AG19 (ag19-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 500,000 Max Cl/Cd: 81.68 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag19-il-500000.txt Download as CSV file: xf-ag19-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG19
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5426 0.10948 0.10724 0.0170 1.0000 0.0101
-8.500 -0.5461 0.10338 0.10118 0.0151 1.0000 0.0104
-8.250 -0.5424 0.09954 0.09735 0.0138 1.0000 0.0106
-8.000 -0.5366 0.09618 0.09401 0.0128 1.0000 0.0109
-7.750 -0.5306 0.09286 0.09070 0.0114 1.0000 0.0111
-7.500 -0.5246 0.08949 0.08736 0.0096 1.0000 0.0113
-7.250 -0.5174 0.08595 0.08383 0.0069 1.0000 0.0116
-7.000 -0.5063 0.08198 0.07988 0.0029 1.0000 0.0118
-6.750 -0.4929 0.07774 0.07565 -0.0018 1.0000 0.0122
-6.500 -0.4770 0.07321 0.07112 -0.0073 1.0000 0.0126
-6.250 -0.4581 0.06835 0.06624 -0.0135 1.0000 0.0131
-6.000 -0.4359 0.06311 0.06098 -0.0203 1.0000 0.0138
-5.750 -0.4101 0.05742 0.05523 -0.0275 1.0000 0.0146
-5.500 -0.3770 0.05132 0.04901 -0.0349 1.0000 0.0161
-5.250 -0.3435 0.04650 0.04402 -0.0397 1.0000 0.0169
-5.000 -0.3150 0.04092 0.03822 -0.0437 1.0000 0.0170
-4.500 -0.2648 0.02701 0.02354 -0.0509 1.0000 0.0191
-4.250 -0.2396 0.02497 0.02135 -0.0515 1.0000 0.0210
-4.000 -0.2122 0.02234 0.01841 -0.0518 1.0000 0.0236
-3.500 -0.1534 0.01577 0.01076 -0.0511 1.0000 0.0175
-3.250 -0.1257 0.01279 0.00745 -0.0509 1.0000 0.0153
-3.000 -0.0985 0.01117 0.00560 -0.0505 1.0000 0.0149
-2.750 -0.0715 0.01004 0.00433 -0.0500 1.0000 0.0153
-2.500 -0.0447 0.00934 0.00352 -0.0496 1.0000 0.0166
-2.250 -0.0167 0.00839 0.00247 -0.0495 1.0000 0.0220
-2.000 0.0103 0.00797 0.00207 -0.0492 1.0000 0.0370
-1.750 0.0453 0.00738 0.00173 -0.0508 0.9969 0.1036
-1.500 0.0843 0.00687 0.00159 -0.0535 0.9908 0.2124
-1.250 0.1227 0.00635 0.00148 -0.0560 0.9830 0.3483
-1.000 0.1583 0.00584 0.00143 -0.0578 0.9709 0.4976
-0.750 0.1903 0.00513 0.00139 -0.0586 0.9550 0.7107
-0.500 0.2183 0.00446 0.00128 -0.0578 0.9328 1.0000
-0.250 0.2455 0.00450 0.00119 -0.0572 0.9058 1.0000
0.000 0.2711 0.00458 0.00112 -0.0563 0.8768 1.0000
0.250 0.2967 0.00469 0.00108 -0.0554 0.8467 1.0000
0.500 0.3227 0.00482 0.00105 -0.0546 0.8153 1.0000
0.750 0.3489 0.00497 0.00103 -0.0540 0.7829 1.0000
1.000 0.3753 0.00514 0.00103 -0.0534 0.7497 1.0000
1.250 0.4020 0.00531 0.00105 -0.0529 0.7144 1.0000
1.500 0.4286 0.00550 0.00108 -0.0525 0.6768 1.0000
1.750 0.4553 0.00572 0.00113 -0.0521 0.6350 1.0000
2.000 0.4820 0.00597 0.00119 -0.0517 0.5891 1.0000
2.250 0.5086 0.00626 0.00126 -0.0514 0.5397 1.0000
2.500 0.5352 0.00657 0.00136 -0.0512 0.4889 1.0000
2.750 0.5619 0.00690 0.00149 -0.0509 0.4393 1.0000
3.250 0.6153 0.00757 0.00183 -0.0506 0.3534 1.0000
3.500 0.6423 0.00787 0.00200 -0.0504 0.3185 1.0000
3.750 0.6690 0.00821 0.00220 -0.0503 0.2843 1.0000
4.000 0.6959 0.00852 0.00241 -0.0501 0.2542 1.0000
4.250 0.7227 0.00885 0.00266 -0.0500 0.2253 1.0000
4.500 0.7493 0.00920 0.00291 -0.0498 0.1959 1.0000
4.750 0.7759 0.00956 0.00319 -0.0496 0.1708 1.0000
5.000 0.8023 0.00995 0.00349 -0.0494 0.1453 1.0000
5.250 0.8286 0.01037 0.00383 -0.0492 0.1231 1.0000
5.500 0.8550 0.01077 0.00421 -0.0490 0.1039 1.0000
5.750 0.8810 0.01125 0.00462 -0.0488 0.0860 1.0000
6.000 0.9070 0.01172 0.00506 -0.0485 0.0716 1.0000
6.250 0.9329 0.01220 0.00553 -0.0483 0.0585 1.0000
6.500 0.9586 0.01273 0.00606 -0.0480 0.0466 1.0000
6.750 0.9839 0.01336 0.00667 -0.0476 0.0356 1.0000
7.000 1.0084 0.01420 0.00756 -0.0472 0.0255 1.0000
7.250 1.0342 0.01463 0.00803 -0.0469 0.0198 1.0000
7.500 1.0575 0.01582 0.00936 -0.0461 0.0148 1.0000
7.750 1.0814 0.01672 0.01035 -0.0456 0.0118 1.0000
8.000 1.1005 0.01888 0.01275 -0.0444 0.0094 1.0000
8.250 1.1249 0.01954 0.01352 -0.0439 0.0083 1.0000
8.500 1.1466 0.02086 0.01501 -0.0431 0.0075 1.0000
8.750 1.1678 0.02219 0.01650 -0.0423 0.0068 1.0000
9.000 1.1875 0.02379 0.01831 -0.0415 0.0062 1.0000
9.250 1.1993 0.02726 0.02216 -0.0398 0.0057 1.0000
9.500 1.2006 0.03296 0.02848 -0.0376 0.0054 1.0000
9.750 1.2069 0.03671 0.03264 -0.0361 0.0053 1.0000
10.000 1.2092 0.04053 0.03685 -0.0346 0.0053 1.0000
10.250 1.2019 0.04520 0.04189 -0.0331 0.0053 1.0000
10.500 1.1784 0.05069 0.04771 -0.0314 0.0054 1.0000
10.750 1.1657 0.05461 0.05182 -0.0318 0.0054 1.0000
11.000 1.1517 0.06008 0.05748 -0.0354 0.0054 1.0000
11.250 1.1396 0.06699 0.06456 -0.0415 0.0054 1.0000
11.500 1.1290 0.07505 0.07277 -0.0487 0.0055 1.0000
11.750 1.1182 0.08366 0.08150 -0.0555 0.0055 1.0000
12.000 1.1061 0.09241 0.09034 -0.0613 0.0055 1.0000
12.250 1.0947 0.10059 0.09859 -0.0661 0.0056 1.0000
12.500 1.0814 0.10911 0.10716 -0.0705 0.0056 1.0000
12.750 1.0671 0.11791 0.11600 -0.0747 0.0058 1.0000
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Polar data table (+)
Polar graphs
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