MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 100,000 Max Cl/Cd: 45.63 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh44-il-100000-n5.txt Download as CSV file: xf-mh44-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5490 0.09026 0.08551 -0.0085 1.0000 0.0185
-9.250 -0.5521 0.08502 0.08033 -0.0114 1.0000 0.0183
-9.000 -0.5577 0.07901 0.07438 -0.0153 1.0000 0.0180
-8.750 -0.5650 0.07209 0.06751 -0.0207 1.0000 0.0176
-8.500 -0.5801 0.06457 0.05995 -0.0272 1.0000 0.0173
-8.250 -0.5931 0.05939 0.05464 -0.0294 1.0000 0.0170
-8.000 -0.6016 0.05425 0.04929 -0.0306 1.0000 0.0168
-7.750 -0.6047 0.04953 0.04426 -0.0310 1.0000 0.0165
-7.500 -0.6031 0.04511 0.03947 -0.0306 1.0000 0.0163
-7.250 -0.5970 0.04117 0.03511 -0.0297 1.0000 0.0161
-7.000 -0.5875 0.03755 0.03104 -0.0285 1.0000 0.0160
-6.750 -0.5749 0.03441 0.02745 -0.0270 1.0000 0.0160
-6.500 -0.5600 0.03172 0.02434 -0.0255 1.0000 0.0160
-6.250 -0.5437 0.02941 0.02167 -0.0239 1.0000 0.0162
-6.000 -0.5272 0.02742 0.01937 -0.0221 1.0000 0.0166
-5.750 -0.5110 0.02567 0.01738 -0.0200 1.0000 0.0170
-5.500 -0.4954 0.02426 0.01573 -0.0179 1.0000 0.0177
-5.250 -0.4798 0.02319 0.01445 -0.0157 1.0000 0.0192
-5.000 -0.4665 0.02191 0.01311 -0.0134 1.0000 0.0212
-4.750 -0.4356 0.02067 0.01178 -0.0144 0.9921 0.0238
-4.500 -0.4017 0.01943 0.01035 -0.0157 0.9839 0.0269
-4.250 -0.3688 0.01826 0.00907 -0.0170 0.9752 0.0351
-4.000 -0.3349 0.01691 0.00774 -0.0184 0.9676 0.0614
-3.750 -0.3057 0.01537 0.00704 -0.0195 0.9585 0.2003
-3.500 -0.2746 0.01473 0.00673 -0.0205 0.9491 0.2947
-3.250 -0.2431 0.01419 0.00650 -0.0213 0.9404 0.3839
-3.000 -0.2132 0.01379 0.00622 -0.0216 0.9304 0.4462
-2.750 -0.1843 0.01346 0.00600 -0.0216 0.9200 0.5037
-2.500 -0.1551 0.01314 0.00580 -0.0215 0.9100 0.5650
-2.250 -0.1253 0.01282 0.00563 -0.0213 0.9005 0.6323
-2.000 -0.0965 0.01253 0.00549 -0.0208 0.8894 0.7051
-1.750 -0.0610 0.01229 0.00541 -0.0214 0.8796 0.7868
-1.500 -0.0095 0.01216 0.00530 -0.0252 0.8720 0.8627
-1.250 0.0399 0.01213 0.00517 -0.0289 0.8612 0.9139
-1.000 0.0858 0.01213 0.00504 -0.0321 0.8496 0.9474
-0.750 0.1268 0.01215 0.00492 -0.0345 0.8368 0.9752
-0.500 0.1708 0.01211 0.00474 -0.0377 0.8236 0.9982
-0.250 0.1947 0.01210 0.00461 -0.0369 0.8083 1.0000
0.000 0.2167 0.01211 0.00452 -0.0356 0.7925 1.0000
0.250 0.2389 0.01212 0.00442 -0.0344 0.7765 1.0000
0.500 0.2613 0.01214 0.00434 -0.0331 0.7602 1.0000
0.750 0.2839 0.01216 0.00428 -0.0319 0.7433 1.0000
1.000 0.3070 0.01220 0.00425 -0.0307 0.7252 1.0000
1.250 0.3301 0.01225 0.00422 -0.0296 0.7071 1.0000
1.500 0.3533 0.01231 0.00418 -0.0284 0.6892 1.0000
1.750 0.3769 0.01240 0.00419 -0.0273 0.6698 1.0000
2.000 0.4005 0.01251 0.00421 -0.0263 0.6502 1.0000
2.250 0.4243 0.01263 0.00427 -0.0252 0.6306 1.0000
2.500 0.4482 0.01278 0.00435 -0.0243 0.6096 1.0000
2.750 0.4721 0.01294 0.00443 -0.0233 0.5894 1.0000
3.000 0.4962 0.01312 0.00456 -0.0225 0.5677 1.0000
3.250 0.5202 0.01333 0.00472 -0.0216 0.5469 1.0000
3.500 0.5443 0.01355 0.00490 -0.0207 0.5249 1.0000
3.750 0.5682 0.01380 0.00508 -0.0199 0.5038 1.0000
4.000 0.5922 0.01405 0.00531 -0.0191 0.4814 1.0000
4.250 0.6159 0.01434 0.00558 -0.0183 0.4593 1.0000
4.500 0.6396 0.01464 0.00585 -0.0175 0.4364 1.0000
4.750 0.6632 0.01497 0.00616 -0.0167 0.4132 1.0000
5.000 0.6865 0.01532 0.00647 -0.0158 0.3899 1.0000
5.250 0.7097 0.01570 0.00686 -0.0150 0.3655 1.0000
5.500 0.7327 0.01610 0.00726 -0.0142 0.3412 1.0000
5.750 0.7552 0.01655 0.00768 -0.0134 0.3164 1.0000
6.000 0.7774 0.01704 0.00813 -0.0125 0.2920 1.0000
6.250 0.7995 0.01756 0.00864 -0.0117 0.2670 1.0000
6.500 0.8212 0.01812 0.00923 -0.0108 0.2431 1.0000
6.750 0.8423 0.01874 0.00983 -0.0099 0.2206 1.0000
7.000 0.8632 0.01940 0.01049 -0.0090 0.1983 1.0000
7.250 0.8836 0.02011 0.01119 -0.0080 0.1777 1.0000
7.500 0.9035 0.02086 0.01196 -0.0070 0.1578 1.0000
7.750 0.9224 0.02171 0.01279 -0.0060 0.1403 1.0000
8.000 0.9414 0.02255 0.01372 -0.0049 0.1232 1.0000
8.250 0.9595 0.02347 0.01469 -0.0038 0.1076 1.0000
8.500 0.9766 0.02447 0.01573 -0.0026 0.0939 1.0000
8.750 0.9927 0.02555 0.01686 -0.0012 0.0821 1.0000
9.000 1.0071 0.02676 0.01810 0.0002 0.0725 1.0000
9.250 1.0207 0.02798 0.01937 0.0016 0.0634 1.0000
9.500 1.0340 0.02927 0.02082 0.0033 0.0560 1.0000
9.750 1.0432 0.03078 0.02232 0.0050 0.0505 1.0000
10.000 1.0549 0.03214 0.02395 0.0067 0.0449 1.0000
10.250 1.0621 0.03370 0.02559 0.0086 0.0413 1.0000
10.500 1.0657 0.03555 0.02752 0.0109 0.0389 1.0000
10.750 1.0711 0.03730 0.02951 0.0130 0.0360 1.0000
11.000 1.0744 0.03907 0.03143 0.0147 0.0334 1.0000
11.250 1.0750 0.04102 0.03347 0.0161 0.0313 1.0000
11.500 1.0742 0.04361 0.03609 0.0174 0.0297 1.0000
11.750 1.0754 0.04622 0.03901 0.0184 0.0285 1.0000
12.000 1.0739 0.04918 0.04224 0.0191 0.0274 1.0000
12.250 1.0697 0.05238 0.04568 0.0192 0.0261 1.0000
12.500 1.0642 0.05578 0.04928 0.0188 0.0251 1.0000
12.750 1.0570 0.05950 0.05316 0.0179 0.0240 1.0000
13.000 1.0493 0.06358 0.05741 0.0165 0.0234 1.0000
13.250 1.0408 0.06782 0.06174 0.0146 0.0225 1.0000
13.500 1.0298 0.07286 0.06692 0.0123 0.0221 1.0000
13.750 1.0163 0.07862 0.07285 0.0094 0.0218 1.0000
14.000 1.0014 0.08495 0.07935 0.0060 0.0217 1.0000
14.250 0.9838 0.09215 0.08673 0.0018 0.0217 1.0000
14.500 0.9621 0.10093 0.09572 -0.0036 0.0220 1.0000
14.750 0.8710 0.12984 0.12499 -0.0207 0.0273 1.0000
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Polar data table (+)
Polar graphs
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