AG38 (ag38-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 500,000 Max Cl/Cd: 73.45 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag38-il-500000-n5.txt Download as CSV file: xf-ag38-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG38
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5347 0.08648 0.08422 -0.0056 1.0000 0.0089
-9.000 -0.5333 0.08303 0.08080 -0.0077 1.0000 0.0087
-8.750 -0.5292 0.07872 0.07651 -0.0118 1.0000 0.0085
-8.500 -0.5220 0.07363 0.07141 -0.0172 1.0000 0.0083
-8.250 -0.5129 0.06796 0.06571 -0.0230 1.0000 0.0081
-8.000 -0.5021 0.06176 0.05944 -0.0286 1.0000 0.0079
-7.750 -0.4902 0.05507 0.05265 -0.0335 1.0000 0.0077
-7.500 -0.4775 0.04790 0.04528 -0.0371 1.0000 0.0075
-7.250 -0.4639 0.04032 0.03740 -0.0392 1.0000 0.0075
-7.000 -0.4487 0.03234 0.02896 -0.0401 1.0000 0.0076
-6.750 -0.4329 0.02234 0.01799 -0.0398 1.0000 0.0081
-6.500 -0.4115 0.01822 0.01321 -0.0390 1.0000 0.0085
-6.250 -0.3865 0.01657 0.01119 -0.0385 0.9996 0.0090
-6.000 -0.3550 0.01495 0.00927 -0.0395 0.9978 0.0095
-5.750 -0.3227 0.01393 0.00811 -0.0405 0.9959 0.0099
-5.500 -0.2900 0.01308 0.00714 -0.0416 0.9941 0.0103
-5.250 -0.2586 0.01233 0.00627 -0.0424 0.9916 0.0108
-5.000 -0.2261 0.01164 0.00548 -0.0433 0.9888 0.0115
-4.750 -0.1924 0.01103 0.00479 -0.0446 0.9862 0.0122
-4.500 -0.1584 0.01051 0.00420 -0.0458 0.9835 0.0129
-4.250 -0.1276 0.01000 0.00368 -0.0465 0.9779 0.0143
-4.000 -0.0946 0.00970 0.00336 -0.0475 0.9724 0.0161
-3.750 -0.0633 0.00937 0.00299 -0.0481 0.9651 0.0174
-3.500 -0.0316 0.00898 0.00258 -0.0488 0.9564 0.0198
-3.250 -0.0025 0.00876 0.00233 -0.0489 0.9444 0.0230
-3.000 0.0260 0.00852 0.00209 -0.0488 0.9304 0.0287
-2.750 0.0535 0.00832 0.00189 -0.0485 0.9107 0.0380
-2.500 0.0791 0.00812 0.00168 -0.0476 0.8624 0.0629
-2.250 0.1036 0.00799 0.00150 -0.0466 0.8167 0.1145
-2.000 0.1297 0.00777 0.00142 -0.0463 0.7816 0.2066
-1.750 0.1561 0.00743 0.00137 -0.0462 0.7490 0.3439
-1.500 0.1820 0.00689 0.00134 -0.0461 0.7146 0.5455
-1.250 0.2039 0.00624 0.00136 -0.0447 0.6639 0.7904
-1.000 0.2288 0.00604 0.00131 -0.0433 0.6127 0.9764
-0.750 0.2603 0.00621 0.00128 -0.0442 0.5831 1.0000
-0.500 0.2878 0.00636 0.00129 -0.0441 0.5617 1.0000
-0.250 0.3154 0.00650 0.00131 -0.0440 0.5438 1.0000
0.000 0.3431 0.00663 0.00134 -0.0439 0.5275 1.0000
0.500 0.3986 0.00688 0.00142 -0.0439 0.4968 1.0000
0.750 0.4264 0.00701 0.00147 -0.0439 0.4807 1.0000
1.000 0.4542 0.00713 0.00154 -0.0439 0.4621 1.0000
1.250 0.4819 0.00728 0.00160 -0.0439 0.4389 1.0000
1.500 0.5093 0.00747 0.00167 -0.0438 0.4100 1.0000
1.750 0.5366 0.00770 0.00176 -0.0438 0.3781 1.0000
2.000 0.5637 0.00796 0.00189 -0.0438 0.3455 1.0000
2.250 0.5907 0.00825 0.00204 -0.0438 0.3118 1.0000
2.500 0.6177 0.00856 0.00220 -0.0438 0.2779 1.0000
2.750 0.6445 0.00889 0.00239 -0.0437 0.2444 1.0000
3.000 0.6713 0.00922 0.00260 -0.0437 0.2146 1.0000
3.250 0.6981 0.00955 0.00282 -0.0437 0.1874 1.0000
3.500 0.7248 0.00989 0.00305 -0.0437 0.1620 1.0000
3.750 0.7514 0.01023 0.00330 -0.0437 0.1393 1.0000
4.000 0.7778 0.01062 0.00359 -0.0436 0.1156 1.0000
4.250 0.8043 0.01098 0.00388 -0.0436 0.0963 1.0000
4.500 0.8304 0.01140 0.00421 -0.0435 0.0776 1.0000
4.750 0.8565 0.01179 0.00454 -0.0434 0.0639 1.0000
5.000 0.8827 0.01217 0.00491 -0.0433 0.0536 1.0000
5.250 0.9088 0.01255 0.00528 -0.0432 0.0456 1.0000
5.500 0.9347 0.01295 0.00569 -0.0431 0.0391 1.0000
5.750 0.9604 0.01337 0.00610 -0.0429 0.0343 1.0000
6.000 0.9859 0.01382 0.00660 -0.0427 0.0306 1.0000
6.250 1.0116 0.01421 0.00705 -0.0426 0.0279 1.0000
6.500 1.0366 0.01471 0.00755 -0.0424 0.0249 1.0000
6.750 1.0612 0.01527 0.00817 -0.0420 0.0227 1.0000
7.000 1.0860 0.01574 0.00873 -0.0418 0.0214 1.0000
7.250 1.1105 0.01625 0.00932 -0.0415 0.0200 1.0000
7.500 1.1346 0.01680 0.00991 -0.0412 0.0185 1.0000
7.750 1.1567 0.01765 0.01083 -0.0406 0.0168 1.0000
8.000 1.1804 0.01822 0.01149 -0.0402 0.0162 1.0000
8.250 1.2033 0.01886 0.01225 -0.0397 0.0154 1.0000
8.500 1.2258 0.01953 0.01301 -0.0392 0.0145 1.0000
8.750 1.2482 0.02018 0.01374 -0.0387 0.0137 1.0000
9.000 1.2696 0.02093 0.01456 -0.0381 0.0128 1.0000
9.250 1.2875 0.02213 0.01586 -0.0371 0.0119 1.0000
9.500 1.3079 0.02294 0.01680 -0.0364 0.0116 1.0000
9.750 1.3272 0.02384 0.01786 -0.0355 0.0111 1.0000
10.000 1.3455 0.02480 0.01896 -0.0346 0.0106 1.0000
10.250 1.3634 0.02575 0.02003 -0.0336 0.0101 1.0000
10.500 1.3810 0.02666 0.02104 -0.0326 0.0096 1.0000
10.750 1.3973 0.02762 0.02210 -0.0316 0.0091 1.0000
11.000 1.4097 0.02893 0.02353 -0.0301 0.0087 1.0000
11.250 1.4171 0.03061 0.02537 -0.0281 0.0083 1.0000
11.500 1.4257 0.03198 0.02691 -0.0262 0.0081 1.0000
11.750 1.4288 0.03346 0.02857 -0.0235 0.0079 1.0000
12.000 1.4297 0.03520 0.03049 -0.0211 0.0077 1.0000
12.250 1.4292 0.03723 0.03269 -0.0191 0.0075 1.0000
12.500 1.4269 0.03964 0.03527 -0.0178 0.0074 1.0000
12.750 1.4229 0.04257 0.03838 -0.0173 0.0072 1.0000
13.000 1.4174 0.04611 0.04210 -0.0178 0.0071 1.0000
13.250 1.4102 0.05037 0.04654 -0.0194 0.0069 1.0000
13.500 1.4011 0.05551 0.05187 -0.0221 0.0068 1.0000
13.750 1.3884 0.06172 0.05825 -0.0257 0.0068 1.0000
14.000 1.3715 0.06887 0.06559 -0.0298 0.0067 1.0000
14.250 1.3499 0.07695 0.07384 -0.0343 0.0068 1.0000
14.500 1.3239 0.08610 0.08317 -0.0392 0.0068 1.0000
14.750 1.2932 0.09634 0.09357 -0.0445 0.0069 1.0000
15.000 1.2614 0.10705 0.10443 -0.0498 0.0070 1.0000
15.250 1.2280 0.11854 0.11606 -0.0556 0.0071 1.0000
15.500 1.1942 0.13069 0.12833 -0.0617 0.0073 1.0000
15.750 1.1580 0.14417 0.14194 -0.0686 0.0075 1.0000
16.000 1.1084 0.16251 0.16041 -0.0779 0.0077 1.0000
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