MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 500,000 Max Cl/Cd: 97.59 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh83-il-500000-n5.txt Download as CSV file: xf-mh83-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 83 13.29%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2589 0.09066 0.08706 -0.0114 0.5755 0.0120
-8.250 -0.2578 0.08631 0.08270 -0.0136 0.5686 0.0115
-7.750 -0.4079 0.02978 0.02527 -0.0605 0.5938 0.0104
-7.500 -0.3874 0.02648 0.02149 -0.0624 0.5839 0.0105
-7.250 -0.3650 0.02375 0.01837 -0.0635 0.5744 0.0106
-7.000 -0.3399 0.02202 0.01636 -0.0641 0.5638 0.0107
-6.750 -0.3137 0.02076 0.01488 -0.0644 0.5539 0.0109
-6.250 -0.2594 0.01897 0.01273 -0.0648 0.5334 0.0113
-6.000 -0.2317 0.01821 0.01179 -0.0649 0.5239 0.0115
-5.750 -0.2038 0.01746 0.01086 -0.0649 0.5138 0.0118
-5.500 -0.1758 0.01673 0.00994 -0.0649 0.5044 0.0121
-5.250 -0.1476 0.01601 0.00904 -0.0649 0.4951 0.0123
-5.000 -0.1192 0.01534 0.00822 -0.0649 0.4869 0.0125
-4.750 -0.0907 0.01477 0.00750 -0.0649 0.4778 0.0127
-4.500 -0.0621 0.01427 0.00687 -0.0648 0.4691 0.0130
-4.250 -0.0334 0.01386 0.00634 -0.0648 0.4598 0.0132
-4.000 -0.0048 0.01333 0.00573 -0.0648 0.4520 0.0135
-3.750 0.0239 0.01295 0.00529 -0.0648 0.4440 0.0139
-3.500 0.0528 0.01265 0.00492 -0.0648 0.4369 0.0143
-3.250 0.0818 0.01238 0.00458 -0.0647 0.4289 0.0148
-3.000 0.1108 0.01215 0.00428 -0.0647 0.4212 0.0153
-2.750 0.1399 0.01194 0.00399 -0.0647 0.4133 0.0158
-2.500 0.1689 0.01175 0.00373 -0.0647 0.4060 0.0166
-2.250 0.1981 0.01157 0.00352 -0.0647 0.3995 0.0178
-2.000 0.2272 0.01145 0.00333 -0.0647 0.3927 0.0190
-1.750 0.2564 0.01131 0.00314 -0.0646 0.3869 0.0204
-1.500 0.2855 0.01120 0.00298 -0.0646 0.3804 0.0227
-1.000 0.3437 0.01090 0.00273 -0.0647 0.3678 0.0516
-0.750 0.3726 0.01075 0.00267 -0.0648 0.3616 0.0862
-0.500 0.4016 0.01067 0.00263 -0.0648 0.3564 0.1143
-0.250 0.4306 0.01054 0.00262 -0.0649 0.3515 0.1549
0.000 0.4594 0.01040 0.00263 -0.0650 0.3463 0.2142
0.250 0.4881 0.01032 0.00266 -0.0651 0.3413 0.2707
0.500 0.5170 0.01024 0.00269 -0.0652 0.3367 0.3189
0.750 0.5459 0.01019 0.00273 -0.0652 0.3316 0.3636
1.000 0.5745 0.01017 0.00279 -0.0653 0.3268 0.4147
1.250 0.6031 0.01011 0.00286 -0.0653 0.3231 0.4775
1.500 0.6315 0.01000 0.00294 -0.0653 0.3193 0.5535
1.750 0.6593 0.00989 0.00304 -0.0652 0.3154 0.6428
2.000 0.6848 0.00966 0.00316 -0.0645 0.3116 0.7727
2.500 0.7419 0.00949 0.00327 -0.0640 0.3044 1.0000
2.750 0.7706 0.00963 0.00335 -0.0641 0.3008 1.0000
3.000 0.7992 0.00980 0.00345 -0.0641 0.2975 1.0000
3.250 0.8275 0.00998 0.00357 -0.0641 0.2943 1.0000
3.500 0.8560 0.01014 0.00369 -0.0641 0.2917 1.0000
3.750 0.8845 0.01028 0.00381 -0.0641 0.2888 1.0000
4.000 0.9128 0.01044 0.00394 -0.0641 0.2856 1.0000
4.250 0.9410 0.01062 0.00408 -0.0641 0.2825 1.0000
4.500 0.9690 0.01082 0.00423 -0.0641 0.2797 1.0000
4.750 0.9968 0.01103 0.00441 -0.0641 0.2772 1.0000
5.000 1.0250 0.01119 0.00457 -0.0641 0.2750 1.0000
5.250 1.0530 0.01136 0.00473 -0.0641 0.2724 1.0000
5.500 1.0807 0.01155 0.00491 -0.0641 0.2696 1.0000
5.750 1.1083 0.01176 0.00510 -0.0641 0.2669 1.0000
6.000 1.1356 0.01200 0.00531 -0.0641 0.2645 1.0000
6.250 1.1627 0.01225 0.00555 -0.0640 0.2622 1.0000
6.500 1.1903 0.01243 0.00575 -0.0640 0.2601 1.0000
6.750 1.2177 0.01263 0.00597 -0.0640 0.2577 1.0000
7.000 1.2448 0.01285 0.00620 -0.0640 0.2552 1.0000
7.250 1.2716 0.01309 0.00645 -0.0639 0.2530 1.0000
7.500 1.2981 0.01335 0.00671 -0.0638 0.2507 1.0000
7.750 1.3242 0.01365 0.00700 -0.0637 0.2482 1.0000
8.000 1.3507 0.01389 0.00727 -0.0636 0.2462 1.0000
8.250 1.3772 0.01412 0.00754 -0.0635 0.2440 1.0000
8.500 1.4034 0.01438 0.00784 -0.0634 0.2419 1.0000
8.750 1.4292 0.01465 0.00814 -0.0633 0.2397 1.0000
9.000 1.4546 0.01495 0.00845 -0.0632 0.2372 1.0000
9.250 1.4794 0.01530 0.00881 -0.0630 0.2347 1.0000
9.500 1.5040 0.01565 0.00918 -0.0627 0.2325 1.0000
9.750 1.5293 0.01592 0.00952 -0.0625 0.2307 1.0000
10.000 1.5540 0.01622 0.00988 -0.0623 0.2283 1.0000
10.250 1.5781 0.01655 0.01025 -0.0620 0.2257 1.0000
10.500 1.6015 0.01691 0.01065 -0.0617 0.2232 1.0000
10.750 1.6239 0.01733 0.01109 -0.0613 0.2207 1.0000
11.000 1.6458 0.01777 0.01156 -0.0608 0.2183 1.0000
11.250 1.6685 0.01812 0.01199 -0.0604 0.2159 1.0000
11.500 1.6902 0.01852 0.01247 -0.0599 0.2133 1.0000
11.750 1.7105 0.01898 0.01297 -0.0592 0.2104 1.0000
12.000 1.7288 0.01952 0.01354 -0.0584 0.2076 1.0000
12.250 1.7449 0.02013 0.01420 -0.0573 0.2048 1.0000
12.500 1.7610 0.02063 0.01479 -0.0561 0.2024 1.0000
12.750 1.7728 0.02126 0.01550 -0.0545 0.1996 1.0000
13.000 1.7823 0.02209 0.01638 -0.0530 0.1966 1.0000
13.250 1.7901 0.02315 0.01749 -0.0516 0.1937 1.0000
13.500 1.7980 0.02431 0.01871 -0.0505 0.1905 1.0000
13.750 1.8081 0.02544 0.01992 -0.0497 0.1867 1.0000
14.000 1.8153 0.02687 0.02142 -0.0490 0.1833 1.0000
14.250 1.8175 0.02879 0.02337 -0.0483 0.1795 1.0000
14.500 1.8239 0.03047 0.02515 -0.0479 0.1758 1.0000
14.750 1.8275 0.03249 0.02724 -0.0476 0.1715 1.0000
15.000 1.8256 0.03510 0.02990 -0.0474 0.1675 1.0000
15.250 1.8252 0.03767 0.03254 -0.0474 0.1640 1.0000
15.500 1.8236 0.04045 0.03541 -0.0475 0.1593 1.0000
15.750 1.8149 0.04412 0.03913 -0.0479 0.1551 1.0000
16.000 1.8078 0.04768 0.04277 -0.0484 0.1513 1.0000
16.250 1.7977 0.05171 0.04688 -0.0492 0.1461 1.0000
16.500 1.7816 0.05666 0.05190 -0.0503 0.1422 1.0000
16.750 1.7703 0.06118 0.05650 -0.0515 0.1378 1.0000
17.000 1.7547 0.06644 0.06184 -0.0531 0.1332 1.0000
17.250 1.7337 0.07264 0.06811 -0.0551 0.1292 1.0000
17.500 1.7206 0.07788 0.07344 -0.0569 0.1248 1.0000
17.750 1.7012 0.08414 0.07977 -0.0592 0.1204 1.0000
18.000 1.6833 0.09036 0.08607 -0.0615 0.1172 1.0000
18.250 1.6683 0.09623 0.09203 -0.0639 0.1129 1.0000
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Polar data table (+)
Polar graphs
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