AG37 (ag37-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 50,000 Max Cl/Cd: 32.88 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag37-il-50000.txt Download as CSV file: xf-ag37-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG37
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5251 0.12185 0.11490 0.0062 1.0000 0.1788
-10.250 -0.5092 0.11663 0.10965 0.0073 1.0000 0.1862
-10.000 -0.5194 0.11520 0.10833 0.0044 1.0000 0.1935
-9.750 -0.5027 0.11021 0.10333 0.0059 1.0000 0.2043
-9.500 -0.5026 0.10699 0.10019 0.0048 1.0000 0.2121
-9.250 -0.5089 0.10508 0.09838 0.0030 1.0000 0.2224
-9.000 -0.4955 0.10071 0.09403 0.0042 1.0000 0.2350
-8.750 -0.4881 0.09698 0.09035 0.0045 1.0000 0.2459
-8.250 -0.4884 0.09090 0.08444 0.0035 1.0000 0.2700
-8.000 -0.4822 0.08750 0.08110 0.0037 1.0000 0.2853
-7.750 -0.4740 0.08411 0.07777 0.0045 1.0000 0.3028
-7.500 -0.4769 0.08169 0.07543 0.0029 1.0000 0.3246
-7.250 -0.4634 0.07774 0.07150 0.0057 1.0000 0.3445
-7.000 -0.4603 0.07488 0.06871 0.0064 1.0000 0.3714
-6.750 -0.4476 0.07161 0.06549 0.0104 1.0000 0.4038
-6.500 -0.4402 0.06884 0.06280 0.0144 1.0000 0.4460
-6.250 -0.4259 0.06581 0.05981 0.0198 1.0000 0.4931
-5.500 -0.3179 0.03920 0.03075 -0.0385 1.0000 0.1427
-5.250 -0.2899 0.03534 0.02622 -0.0390 1.0000 0.1315
-5.000 -0.2626 0.03205 0.02232 -0.0389 1.0000 0.1261
-4.750 -0.2367 0.02968 0.01958 -0.0384 1.0000 0.1293
-4.500 -0.2097 0.02759 0.01699 -0.0377 1.0000 0.1342
-4.250 -0.1826 0.02552 0.01457 -0.0369 1.0000 0.1382
-4.000 -0.1564 0.02397 0.01281 -0.0360 1.0000 0.1506
-3.750 -0.1303 0.02232 0.01123 -0.0351 1.0000 0.1681
-3.500 -0.1035 0.02086 0.00988 -0.0342 1.0000 0.2029
-3.250 -0.0688 0.01547 0.00803 -0.0321 1.0000 1.0000
-3.000 -0.0444 0.01549 0.00720 -0.0311 1.0000 1.0000
-2.750 -0.0217 0.01554 0.00681 -0.0302 1.0000 1.0000
-2.500 0.0007 0.01563 0.00655 -0.0295 1.0000 1.0000
-2.250 0.0231 0.01575 0.00638 -0.0288 1.0000 1.0000
-2.000 0.0453 0.01591 0.00631 -0.0282 1.0000 1.0000
-1.750 0.0672 0.01612 0.00632 -0.0276 1.0000 1.0000
-1.500 0.0888 0.01638 0.00642 -0.0271 1.0000 1.0000
-1.250 0.1099 0.01671 0.00660 -0.0267 1.0000 1.0000
-1.000 0.1302 0.01712 0.00691 -0.0264 1.0000 1.0000
-0.750 0.1496 0.01764 0.00735 -0.0263 1.0000 1.0000
-0.500 0.1678 0.01831 0.00796 -0.0263 1.0000 1.0000
-0.250 0.1846 0.01915 0.00875 -0.0266 1.0000 1.0000
0.000 0.2006 0.02013 0.00969 -0.0272 1.0000 1.0000
0.250 0.2749 0.02106 0.01060 -0.0378 0.9728 1.0000
0.500 0.3418 0.02167 0.01124 -0.0463 0.9446 1.0000
0.750 0.4033 0.02199 0.01164 -0.0531 0.9163 1.0000
1.000 0.4610 0.02206 0.01183 -0.0585 0.8888 1.0000
1.250 0.5109 0.02197 0.01185 -0.0617 0.8618 1.0000
1.500 0.5539 0.02188 0.01185 -0.0632 0.8348 1.0000
1.750 0.5901 0.02189 0.01197 -0.0633 0.8072 1.0000
2.000 0.6208 0.02203 0.01215 -0.0623 0.7791 1.0000
2.250 0.6482 0.02227 0.01242 -0.0608 0.7507 1.0000
2.500 0.6738 0.02258 0.01276 -0.0591 0.7221 1.0000
2.750 0.6982 0.02294 0.01318 -0.0572 0.6935 1.0000
3.000 0.7221 0.02333 0.01360 -0.0553 0.6646 1.0000
3.250 0.7459 0.02372 0.01400 -0.0534 0.6360 1.0000
3.500 0.7697 0.02420 0.01448 -0.0515 0.6070 1.0000
3.750 0.7928 0.02485 0.01517 -0.0496 0.5767 1.0000
4.000 0.8154 0.02557 0.01591 -0.0478 0.5453 1.0000
4.250 0.8379 0.02626 0.01660 -0.0459 0.5129 1.0000
4.500 0.8606 0.02680 0.01709 -0.0439 0.4796 1.0000
4.750 0.8815 0.02735 0.01775 -0.0419 0.4423 1.0000
5.000 0.9030 0.02766 0.01797 -0.0398 0.4037 1.0000
5.250 0.9234 0.02808 0.01826 -0.0376 0.3607 1.0000
5.500 0.9425 0.02889 0.01891 -0.0354 0.3140 1.0000
5.750 0.9613 0.03009 0.01992 -0.0335 0.2686 1.0000
6.000 0.9805 0.03180 0.02151 -0.0318 0.2305 1.0000
6.250 0.9998 0.03360 0.02324 -0.0304 0.2000 1.0000
6.500 1.0216 0.03591 0.02545 -0.0293 0.1791 1.0000
6.750 1.0400 0.03833 0.02817 -0.0280 0.1614 1.0000
7.000 1.0600 0.04133 0.03136 -0.0270 0.1501 1.0000
7.250 1.0800 0.04419 0.03435 -0.0261 0.1397 1.0000
7.500 1.0884 0.04795 0.03886 -0.0243 0.1325 1.0000
7.750 1.1061 0.05140 0.04242 -0.0235 0.1269 1.0000
8.000 1.1106 0.05627 0.04781 -0.0220 0.1247 1.0000
8.250 1.1053 0.06147 0.05362 -0.0205 0.1234 1.0000
8.500 1.0939 0.06697 0.05961 -0.0194 0.1229 1.0000
8.750 1.0776 0.07272 0.06568 -0.0188 0.1232 1.0000
9.000 1.0586 0.07858 0.07175 -0.0188 0.1241 1.0000
9.250 1.0394 0.08428 0.07756 -0.0191 0.1250 1.0000
9.500 1.0226 0.09043 0.08379 -0.0204 0.1260 1.0000
9.750 0.9115 0.11712 0.11020 -0.0448 0.1549 1.0000
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Polar data table (+)
Polar graphs
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