AG09 (ag09-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 100,000 Max Cl/Cd: 44.27 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag09-il-100000.txt Download as CSV file: xf-ag09-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG09
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5869 0.11184 0.10699 0.0239 1.0000 0.0656
-8.250 -0.5888 0.10973 0.10496 0.0184 1.0000 0.0669
-8.000 -0.5880 0.10723 0.10252 0.0102 1.0000 0.0674
-7.750 -0.5808 0.10220 0.09754 0.0054 1.0000 0.0680
-7.500 -0.5683 0.09677 0.09209 0.0171 1.0000 0.0722
-7.250 -0.5610 0.09324 0.08858 0.0147 1.0000 0.0757
-7.000 -0.5502 0.08951 0.08487 0.0058 1.0000 0.0797
-6.750 -0.5320 0.08488 0.08013 -0.0089 1.0000 0.0814
-6.500 -0.5270 0.08009 0.07543 -0.0013 1.0000 0.0836
-6.250 -0.5141 0.07637 0.07172 -0.0016 1.0000 0.0871
-6.000 -0.4806 0.07228 0.06722 -0.0191 1.0000 0.0950
-5.750 -0.4738 0.06686 0.06202 -0.0146 1.0000 0.0968
-5.500 -0.4590 0.06332 0.05850 -0.0140 1.0000 0.1008
-5.250 -0.4297 0.05851 0.05340 -0.0221 1.0000 0.1101
-5.000 -0.4145 0.05498 0.04994 -0.0208 1.0000 0.1143
-4.750 -0.3872 0.05077 0.04549 -0.0253 1.0000 0.1251
-4.500 -0.3630 0.04735 0.04190 -0.0273 1.0000 0.1388
-4.250 -0.3416 0.04416 0.03864 -0.0278 1.0000 0.1541
-4.000 -0.3178 0.04098 0.03537 -0.0287 1.0000 0.1695
-3.750 -0.2599 0.03083 0.02346 -0.0344 1.0000 0.0804
-3.500 -0.2328 0.02682 0.01920 -0.0347 1.0000 0.0758
-3.250 -0.2031 0.02391 0.01572 -0.0347 1.0000 0.0777
-3.000 -0.1730 0.02170 0.01283 -0.0343 1.0000 0.0808
-2.750 -0.1458 0.01936 0.01035 -0.0341 1.0000 0.0862
-2.500 -0.1183 0.01800 0.00880 -0.0337 1.0000 0.0992
-2.250 -0.0909 0.01662 0.00727 -0.0332 1.0000 0.1126
-2.000 -0.0642 0.01561 0.00625 -0.0327 1.0000 0.1335
-1.750 -0.0380 0.01463 0.00538 -0.0322 1.0000 0.1601
-1.500 -0.0120 0.01370 0.00458 -0.0316 1.0000 0.1929
-1.250 0.0133 0.01276 0.00396 -0.0311 1.0000 0.2468
-1.000 0.0391 0.00974 0.00333 -0.0296 1.0000 1.0000
-0.750 0.0652 0.00976 0.00301 -0.0291 1.0000 1.0000
-0.500 0.0908 0.00979 0.00284 -0.0285 1.0000 1.0000
-0.250 0.1161 0.00984 0.00275 -0.0280 1.0000 1.0000
0.000 0.1412 0.00990 0.00270 -0.0276 1.0000 1.0000
0.250 0.1662 0.00998 0.00271 -0.0271 1.0000 1.0000
0.500 0.1910 0.01008 0.00277 -0.0268 1.0000 1.0000
0.750 0.2156 0.01021 0.00289 -0.0264 1.0000 1.0000
1.000 0.2399 0.01039 0.00307 -0.0261 1.0000 1.0000
1.250 0.2640 0.01062 0.00333 -0.0260 1.0000 1.0000
1.500 0.2878 0.01093 0.00368 -0.0261 1.0000 1.0000
1.750 0.3562 0.01100 0.00390 -0.0345 0.9701 1.0000
2.000 0.4111 0.01094 0.00395 -0.0392 0.9280 1.0000
2.250 0.4486 0.01093 0.00396 -0.0398 0.8730 1.0000
2.500 0.4736 0.01105 0.00399 -0.0376 0.8106 1.0000
2.750 0.4953 0.01131 0.00409 -0.0349 0.7443 1.0000
3.000 0.5173 0.01170 0.00422 -0.0326 0.6746 1.0000
3.250 0.5401 0.01220 0.00442 -0.0308 0.6058 1.0000
3.500 0.5637 0.01277 0.00470 -0.0294 0.5421 1.0000
3.750 0.5878 0.01339 0.00510 -0.0283 0.4854 1.0000
4.000 0.6124 0.01405 0.00552 -0.0275 0.4360 1.0000
4.250 0.6373 0.01474 0.00601 -0.0268 0.3917 1.0000
4.500 0.6623 0.01543 0.00656 -0.0262 0.3512 1.0000
4.750 0.6875 0.01610 0.00715 -0.0256 0.3122 1.0000
5.000 0.7126 0.01682 0.00784 -0.0251 0.2751 1.0000
5.250 0.7372 0.01759 0.00847 -0.0245 0.2386 1.0000
5.500 0.7616 0.01837 0.00920 -0.0240 0.1984 1.0000
5.750 0.7856 0.01936 0.01011 -0.0235 0.1538 1.0000
6.000 0.8091 0.02074 0.01139 -0.0228 0.1108 1.0000
6.250 0.8325 0.02256 0.01319 -0.0220 0.0836 1.0000
6.500 0.8562 0.02447 0.01511 -0.0212 0.0681 1.0000
6.750 0.8802 0.02693 0.01776 -0.0203 0.0595 1.0000
7.000 0.9023 0.02991 0.02072 -0.0197 0.0526 1.0000
7.250 0.9257 0.03282 0.02428 -0.0186 0.0506 1.0000
7.500 0.9458 0.03669 0.02881 -0.0175 0.0496 1.0000
7.750 0.9623 0.04104 0.03387 -0.0166 0.0488 1.0000
8.000 0.9748 0.04570 0.03918 -0.0160 0.0477 1.0000
8.250 0.9820 0.05114 0.04520 -0.0157 0.0475 1.0000
8.500 0.9830 0.05744 0.05200 -0.0161 0.0486 1.0000
8.750 0.9808 0.06367 0.05855 -0.0169 0.0502 1.0000
9.000 0.9793 0.06956 0.06457 -0.0176 0.0517 1.0000
9.250 0.9283 0.08652 0.08205 -0.0307 0.0675 1.0000
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Polar data table (+)
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