AG38 (ag38-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 50,000 Max Cl/Cd: 36.03 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag38-il-50000-n5.txt Download as CSV file: xf-ag38-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5184 0.10746 0.10044 -0.0006 1.0000 0.1082
-9.250 -0.5323 0.10548 0.09860 -0.0065 1.0000 0.1122
-9.000 -0.5317 0.10146 0.09467 -0.0102 1.0000 0.1132
-8.750 -0.5183 0.09687 0.09009 -0.0075 1.0000 0.1151
-8.500 -0.5105 0.09303 0.08628 -0.0083 1.0000 0.1172
-8.000 -0.4915 0.07819 0.07119 -0.0258 1.0000 0.0564
-7.750 -0.4817 0.07415 0.06715 -0.0263 1.0000 0.0552
-7.500 -0.4709 0.06974 0.06269 -0.0284 1.0000 0.0543
-7.250 -0.4585 0.06523 0.05808 -0.0307 1.0000 0.0536
-7.000 -0.4443 0.06071 0.05341 -0.0329 1.0000 0.0528
-6.750 -0.4282 0.05617 0.04867 -0.0349 1.0000 0.0516
-6.500 -0.4101 0.05156 0.04377 -0.0366 1.0000 0.0499
-6.250 -0.3897 0.04695 0.03876 -0.0381 1.0000 0.0483
-6.000 -0.3676 0.04270 0.03401 -0.0391 1.0000 0.0472
-5.750 -0.3443 0.03901 0.02978 -0.0394 1.0000 0.0466
-5.500 -0.3206 0.03591 0.02622 -0.0394 1.0000 0.0469
-5.250 -0.2971 0.03357 0.02358 -0.0392 1.0000 0.0493
-5.000 -0.2723 0.03131 0.02090 -0.0388 1.0000 0.0523
-4.750 -0.2464 0.02908 0.01820 -0.0382 1.0000 0.0541
-4.500 -0.2204 0.02709 0.01578 -0.0374 1.0000 0.0556
-4.250 -0.1950 0.02533 0.01374 -0.0365 1.0000 0.0585
-4.000 -0.1705 0.02404 0.01238 -0.0358 1.0000 0.0650
-3.750 -0.1446 0.02281 0.01087 -0.0348 1.0000 0.0703
-3.500 -0.1198 0.02165 0.00970 -0.0340 1.0000 0.0786
-3.250 -0.0942 0.02069 0.00867 -0.0334 1.0000 0.0929
-3.000 -0.0684 0.01970 0.00770 -0.0329 1.0000 0.1182
-2.750 -0.0420 0.01799 0.00685 -0.0332 1.0000 0.2520
-2.500 -0.0178 0.01532 0.00648 -0.0308 1.0000 1.0000
-2.250 0.0059 0.01537 0.00612 -0.0300 1.0000 1.0000
-2.000 0.0294 0.01544 0.00586 -0.0293 1.0000 1.0000
-1.750 0.0529 0.01554 0.00571 -0.0287 1.0000 1.0000
-1.500 0.0763 0.01568 0.00564 -0.0281 1.0000 1.0000
-1.250 0.0995 0.01584 0.00564 -0.0276 1.0000 1.0000
-1.000 0.1226 0.01605 0.00570 -0.0272 1.0000 1.0000
-0.750 0.1452 0.01630 0.00584 -0.0268 1.0000 1.0000
-0.500 0.1677 0.01661 0.00608 -0.0265 0.9998 1.0000
-0.250 0.2177 0.01687 0.00624 -0.0315 0.9811 1.0000
0.000 0.2657 0.01705 0.00638 -0.0359 0.9602 1.0000
0.250 0.3129 0.01716 0.00650 -0.0400 0.9382 1.0000
0.500 0.3571 0.01720 0.00656 -0.0431 0.9132 1.0000
0.750 0.3936 0.01722 0.00661 -0.0446 0.8811 1.0000
1.000 0.4328 0.01717 0.00659 -0.0462 0.8509 1.0000
1.250 0.4710 0.01715 0.00659 -0.0474 0.8199 1.0000
1.500 0.5051 0.01721 0.00661 -0.0477 0.7870 1.0000
1.750 0.5344 0.01739 0.00675 -0.0473 0.7517 1.0000
2.000 0.5615 0.01764 0.00698 -0.0464 0.7165 1.0000
2.250 0.5871 0.01793 0.00722 -0.0454 0.6807 1.0000
2.500 0.6121 0.01824 0.00747 -0.0442 0.6457 1.0000
2.750 0.6369 0.01860 0.00771 -0.0430 0.6130 1.0000
3.000 0.6612 0.01905 0.00810 -0.0418 0.5792 1.0000
3.250 0.6853 0.01954 0.00859 -0.0408 0.5452 1.0000
3.500 0.7091 0.02005 0.00907 -0.0397 0.5103 1.0000
3.750 0.7328 0.02056 0.00960 -0.0388 0.4720 1.0000
4.000 0.7560 0.02106 0.01012 -0.0378 0.4305 1.0000
4.250 0.7785 0.02161 0.01066 -0.0367 0.3868 1.0000
4.500 0.8005 0.02228 0.01121 -0.0357 0.3415 1.0000
4.750 0.8222 0.02312 0.01191 -0.0348 0.2957 1.0000
5.000 0.8436 0.02410 0.01277 -0.0340 0.2509 1.0000
5.250 0.8646 0.02524 0.01381 -0.0332 0.2106 1.0000
5.500 0.8854 0.02651 0.01502 -0.0325 0.1754 1.0000
5.750 0.9059 0.02792 0.01638 -0.0317 0.1483 1.0000
6.000 0.9257 0.02941 0.01780 -0.0309 0.1272 1.0000
6.250 0.9462 0.03099 0.01948 -0.0299 0.1114 1.0000
6.500 0.9664 0.03266 0.02125 -0.0290 0.0996 1.0000
6.750 0.9855 0.03432 0.02293 -0.0282 0.0893 1.0000
7.000 1.0072 0.03636 0.02533 -0.0272 0.0820 1.0000
7.250 1.0266 0.03835 0.02730 -0.0264 0.0761 1.0000
7.500 1.0452 0.04061 0.03006 -0.0254 0.0696 1.0000
7.750 1.0632 0.04291 0.03257 -0.0245 0.0657 1.0000
8.000 1.0796 0.04598 0.03593 -0.0236 0.0631 1.0000
8.250 1.0901 0.04947 0.04005 -0.0222 0.0602 1.0000
8.500 1.0983 0.05262 0.04363 -0.0209 0.0569 1.0000
8.750 1.1061 0.05547 0.04672 -0.0198 0.0543 1.0000
9.000 1.1116 0.05889 0.05037 -0.0186 0.0529 1.0000
9.250 1.1098 0.06310 0.05487 -0.0174 0.0521 1.0000
9.500 1.0978 0.06770 0.05989 -0.0160 0.0518 1.0000
9.750 1.0802 0.07218 0.06467 -0.0148 0.0517 1.0000
10.000 1.0593 0.07701 0.06973 -0.0147 0.0517 1.0000
10.250 1.0373 0.08275 0.07564 -0.0167 0.0519 1.0000
10.500 1.0155 0.08956 0.08259 -0.0206 0.0521 1.0000
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Polar data table (+)
Polar graphs
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