MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 500,000 Max Cl/Cd: 62.6 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh95-il-500000.txt Download as CSV file: xf-mh95-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5776 0.08675 0.08384 -0.0657 1.0000 0.0218
-14.750 -0.5938 0.08100 0.07805 -0.0671 1.0000 0.0215
-14.500 -0.6232 0.07327 0.07021 -0.0700 1.0000 0.0214
-14.250 -0.6529 0.06607 0.06288 -0.0723 1.0000 0.0212
-14.000 -0.6802 0.05980 0.05649 -0.0735 1.0000 0.0210
-13.750 -0.7085 0.05397 0.05051 -0.0739 1.0000 0.0208
-13.500 -0.7370 0.04874 0.04513 -0.0734 1.0000 0.0207
-13.250 -0.7632 0.06236 0.05895 -0.0722 1.0000 0.0248
-13.000 -0.7870 0.05860 0.05508 -0.0709 1.0000 0.0245
-12.750 -0.9603 0.04210 0.03703 -0.0595 1.0000 0.0189
-12.500 -0.9730 0.04066 0.03546 -0.0552 1.0000 0.0188
-12.250 -0.9836 0.03905 0.03373 -0.0509 1.0000 0.0189
-12.000 -0.9957 0.03785 0.03239 -0.0459 1.0000 0.0189
-11.750 -1.0100 0.03692 0.03133 -0.0402 1.0000 0.0188
-11.500 -0.9939 0.03496 0.02920 -0.0401 0.9978 0.0188
-11.250 -0.9738 0.03314 0.02724 -0.0404 0.9957 0.0189
-11.000 -0.9503 0.03152 0.02550 -0.0411 0.9939 0.0191
-10.750 -0.9276 0.03002 0.02388 -0.0413 0.9919 0.0191
-10.500 -0.9056 0.02883 0.02263 -0.0413 0.9890 0.0193
-10.250 -0.8808 0.02775 0.02148 -0.0417 0.9866 0.0196
-10.000 -0.8528 0.02661 0.02027 -0.0426 0.9847 0.0197
-9.750 -0.8233 0.02570 0.01931 -0.0438 0.9832 0.0202
-9.500 -0.7923 0.02487 0.01841 -0.0452 0.9820 0.0207
-9.250 -0.7752 0.02401 0.01749 -0.0437 0.9770 0.0209
-9.000 -0.7483 0.02319 0.01660 -0.0442 0.9742 0.0213
-8.750 -0.7186 0.02236 0.01570 -0.0451 0.9722 0.0216
-8.500 -0.6867 0.02164 0.01492 -0.0465 0.9707 0.0220
-8.250 -0.6571 0.02044 0.01374 -0.0477 0.9694 0.0224
-8.000 -0.6458 0.01978 0.01308 -0.0450 0.9624 0.0228
-7.750 -0.6183 0.01908 0.01238 -0.0455 0.9596 0.0234
-7.500 -0.5874 0.01841 0.01169 -0.0466 0.9576 0.0241
-7.250 -0.5547 0.01776 0.01102 -0.0481 0.9561 0.0248
-7.000 -0.5376 0.01730 0.01052 -0.0462 0.9501 0.0254
-6.750 -0.5140 0.01657 0.00979 -0.0458 0.9459 0.0263
-6.500 -0.4825 0.01598 0.00920 -0.0469 0.9437 0.0277
-6.250 -0.4476 0.01547 0.00868 -0.0486 0.9422 0.0295
-6.000 -0.4128 0.01482 0.00806 -0.0503 0.9410 0.0323
-5.750 -0.3952 0.01444 0.00766 -0.0483 0.9346 0.0349
-5.500 -0.3678 0.01387 0.00715 -0.0484 0.9307 0.0416
-5.250 -0.3392 0.01284 0.00643 -0.0492 0.9283 0.0917
-5.000 -0.3104 0.01175 0.00582 -0.0501 0.9262 0.1855
-4.750 -0.2795 0.01092 0.00535 -0.0513 0.9245 0.2613
-4.000 -0.2099 0.00919 0.00433 -0.0490 0.9092 0.4391
-3.750 -0.1911 0.00875 0.00409 -0.0471 0.9020 0.4918
-3.500 -0.1675 0.00823 0.00385 -0.0462 0.8961 0.5611
-3.250 -0.1364 0.00785 0.00368 -0.0467 0.8922 0.6256
-3.000 -0.1147 0.00773 0.00364 -0.0451 0.8840 0.6624
-2.750 -0.0845 0.00762 0.00359 -0.0452 0.8777 0.6893
-2.500 -0.0545 0.00755 0.00350 -0.0453 0.8706 0.7039
-2.250 -0.0269 0.00749 0.00339 -0.0450 0.8614 0.7152
-2.000 0.0029 0.00744 0.00334 -0.0450 0.8522 0.7236
-1.750 0.0328 0.00740 0.00322 -0.0452 0.8420 0.7328
-1.500 0.0597 0.00739 0.00320 -0.0447 0.8299 0.7398
-1.250 0.0886 0.00740 0.00315 -0.0446 0.8179 0.7473
-1.000 0.1178 0.00741 0.00309 -0.0447 0.8051 0.7542
-0.750 0.1442 0.00745 0.00311 -0.0440 0.7908 0.7606
-0.500 0.1706 0.00751 0.00309 -0.0435 0.7758 0.7678
-0.250 0.1969 0.00756 0.00310 -0.0430 0.7605 0.7735
0.000 0.2230 0.00764 0.00313 -0.0424 0.7443 0.7789
0.250 0.2485 0.00773 0.00314 -0.0417 0.7274 0.7848
0.500 0.2735 0.00781 0.00313 -0.0409 0.7096 0.7899
0.750 0.2980 0.00791 0.00319 -0.0400 0.6915 0.7943
1.000 0.3220 0.00803 0.00324 -0.0390 0.6724 0.7994
1.250 0.3456 0.00816 0.00328 -0.0380 0.6531 0.8052
1.500 0.3684 0.00827 0.00332 -0.0368 0.6328 0.8098
1.750 0.3907 0.00842 0.00340 -0.0355 0.6118 0.8143
2.000 0.4125 0.00858 0.00347 -0.0341 0.5893 0.8192
2.250 0.4337 0.00874 0.00352 -0.0328 0.5630 0.8243
2.500 0.4531 0.00891 0.00358 -0.0309 0.5353 0.8284
2.750 0.4731 0.00910 0.00368 -0.0292 0.5082 0.8325
3.250 0.5144 0.00949 0.00387 -0.0263 0.4605 0.8417
3.500 0.5347 0.00967 0.00395 -0.0249 0.4366 0.8456
3.750 0.5540 0.00988 0.00408 -0.0231 0.4139 0.8493
4.000 0.5731 0.01009 0.00421 -0.0214 0.3928 0.8536
4.250 0.5931 0.01029 0.00433 -0.0199 0.3729 0.8582
4.500 0.6133 0.01048 0.00444 -0.0185 0.3537 0.8624
4.750 0.6318 0.01068 0.00459 -0.0167 0.3356 0.8663
5.000 0.6507 0.01091 0.00475 -0.0150 0.3179 0.8707
5.250 0.6707 0.01114 0.00492 -0.0136 0.3017 0.8754
5.500 0.6910 0.01139 0.00510 -0.0123 0.2868 0.8799
5.750 0.7095 0.01162 0.00530 -0.0105 0.2730 0.8842
6.000 0.7290 0.01184 0.00550 -0.0090 0.2598 0.8891
6.250 0.7491 0.01210 0.00571 -0.0077 0.2468 0.8942
6.500 0.7679 0.01235 0.00592 -0.0061 0.2346 0.8989
6.750 0.7851 0.01262 0.00616 -0.0042 0.2224 0.9042
7.000 0.8044 0.01286 0.00638 -0.0027 0.2109 0.9102
7.250 0.8220 0.01313 0.00662 -0.0010 0.1993 0.9158
7.500 0.8379 0.01343 0.00689 0.0011 0.1876 0.9221
7.750 0.8547 0.01374 0.00716 0.0029 0.1756 0.9292
8.000 0.8694 0.01401 0.00743 0.0052 0.1647 0.9370
8.250 0.8843 0.01434 0.00774 0.0073 0.1551 0.9459
8.500 0.8985 0.01472 0.00808 0.0095 0.1455 0.9565
8.750 0.9208 0.01508 0.00845 0.0100 0.1378 0.9661
9.000 0.9475 0.01566 0.00899 0.0093 0.1300 0.9754
9.250 0.9796 0.01612 0.00947 0.0077 0.1243 0.9839
9.500 1.0073 0.01679 0.01010 0.0065 0.1186 1.0000
9.750 1.0249 0.01720 0.01053 0.0076 0.1154 1.0000
10.000 1.0437 0.01764 0.01098 0.0084 0.1123 1.0000
10.250 1.0605 0.01819 0.01153 0.0095 0.1094 1.0000
10.500 1.0740 0.01893 0.01224 0.0111 0.1064 1.0000
10.750 1.0895 0.01955 0.01290 0.0123 0.1044 1.0000
11.000 1.1071 0.02008 0.01347 0.0134 0.1025 1.0000
11.250 1.1234 0.02066 0.01409 0.0145 0.1006 1.0000
11.500 1.1384 0.02132 0.01477 0.0157 0.0987 1.0000
11.750 1.1512 0.02210 0.01556 0.0172 0.0968 1.0000
12.000 1.1609 0.02311 0.01657 0.0189 0.0947 1.0000
12.250 1.1729 0.02402 0.01752 0.0203 0.0934 1.0000
12.500 1.1880 0.02471 0.01829 0.0214 0.0923 1.0000
12.750 1.2018 0.02551 0.01914 0.0225 0.0911 1.0000
13.000 1.2151 0.02634 0.02003 0.0235 0.0894 1.0000
13.250 1.2272 0.02726 0.02100 0.0247 0.0882 1.0000
13.500 1.2383 0.02828 0.02205 0.0258 0.0870 1.0000
13.750 1.2480 0.02943 0.02322 0.0269 0.0857 1.0000
14.000 1.2559 0.03079 0.02459 0.0282 0.0843 1.0000
14.250 1.2653 0.03207 0.02593 0.0292 0.0830 1.0000
14.500 1.2766 0.03317 0.02712 0.0300 0.0822 1.0000
14.750 1.2868 0.03438 0.02842 0.0307 0.0812 1.0000
15.000 1.2965 0.03567 0.02978 0.0314 0.0801 1.0000
15.250 1.3055 0.03704 0.03122 0.0320 0.0789 1.0000
15.500 1.3138 0.03850 0.03274 0.0326 0.0779 1.0000
15.750 1.3214 0.04007 0.03436 0.0331 0.0769 1.0000
16.000 1.3279 0.04177 0.03609 0.0335 0.0758 1.0000
16.250 1.3344 0.04354 0.03787 0.0340 0.0746 1.0000
16.500 1.3407 0.04536 0.03976 0.0344 0.0736 1.0000
16.750 1.3460 0.04731 0.04183 0.0344 0.0729 1.0000
17.000 1.3508 0.04938 0.04401 0.0344 0.0721 1.0000
17.250 1.3552 0.05154 0.04627 0.0343 0.0712 1.0000
17.500 1.3591 0.05381 0.04863 0.0340 0.0703 1.0000
17.750 1.3625 0.05618 0.05108 0.0336 0.0693 1.0000
18.000 1.3657 0.05861 0.05358 0.0331 0.0685 1.0000
18.250 1.3682 0.06119 0.05621 0.0324 0.0676 1.0000
18.500 1.3708 0.06377 0.05882 0.0319 0.0667 1.0000
18.750 1.3751 0.06601 0.06108 0.0317 0.0654 1.0000
19.000 1.3735 0.06930 0.06450 0.0306 0.0648 1.0000
19.250 1.3704 0.07288 0.06823 0.0291 0.0642 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 95 15.86% (mh95-il)