AH 80-136 (ah80136-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 200,000 Max Cl/Cd: 71.21 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80136-il-200000-n5.txt Download as CSV file: xf-ah80136-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-136
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5467 0.08972 0.08575 0.0175 0.6332 0.0156
-8.250 -0.5527 0.08293 0.07897 0.0112 0.6318 0.0153
-8.000 -0.5650 0.07530 0.07129 0.0037 0.6306 0.0149
-7.750 -0.5739 0.06759 0.06342 -0.0010 0.6296 0.0144
-7.500 -0.5812 0.05924 0.05477 -0.0038 0.6286 0.0140
-7.250 -0.5824 0.05166 0.04679 -0.0047 0.6276 0.0138
-7.000 -0.5751 0.04613 0.04088 -0.0047 0.6259 0.0138
-6.750 -0.5623 0.04195 0.03635 -0.0043 0.6241 0.0140
-6.500 -0.5462 0.03845 0.03246 -0.0039 0.6222 0.0143
-6.250 -0.5265 0.03606 0.02976 -0.0035 0.6202 0.0151
-6.000 -0.5065 0.03303 0.02628 -0.0028 0.6184 0.0162
-5.750 -0.4854 0.02980 0.02248 -0.0019 0.6166 0.0168
-5.500 -0.4622 0.02711 0.01927 -0.0010 0.6150 0.0172
-5.250 -0.4372 0.02510 0.01679 -0.0004 0.6135 0.0177
-5.000 -0.4115 0.02342 0.01493 -0.0002 0.6117 0.0184
-4.750 -0.3847 0.02244 0.01384 -0.0003 0.6095 0.0193
-4.500 -0.3575 0.02152 0.01279 -0.0002 0.6075 0.0204
-4.250 -0.3300 0.02082 0.01194 -0.0002 0.6054 0.0225
-4.000 -0.3027 0.01997 0.01093 0.0000 0.6034 0.0243
-3.750 -0.2764 0.01908 0.01001 0.0002 0.6017 0.0260
-3.500 -0.2496 0.01846 0.00931 0.0004 0.6001 0.0281
-3.250 -0.2222 0.01805 0.00878 0.0005 0.5988 0.0312
-3.000 -0.1953 0.01731 0.00805 0.0005 0.5968 0.0340
-2.750 -0.1677 0.01684 0.00757 0.0003 0.5945 0.0372
-2.500 -0.1397 0.01652 0.00719 0.0002 0.5922 0.0417
-2.250 -0.1123 0.01606 0.00667 0.0002 0.5901 0.0464
-2.000 -0.0844 0.01576 0.00631 0.0001 0.5883 0.0533
-1.750 -0.0567 0.01542 0.00595 0.0001 0.5868 0.0646
-1.500 -0.0299 0.01491 0.00564 0.0001 0.5854 0.1179
-1.250 -0.0077 0.01365 0.00533 0.0004 0.5841 0.3674
-1.000 0.0148 0.01279 0.00535 0.0010 0.5815 0.5873
-0.750 0.0351 0.01213 0.00549 0.0032 0.5792 0.7745
-0.500 0.0699 0.01214 0.00577 0.0030 0.5771 0.9068
-0.250 0.1193 0.01238 0.00594 -0.0005 0.5751 0.9645
0.000 0.1636 0.01246 0.00588 -0.0038 0.5731 0.9771
0.250 0.2023 0.01248 0.00577 -0.0061 0.5714 0.9827
0.500 0.2390 0.01252 0.00568 -0.0081 0.5700 0.9887
0.750 0.2770 0.01262 0.00574 -0.0105 0.5676 0.9941
1.000 0.3154 0.01271 0.00580 -0.0131 0.5647 0.9984
1.250 0.3460 0.01278 0.00582 -0.0140 0.5622 1.0000
1.500 0.3721 0.01283 0.00582 -0.0140 0.5601 1.0000
1.750 0.3981 0.01287 0.00580 -0.0138 0.5581 1.0000
2.000 0.4238 0.01290 0.00575 -0.0136 0.5564 1.0000
2.250 0.4500 0.01298 0.00580 -0.0135 0.5543 1.0000
2.500 0.4773 0.01315 0.00602 -0.0138 0.5506 1.0000
2.750 0.5038 0.01325 0.00611 -0.0139 0.5475 1.0000
3.000 0.5300 0.01328 0.00613 -0.0137 0.5447 1.0000
3.250 0.5559 0.01329 0.00608 -0.0134 0.5424 1.0000
3.500 0.5822 0.01335 0.00612 -0.0133 0.5399 1.0000
3.750 0.6095 0.01356 0.00643 -0.0137 0.5357 1.0000
4.000 0.6362 0.01366 0.00656 -0.0137 0.5324 1.0000
4.250 0.6626 0.01371 0.00660 -0.0136 0.5297 1.0000
4.500 0.6888 0.01373 0.00660 -0.0133 0.5275 1.0000
4.750 0.7159 0.01393 0.00690 -0.0136 0.5236 1.0000
5.000 0.7429 0.01411 0.00715 -0.0138 0.5195 1.0000
5.250 0.7696 0.01417 0.00725 -0.0138 0.5162 1.0000
5.500 0.7961 0.01418 0.00726 -0.0136 0.5135 1.0000
5.750 0.8233 0.01440 0.00761 -0.0139 0.5090 1.0000
6.000 0.8503 0.01456 0.00786 -0.0142 0.5043 1.0000
6.250 0.8772 0.01459 0.00793 -0.0141 0.5006 1.0000
6.500 0.9043 0.01470 0.00814 -0.0143 0.4961 1.0000
6.750 0.9314 0.01490 0.00846 -0.0146 0.4900 1.0000
7.000 0.9585 0.01485 0.00845 -0.0145 0.4852 1.0000
7.250 0.9856 0.01510 0.00886 -0.0150 0.4774 1.0000
7.500 1.0127 0.01511 0.00893 -0.0150 0.4714 1.0000
7.750 1.0397 0.01531 0.00927 -0.0154 0.4613 1.0000
8.000 1.0665 0.01536 0.00939 -0.0155 0.4477 1.0000
8.250 1.0930 0.01543 0.00948 -0.0157 0.4296 1.0000
8.500 1.1187 0.01571 0.00979 -0.0160 0.4068 1.0000
8.750 1.1428 0.01618 0.01018 -0.0163 0.3778 1.0000
9.000 1.1639 0.01706 0.01090 -0.0167 0.3417 1.0000
9.250 1.1814 0.01841 0.01209 -0.0174 0.3041 1.0000
9.500 1.1930 0.02051 0.01402 -0.0188 0.2615 1.0000
9.750 1.1954 0.02358 0.01688 -0.0208 0.2182 1.0000
10.000 1.1875 0.02657 0.01969 -0.0205 0.1830 1.0000
10.250 1.1789 0.02969 0.02258 -0.0200 0.1486 1.0000
10.500 1.1701 0.03281 0.02550 -0.0194 0.1145 1.0000
10.750 1.1622 0.03587 0.02836 -0.0187 0.0859 1.0000
11.000 1.1580 0.03862 0.03100 -0.0182 0.0678 1.0000
11.250 1.1571 0.04112 0.03346 -0.0177 0.0559 1.0000
11.500 1.1568 0.04360 0.03592 -0.0172 0.0469 1.0000
11.750 1.1589 0.04590 0.03825 -0.0169 0.0398 1.0000
12.000 1.1610 0.04833 0.04072 -0.0167 0.0343 1.0000
12.250 1.1623 0.05090 0.04332 -0.0165 0.0293 1.0000
12.500 1.1645 0.05344 0.04593 -0.0164 0.0255 1.0000
12.750 1.1658 0.05613 0.04865 -0.0164 0.0222 1.0000
13.000 1.1661 0.05899 0.05159 -0.0165 0.0199 1.0000
13.250 1.1677 0.06177 0.05448 -0.0166 0.0182 1.0000
13.500 1.1685 0.06469 0.05748 -0.0167 0.0168 1.0000
13.750 1.1672 0.06790 0.06075 -0.0170 0.0157 1.0000
14.000 1.1656 0.07121 0.06415 -0.0173 0.0147 1.0000
14.250 1.1670 0.07418 0.06723 -0.0176 0.0138 1.0000
14.500 1.1682 0.07723 0.07039 -0.0180 0.0129 1.0000
14.750 1.1689 0.08037 0.07361 -0.0185 0.0122 1.0000
15.000 1.1684 0.08370 0.07702 -0.0190 0.0116 1.0000
15.250 1.1654 0.08741 0.08079 -0.0197 0.0111 1.0000
15.500 1.1639 0.09092 0.08439 -0.0202 0.0107 1.0000
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Polar data table (+)
Polar graphs
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