MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 200,000 Max Cl/Cd: 67.12 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh83-il-200000-n5.txt Download as CSV file: xf-mh83-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2745 0.11327 0.10937 -0.0043 0.7339 0.0308
-9.500 -0.2735 0.10958 0.10564 -0.0071 0.7219 0.0310
-9.250 -0.2702 0.10589 0.10191 -0.0094 0.7096 0.0311
-9.000 -0.2666 0.10218 0.09816 -0.0115 0.6982 0.0311
-8.750 -0.2618 0.09855 0.09449 -0.0134 0.6865 0.0311
-8.250 -0.2510 0.08932 0.08517 -0.0158 0.6663 0.0230
-8.000 -0.2388 0.08756 0.08336 -0.0158 0.6530 0.0224
-7.750 -0.2327 0.08450 0.08028 -0.0170 0.6423 0.0218
-7.250 -0.2477 0.07292 0.06870 -0.0238 0.6294 0.0193
-7.000 -0.2461 0.06902 0.06479 -0.0269 0.6204 0.0193
-6.750 -0.2470 0.06167 0.05740 -0.0348 0.6146 0.0194
-6.500 -0.2410 0.05259 0.04823 -0.0449 0.6087 0.0193
-6.250 -0.2311 0.04173 0.03699 -0.0551 0.6029 0.0190
-5.750 -0.1931 0.02914 0.02303 -0.0636 0.5870 0.0185
-5.500 -0.1681 0.02602 0.01929 -0.0647 0.5777 0.0186
-5.250 -0.1414 0.02378 0.01657 -0.0652 0.5674 0.0188
-5.000 -0.1140 0.02208 0.01443 -0.0654 0.5579 0.0190
-4.750 -0.0862 0.02076 0.01274 -0.0654 0.5476 0.0193
-4.500 -0.0584 0.01969 0.01147 -0.0654 0.5380 0.0197
-4.250 -0.0306 0.01889 0.01052 -0.0654 0.5282 0.0201
-4.000 -0.0024 0.01818 0.00968 -0.0654 0.5185 0.0207
-3.750 0.0258 0.01760 0.00893 -0.0653 0.5093 0.0216
-3.500 0.0544 0.01707 0.00823 -0.0652 0.5001 0.0229
-3.000 0.1110 0.01608 0.00712 -0.0651 0.4824 0.0250
-2.750 0.1396 0.01569 0.00658 -0.0650 0.4740 0.0262
-2.500 0.1684 0.01530 0.00613 -0.0650 0.4651 0.0276
-2.000 0.2260 0.01473 0.00540 -0.0649 0.4497 0.0329
-1.750 0.2547 0.01448 0.00509 -0.0649 0.4421 0.0402
-1.500 0.2836 0.01414 0.00482 -0.0649 0.4345 0.0603
-1.250 0.3122 0.01391 0.00465 -0.0649 0.4268 0.0975
-1.000 0.3407 0.01372 0.00455 -0.0650 0.4198 0.1374
-0.750 0.3690 0.01346 0.00454 -0.0651 0.4128 0.2118
-0.250 0.4257 0.01319 0.00452 -0.0651 0.4004 0.3276
0.000 0.4539 0.01310 0.00452 -0.0651 0.3941 0.3832
0.250 0.4817 0.01300 0.00454 -0.0650 0.3884 0.4497
0.500 0.5091 0.01285 0.00461 -0.0647 0.3821 0.5333
0.750 0.5351 0.01267 0.00468 -0.0641 0.3766 0.6371
1.000 0.5579 0.01241 0.00473 -0.0625 0.3721 0.7701
1.250 0.5908 0.01217 0.00469 -0.0629 0.3667 1.0000
1.500 0.6193 0.01235 0.00474 -0.0629 0.3617 1.0000
2.000 0.6762 0.01275 0.00489 -0.0628 0.3523 1.0000
2.250 0.7045 0.01294 0.00500 -0.0628 0.3474 1.0000
2.500 0.7326 0.01316 0.00510 -0.0628 0.3433 1.0000
2.750 0.7606 0.01340 0.00523 -0.0627 0.3397 1.0000
3.000 0.7888 0.01361 0.00540 -0.0627 0.3357 1.0000
3.250 0.8168 0.01383 0.00557 -0.0627 0.3317 1.0000
3.500 0.8445 0.01407 0.00572 -0.0626 0.3279 1.0000
3.750 0.8719 0.01436 0.00590 -0.0626 0.3245 1.0000
4.000 0.8998 0.01458 0.00613 -0.0625 0.3208 1.0000
4.250 0.9274 0.01483 0.00635 -0.0625 0.3173 1.0000
4.500 0.9548 0.01510 0.00658 -0.0624 0.3141 1.0000
4.750 0.9819 0.01539 0.00681 -0.0623 0.3111 1.0000
5.000 1.0089 0.01570 0.00705 -0.0622 0.3082 1.0000
5.250 1.0362 0.01597 0.00735 -0.0622 0.3048 1.0000
5.500 1.0632 0.01625 0.00765 -0.0621 0.3016 1.0000
5.750 1.0900 0.01655 0.00794 -0.0620 0.2987 1.0000
6.000 1.1165 0.01687 0.00823 -0.0619 0.2961 1.0000
6.250 1.1428 0.01724 0.00854 -0.0618 0.2935 1.0000
6.500 1.1691 0.01756 0.00891 -0.0616 0.2907 1.0000
6.750 1.1954 0.01789 0.00928 -0.0615 0.2876 1.0000
7.000 1.2214 0.01823 0.00965 -0.0614 0.2848 1.0000
7.250 1.2471 0.01859 0.01003 -0.0612 0.2823 1.0000
7.500 1.2725 0.01896 0.01039 -0.0611 0.2799 1.0000
7.750 1.2977 0.01939 0.01077 -0.0608 0.2775 1.0000
8.000 1.3228 0.01977 0.01127 -0.0607 0.2747 1.0000
8.250 1.3476 0.02017 0.01175 -0.0604 0.2720 1.0000
8.500 1.3722 0.02058 0.01222 -0.0602 0.2695 1.0000
8.750 1.3963 0.02100 0.01269 -0.0599 0.2670 1.0000
9.000 1.4203 0.02143 0.01312 -0.0596 0.2646 1.0000
9.250 1.4440 0.02192 0.01358 -0.0593 0.2622 1.0000
9.500 1.4669 0.02241 0.01422 -0.0590 0.2598 1.0000
9.750 1.4893 0.02292 0.01484 -0.0586 0.2573 1.0000
10.000 1.5113 0.02342 0.01543 -0.0581 0.2546 1.0000
10.250 1.5328 0.02392 0.01600 -0.0576 0.2520 1.0000
10.500 1.5540 0.02444 0.01654 -0.0571 0.2497 1.0000
10.750 1.5755 0.02501 0.01710 -0.0566 0.2476 1.0000
11.000 1.5940 0.02566 0.01793 -0.0559 0.2451 1.0000
11.250 1.6114 0.02633 0.01874 -0.0551 0.2423 1.0000
11.500 1.6281 0.02700 0.01952 -0.0542 0.2396 1.0000
11.750 1.6440 0.02768 0.02028 -0.0533 0.2372 1.0000
12.000 1.6582 0.02835 0.02099 -0.0521 0.2349 1.0000
12.250 1.6720 0.02909 0.02174 -0.0509 0.2327 1.0000
12.500 1.6772 0.03020 0.02304 -0.0492 0.2302 1.0000
12.750 1.6833 0.03140 0.02440 -0.0479 0.2275 1.0000
13.000 1.6893 0.03268 0.02580 -0.0468 0.2248 1.0000
13.250 1.6965 0.03398 0.02718 -0.0460 0.2222 1.0000
13.500 1.7055 0.03521 0.02844 -0.0453 0.2199 1.0000
13.750 1.7098 0.03692 0.03027 -0.0447 0.2174 1.0000
14.000 1.7085 0.03922 0.03277 -0.0444 0.2143 1.0000
14.250 1.7083 0.04153 0.03523 -0.0442 0.2114 1.0000
14.500 1.7095 0.04379 0.03758 -0.0442 0.2086 1.0000
14.750 1.7147 0.04567 0.03949 -0.0441 0.2060 1.0000
15.000 1.7102 0.04873 0.04270 -0.0444 0.2032 1.0000
15.250 1.6991 0.05271 0.04688 -0.0453 0.1999 1.0000
15.500 1.6903 0.05654 0.05085 -0.0462 0.1967 1.0000
15.750 1.6881 0.05959 0.05396 -0.0468 0.1937 1.0000
16.000 1.6875 0.06252 0.05694 -0.0474 0.1910 1.0000
16.250 1.6597 0.06950 0.06417 -0.0500 0.1873 1.0000
16.500 1.6385 0.07582 0.07064 -0.0525 0.1834 1.0000
16.750 1.6377 0.07914 0.07400 -0.0536 0.1802 1.0000
17.000 1.6204 0.08518 0.08016 -0.0560 0.1767 1.0000
17.250 1.5672 0.09739 0.09260 -0.0615 0.1715 1.0000
17.500 1.5672 0.10091 0.09617 -0.0629 0.1680 1.0000
17.750 1.5590 0.10579 0.10111 -0.0650 0.1645 1.0000
18.000 1.4832 0.12313 0.11866 -0.0736 0.1570 1.0000
18.250 1.5095 0.12199 0.11752 -0.0728 0.1548 1.0000
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Polar data table (+)
Polar graphs
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