 -0.8373 0.03029 0.02224 -0.0048 0.9959 0.0375
-7.500 -0.8023 0.02904 0.02082 -0.0065 0.9927 0.0380
-7.250 -0.7705 0.02794 0.01958 -0.0075 0.9884 0.0386
-7.000 -0.7361 0.02691 0.01846 -0.0090 0.9847 0.0396
-6.750 -0.6996 0.02601 0.01768 -0.0112 0.9819 0.0414
-6.500 -0.6730 0.02523 0.01689 -0.0114 0.9759 0.0431
-6.250 -0.6390 0.02452 0.01612 -0.0128 0.9717 0.0447
-6.000 -0.6088 0.02356 0.01526 -0.0139 0.9675 0.0467
-5.750 -0.5842 0.02284 0.01456 -0.0137 0.9607 0.0492
-5.500 -0.5512 0.02208 0.01382 -0.0152 0.9566 0.0529
-5.250 -0.5273 0.02143 0.01318 -0.0149 0.9497 0.0592
-5.000 -0.4997 0.02056 0.01242 -0.0154 0.9439 0.0724
-4.750 -0.4755 0.01850 0.01135 -0.0161 0.9400 0.2149
-4.500 -0.4646 0.01745 0.01086 -0.0137 0.9302 0.3243
-4.250 -0.4345 0.01655 0.01050 -0.0146 0.9258 0.4338
-4.000 -0.4148 0.01598 0.01034 -0.0132 0.9181 0.5171
-3.750 -0.3865 0.01564 0.01039 -0.0129 0.9122 0.6007
-3.500 -0.3487 0.01564 0.01059 -0.0141 0.9089 0.6670
-3.250 -0.3282 0.01580 0.01082 -0.0120 0.8996 0.7027
-3.000 -0.2930 0.01597 0.01097 -0.0125 0.8948 0.7332
-2.750 -0.2520 0.01620 0.01119 -0.0139 0.8920 0.7536
-2.500 -0.2316 0.01639 0.01138 -0.0117 0.8820 0.7663
-2.250 -0.1921 0.01641 0.01135 -0.0131 0.8780 0.7762
-2.000 -0.1492 0.01627 0.01113 -0.0154 0.8754 0.7878
-1.750 -0.1265 0.01640 0.01126 -0.0134 0.8656 0.7947
-1.500 -0.0865 0.01623 0.01103 -0.0151 0.8616 0.8042
-1.250 -0.0402 0.01608 0.01084 -0.0176 0.8594 0.8108
-1.000 -0.0107 0.01607 0.01081 -0.0170 0.8514 0.8182
-0.750 0.0273 0.01580 0.01049 -0.0184 0.8453 0.8267
-0.500 0.0777 0.01564 0.01030 -0.0216 0.8420 0.8307
-0.250 0.1050 0.01553 0.01017 -0.0208 0.8314 0.8373
0.000 0.1469 0.01516 0.00974 -0.0231 0.8249 0.8444
0.250 0.1782 0.01511 0.00968 -0.0229 0.8132 0.8484
0.500 0.2280 0.01497 0.00947 -0.0264 0.8055 0.8522
0.750 0.2460 0.01473 0.00919 -0.0244 0.7905 0.8617
1.000 0.2801 0.01470 0.00913 -0.0248 0.7762 0.8649
1.250 0.3153 0.01467 0.00905 -0.0257 0.7608 0.8687
1.500 0.3442 0.01459 0.00890 -0.0256 0.7443 0.8745
1.750 0.3669 0.01445 0.00868 -0.0244 0.7265 0.8809
2.000 0.3997 0.01447 0.00863 -0.0249 0.7071 0.8841
2.250 0.4284 0.01448 0.00856 -0.0248 0.6865 0.8885
2.500 0.4409 0.01437 0.00835 -0.0218 0.6668 0.8967
2.750 0.4712 0.01444 0.00831 -0.0219 0.6443 0.8997
3.000 0.4956 0.01450 0.00830 -0.0210 0.6195 0.9040
3.250 0.5036 0.01443 0.00813 -0.0171 0.5970 0.9124
3.500 0.5291 0.01453 0.00810 -0.0165 0.5701 0.9159
3.750 0.5514 0.01465 0.00810 -0.0153 0.5422 0.9204
4.000 0.5579 0.01464 0.00797 -0.0112 0.5201 0.9288
4.250 0.5848 0.01482 0.00805 -0.0111 0.4918 0.9322
4.500 0.6067 0.01502 0.00811 -0.0101 0.4660 0.9369
4.750 0.6187 0.01510 0.00811 -0.0072 0.4442 0.9444
5.000 0.6480 0.01538 0.00829 -0.0078 0.4180 0.9477
5.250 0.6712 0.01566 0.00844 -0.0073 0.3955 0.9527
5.500 0.6912 0.01589 0.00858 -0.0062 0.3746 0.9587
5.750 0.7247 0.01626 0.00887 -0.0078 0.3514 0.9617
6.000 0.7515 0.01659 0.00911 -0.0082 0.3316 0.9664
6.250 0.7749 0.01689 0.00934 -0.0079 0.3135 0.9715
6.500 0.8066 0.01729 0.00966 -0.0094 0.2939 0.9749
6.750 0.8333 0.01767 0.00996 -0.0099 0.2763 0.9801
7.000 0.8624 0.01809 0.01032 -0.0109 0.2589 0.9843
7.250 0.8917 0.01855 0.01071 -0.0121 0.2414 0.9884
7.500 0.9180 0.01904 0.01114 -0.0127 0.2249 0.9934
7.750 0.9481 0.01959 0.01162 -0.0142 0.2089 0.9979
8.000 0.9585 0.01997 0.01198 -0.0118 0.1983 1.0000
8.250 0.9481 0.02011 0.01209 -0.0054 0.1926 1.0000
8.500 0.9362 0.02029 0.01222 0.0011 0.1875 1.0000
8.750 0.9322 0.02042 0.01239 0.0063 0.1814 1.0000
9.000 0.9392 0.02094 0.01280 0.0092 0.1747 1.0000
9.250 0.9539 0.02146 0.01335 0.0108 0.1675 1.0000
9.500 0.9689 0.02208 0.01391 0.0123 0.1614 1.0000
9.750 0.9863 0.02280 0.01462 0.0133 0.1559 1.0000
10.000 1.0035 0.02342 0.01527 0.0144 0.1509 1.0000
10.250 1.0211 0.02416 0.01595 0.0154 0.1467 1.0000
10.500 1.0413 0.02501 0.01679 0.0160 0.1426 1.0000
10.750 1.0581 0.02569 0.01755 0.0171 0.1389 1.0000
11.000 1.0755 0.02641 0.01829 0.0180 0.1354 1.0000
11.250 1.0953 0.02725 0.01907 0.0185 0.1323 1.0000
11.500 1.1183 0.02825 0.02008 0.0187 0.1294 1.0000
11.750 1.1342 0.02908 0.02105 0.0198 0.1271 1.0000
12.000 1.1504 0.02994 0.02199 0.0208 0.1246 1.0000
12.250 1.1671 0.03078 0.02286 0.0216 0.1221 1.0000
12.500 1.1870 0.03170 0.02375 0.0221 0.1197 1.0000
12.750 1.2159 0.03308 0.02511 0.0212 0.1172 1.0000
13.000 1.2255 0.03410 0.02631 0.0229 0.1157 1.0000
13.250 1.2362 0.03521 0.02758 0.0243 0.1140 1.0000
13.500 1.2470 0.03636 0.02886 0.0256 0.1121 1.0000
13.750 1.2588 0.03750 0.03007 0.0268 0.1103 1.0000
14.000 1.2734 0.03861 0.03123 0.0275 0.1086 1.0000
14.250 1.2943 0.03984 0.03244 0.0276 0.1067 1.0000
14.500 1.3125 0.04178 0.03446 0.0277 0.1049 1.0000
14.750 1.3103 0.04335 0.03625 0.0298 0.1039 1.0000
15.000 1.3087 0.04510 0.03820 0.0317 0.1027 1.0000
15.250 1.3081 0.04703 0.04031 0.0331 0.1014 1.0000
15.500 1.3076 0.04899 0.04244 0.0344 0.1001 1.0000
15.750 1.3065 0.05106 0.04466 0.0354 0.0988 1.0000
16.000 1.3083 0.05298 0.04667 0.0362 0.0975 1.0000
16.250 1.3155 0.05475 0.04848 0.0366 0.0962 1.0000
16.500 1.3341 0.05641 0.05011 0.0364 0.0945 1.0000
16.750 1.3240 0.05995 0.05384 0.0370 0.0935 1.0000
17.000 1.3008 0.06387 0.05802 0.0374 0.0930 1.0000
17.250 1.2742 0.06864 0.06306 0.0370 0.0925 1.0000
17.500 1.2418 0.07459 0.06928 0.0356 0.0920 1.0000
17.750 1.1977 0.08276 0.07774 0.0325 0.0917 1.0000
18.000 1.1153 0.09780 0.09318 0.0247 0.0921 1.0000
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