MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 50,000 Max Cl/Cd: 26.68 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh83-il-50000-n5.txt Download as CSV file: xf-mh83-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2398 0.11669 0.11103 -0.0138 1.0000 0.1086
-9.000 -0.2420 0.11486 0.10934 -0.0179 1.0000 0.1097
-8.750 -0.2402 0.11242 0.10704 -0.0217 1.0000 0.1101
-8.500 -0.2233 0.10794 0.10264 -0.0246 0.9475 0.1108
-8.250 -0.1898 0.10260 0.09720 -0.0255 0.9087 0.1139
-7.750 -0.1806 0.09288 0.08728 -0.0342 0.8545 0.0722
-7.250 -0.1753 0.08571 0.08000 -0.0375 0.8142 0.0628
-7.000 -0.1690 0.08302 0.07728 -0.0376 0.7966 0.0616
-6.750 -0.1638 0.07999 0.07422 -0.0390 0.7806 0.0600
-6.250 -0.1565 0.06978 0.06384 -0.0503 0.7558 0.0547
-6.000 -0.1451 0.06623 0.06022 -0.0528 0.7418 0.0540
-5.750 -0.1329 0.06204 0.05593 -0.0563 0.7292 0.0532
-5.500 -0.1196 0.05733 0.05100 -0.0603 0.7185 0.0524
-5.250 -0.1034 0.05250 0.04590 -0.0644 0.7068 0.0517
-5.000 -0.0843 0.04778 0.04078 -0.0681 0.6957 0.0512
-4.750 -0.0629 0.04366 0.03614 -0.0706 0.6856 0.0513
-4.500 -0.0385 0.04025 0.03220 -0.0725 0.6734 0.0527
-4.250 -0.0127 0.03711 0.02834 -0.0737 0.6628 0.0546
-4.000 0.0126 0.03520 0.02611 -0.0738 0.6514 0.0566
-3.750 0.0389 0.03353 0.02413 -0.0739 0.6396 0.0585
-3.500 0.0657 0.03181 0.02197 -0.0736 0.6297 0.0606
-3.250 0.0934 0.03032 0.02005 -0.0733 0.6181 0.0638
-3.000 0.1197 0.02944 0.01908 -0.0729 0.6073 0.0689
-2.750 0.1464 0.02842 0.01780 -0.0722 0.5975 0.0752
-2.500 0.1737 0.02762 0.01682 -0.0718 0.5864 0.0844
-2.250 0.2002 0.02684 0.01592 -0.0711 0.5779 0.0988
-2.000 0.2280 0.02620 0.01528 -0.0711 0.5668 0.1261
-1.750 0.2555 0.02553 0.01473 -0.0710 0.5579 0.1755
-1.500 0.2828 0.02509 0.01446 -0.0709 0.5479 0.2438
-1.250 0.3096 0.02469 0.01424 -0.0706 0.5392 0.3172
-1.000 0.3355 0.02434 0.01411 -0.0701 0.5302 0.3962
-0.750 0.3601 0.02400 0.01402 -0.0691 0.5222 0.4904
-0.500 0.3816 0.02363 0.01404 -0.0673 0.5137 0.6120
-0.250 0.4016 0.02297 0.01380 -0.0640 0.5073 0.8139
0.000 0.4383 0.02315 0.01374 -0.0657 0.4975 1.0000
0.500 0.4939 0.02395 0.01387 -0.0658 0.4823 1.0000
0.750 0.5217 0.02425 0.01382 -0.0655 0.4761 1.0000
1.000 0.5485 0.02482 0.01419 -0.0656 0.4686 1.0000
1.250 0.5755 0.02527 0.01441 -0.0655 0.4618 1.0000
1.500 0.6030 0.02559 0.01443 -0.0652 0.4567 1.0000
1.750 0.6284 0.02636 0.01514 -0.0654 0.4488 1.0000
2.000 0.6553 0.02679 0.01536 -0.0651 0.4433 1.0000
2.250 0.6817 0.02734 0.01573 -0.0650 0.4381 1.0000
2.500 0.7063 0.02817 0.01652 -0.0650 0.4313 1.0000
2.750 0.7329 0.02863 0.01681 -0.0648 0.4263 1.0000
3.000 0.7587 0.02922 0.01726 -0.0646 0.4215 1.0000
3.250 0.7816 0.03028 0.01834 -0.0647 0.4151 1.0000
3.500 0.8070 0.03089 0.01886 -0.0644 0.4105 1.0000
3.750 0.8343 0.03127 0.01905 -0.0640 0.4071 1.0000
4.000 0.8536 0.03275 0.02065 -0.0642 0.4005 1.0000
4.250 0.8767 0.03365 0.02153 -0.0640 0.3956 1.0000
4.500 0.9027 0.03415 0.02191 -0.0636 0.3920 1.0000
4.750 0.9245 0.03525 0.02301 -0.0635 0.3878 1.0000
5.000 0.9399 0.03709 0.02499 -0.0635 0.3820 1.0000
5.250 0.9621 0.03802 0.02591 -0.0632 0.3779 1.0000
5.500 0.9884 0.03847 0.02625 -0.0628 0.3748 1.0000
5.750 0.9994 0.04069 0.02862 -0.0627 0.3696 1.0000
6.000 1.0076 0.04312 0.03119 -0.0626 0.3642 1.0000
6.250 1.0274 0.04426 0.03235 -0.0622 0.3607 1.0000
6.500 1.0539 0.04466 0.03267 -0.0617 0.3582 1.0000
6.750 1.0204 0.05127 0.03963 -0.0620 0.3498 1.0000
7.000 1.0235 0.05398 0.04238 -0.0618 0.3452 1.0000
7.250 1.0455 0.05473 0.04312 -0.0612 0.3427 1.0000
7.500 1.0692 0.05539 0.04376 -0.0606 0.3405 1.0000
8.000 0.9059 0.08309 0.07182 -0.0703 0.3163 1.0000
8.250 0.9145 0.08567 0.07441 -0.0705 0.3127 1.0000
8.500 0.9336 0.08681 0.07555 -0.0700 0.3103 1.0000
9.500 0.9375 0.10188 0.09077 -0.0735 0.2939 1.0000
9.750 0.9094 0.10973 0.09867 -0.0768 0.2869 1.0000
10.000 0.9125 0.11329 0.10230 -0.0777 0.2830 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 83 13.29% (mh83-il)