AG38 (ag38-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 50,000 Max Cl/Cd: 34.18 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag38-il-50000.txt Download as CSV file: xf-ag38-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5288 0.10881 0.10200 0.0035 1.0000 0.1981
-9.000 -0.5120 0.10381 0.09700 0.0051 1.0000 0.2076
-8.750 -0.5345 0.10322 0.09659 -0.0001 1.0000 0.2134
-8.500 -0.5209 0.09875 0.09213 0.0019 1.0000 0.2270
-8.250 -0.5137 0.09507 0.08850 0.0022 1.0000 0.2410
-8.000 -0.5111 0.09189 0.08539 0.0012 1.0000 0.2560
-7.750 -0.5100 0.08879 0.08237 -0.0005 1.0000 0.2717
-7.500 -0.4910 0.08434 0.07791 0.0045 1.0000 0.2922
-7.250 -0.4965 0.08222 0.07587 0.0011 1.0000 0.3149
-7.000 -0.4781 0.07788 0.07157 0.0062 1.0000 0.3364
-6.750 -0.4717 0.07475 0.06850 0.0078 1.0000 0.3638
-6.500 -0.4631 0.07169 0.06551 0.0106 1.0000 0.3956
-6.250 -0.4573 0.06884 0.06273 0.0139 1.0000 0.4345
-6.000 -0.4458 0.06585 0.05979 0.0192 1.0000 0.4797
-5.250 -0.3209 0.04151 0.03310 -0.0382 1.0000 0.1538
-5.000 -0.2915 0.03749 0.02848 -0.0392 1.0000 0.1393
-4.750 -0.2651 0.03419 0.02482 -0.0392 1.0000 0.1341
-4.500 -0.2342 0.03133 0.02105 -0.0391 1.0000 0.1261
-4.250 -0.2071 0.02878 0.01816 -0.0385 1.0000 0.1249
-4.000 -0.1800 0.02665 0.01566 -0.0379 1.0000 0.1285
-3.750 -0.1539 0.02490 0.01379 -0.0371 1.0000 0.1371
-3.500 -0.1264 0.02317 0.01184 -0.0361 1.0000 0.1443
-3.250 -0.1005 0.02175 0.01040 -0.0351 1.0000 0.1639
-3.000 -0.0725 0.02028 0.00897 -0.0342 1.0000 0.1963
-2.750 -0.0424 0.01529 0.00716 -0.0317 1.0000 1.0000
-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 0.00585 -0.0268 1.0000 1.0000
-0.500 0.1674 0.01661 0.00608 -0.0264 1.0000 1.0000
-0.250 0.1890 0.01699 0.00641 -0.0262 1.0000 1.0000
0.000 0.2096 0.01747 0.00685 -0.0260 1.0000 1.0000
0.250 0.2292 0.01809 0.00745 -0.0260 1.0000 1.0000
0.500 0.2472 0.01887 0.00824 -0.0262 1.0000 1.0000
0.750 0.2638 0.01985 0.00923 -0.0267 1.0000 1.0000
1.000 0.2920 0.02096 0.01038 -0.0296 0.9948 1.0000
1.250 0.3678 0.02178 0.01132 -0.0404 0.9634 1.0000
1.500 0.4377 0.02217 0.01190 -0.0490 0.9312 1.0000
1.750 0.5067 0.02209 0.01204 -0.0564 0.8995 1.0000
2.000 0.5575 0.02182 0.01198 -0.0596 0.8652 1.0000
2.250 0.6058 0.02132 0.01169 -0.0612 0.8323 1.0000
2.500 0.6419 0.02110 0.01157 -0.0604 0.7963 1.0000
2.750 0.6712 0.02108 0.01159 -0.0584 0.7583 1.0000
3.000 0.6954 0.02129 0.01187 -0.0557 0.7173 1.0000
3.250 0.7183 0.02154 0.01210 -0.0529 0.6747 1.0000
3.500 0.7409 0.02182 0.01230 -0.0501 0.6310 1.0000
3.750 0.7632 0.02233 0.01265 -0.0473 0.5851 1.0000
4.000 0.7842 0.02311 0.01337 -0.0448 0.5347 1.0000
4.250 0.8053 0.02383 0.01392 -0.0424 0.4837 1.0000
4.500 0.8254 0.02446 0.01444 -0.0400 0.4292 1.0000
4.750 0.8453 0.02515 0.01489 -0.0377 0.3738 1.0000
5.000 0.8651 0.02628 0.01573 -0.0357 0.3186 1.0000
5.250 0.8856 0.02780 0.01695 -0.0341 0.2697 1.0000
5.500 0.9071 0.02974 0.01880 -0.0328 0.2303 1.0000
5.750 0.9289 0.03165 0.02058 -0.0317 0.1999 1.0000
6.000 0.9520 0.03418 0.02330 -0.0307 0.1800 1.0000
6.250 0.9734 0.03653 0.02585 -0.0297 0.1626 1.0000
6.500 0.9945 0.03949 0.02916 -0.0287 0.1515 1.0000
6.750 1.0169 0.04257 0.03223 -0.0280 0.1427 1.0000
7.000 1.0290 0.04617 0.03669 -0.0264 0.1356 1.0000
7.250 1.0496 0.04951 0.03995 -0.0259 0.1291 1.0000
7.500 1.0567 0.05433 0.04551 -0.0244 0.1280 1.0000
7.750 1.0593 0.05961 0.05139 -0.0231 0.1277 1.0000
8.000 1.0566 0.06515 0.05743 -0.0222 0.1277 1.0000
8.250 1.0498 0.07087 0.06353 -0.0217 0.1279 1.0000
8.500 1.0410 0.07669 0.06961 -0.0216 0.1284 1.0000
8.750 1.0315 0.08259 0.07571 -0.0218 0.1293 1.0000
9.000 0.8644 0.11801 0.11092 -0.0565 0.2313 1.0000
9.250 0.8802 0.11893 0.11190 -0.0526 0.2007 1.0000
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Polar data table (+)
Polar graphs
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