AH 94-145 (ah94145-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 100,000 Max Cl/Cd: 30.57 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94145-il-100000-n5.txt Download as CSV file: xf-ah94145-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-145
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1647 0.11364 0.10792 -0.0674 0.7836 0.0582
-10.250 -0.1592 0.11041 0.10467 -0.0691 0.7807 0.0586
-9.750 -0.1688 0.09798 0.09218 -0.0774 0.7761 0.0387
-9.500 -0.1585 0.09523 0.08944 -0.0781 0.7728 0.0382
-9.250 -0.1514 0.09196 0.08618 -0.0797 0.7697 0.0377
-9.000 -0.1464 0.08835 0.08258 -0.0818 0.7670 0.0372
-8.750 -0.1433 0.08438 0.07861 -0.0846 0.7644 0.0372
-8.500 -0.1414 0.08007 0.07430 -0.0879 0.7620 0.0374
-8.250 -0.1404 0.07541 0.06962 -0.0919 0.7597 0.0376
-8.000 -0.1415 0.07057 0.06484 -0.0971 0.7564 0.0376
-7.750 -0.1391 0.06417 0.05840 -0.1054 0.7531 0.0374
-7.500 -0.1361 0.05767 0.05175 -0.1121 0.7501 0.0371
-7.250 -0.1316 0.05117 0.04496 -0.1173 0.7475 0.0368
-7.000 -0.1236 0.04497 0.03828 -0.1211 0.7453 0.0368
-6.750 -0.1099 0.03974 0.03243 -0.1235 0.7435 0.0373
-6.500 -0.0924 0.03493 0.02677 -0.1253 0.7405 0.0387
-6.250 -0.0688 0.03418 0.02603 -0.1258 0.7375 0.0402
-6.000 -0.0448 0.03277 0.02437 -0.1263 0.7346 0.0420
-5.750 -0.0198 0.03063 0.02175 -0.1268 0.7321 0.0437
-5.500 0.0064 0.02869 0.01929 -0.1271 0.7299 0.0458
-5.250 0.0328 0.02807 0.01863 -0.1274 0.7281 0.0483
-5.000 0.0598 0.02715 0.01744 -0.1276 0.7262 0.0517
-4.750 0.0854 0.02624 0.01637 -0.1277 0.7230 0.0545
-4.500 0.1113 0.02582 0.01593 -0.1279 0.7199 0.0584
-4.250 0.1382 0.02517 0.01508 -0.1280 0.7173 0.0634
-4.000 0.1649 0.02467 0.01460 -0.1281 0.7150 0.0683
-3.750 0.1923 0.02418 0.01397 -0.1282 0.7132 0.0752
-3.500 0.2197 0.02376 0.01354 -0.1284 0.7115 0.0828
-3.250 0.2466 0.02340 0.01315 -0.1285 0.7094 0.0913
-3.000 0.2711 0.02337 0.01310 -0.1285 0.7057 0.1012
-2.750 0.2967 0.02318 0.01299 -0.1286 0.7027 0.1124
-2.500 0.3232 0.02300 0.01283 -0.1288 0.7003 0.1259
-2.250 0.3504 0.02281 0.01267 -0.1290 0.6982 0.1434
-2.000 0.3783 0.02256 0.01248 -0.1293 0.6963 0.1698
-1.750 0.4066 0.02216 0.01231 -0.1297 0.6947 0.2287
-1.500 0.4309 0.02172 0.01251 -0.1299 0.6920 0.3907
-1.250 0.4491 0.02157 0.01316 -0.1287 0.6882 0.6053
-1.000 0.4641 0.02170 0.01363 -0.1258 0.6852 0.7272
-0.750 0.4781 0.02184 0.01391 -0.1223 0.6826 0.8114
-0.500 0.4959 0.02195 0.01398 -0.1197 0.6804 0.8728
-0.250 0.5166 0.02194 0.01390 -0.1176 0.6787 0.9233
0.000 0.5550 0.02179 0.01364 -0.1193 0.6774 0.9998
0.250 0.5697 0.02293 0.01477 -0.1188 0.6718 0.9998
0.500 0.5938 0.02346 0.01520 -0.1189 0.6684 0.9998
0.750 0.6210 0.02377 0.01540 -0.1193 0.6658 0.9998
1.000 0.6499 0.02398 0.01550 -0.1198 0.6639 0.9998
1.250 0.6794 0.02418 0.01559 -0.1204 0.6623 0.9998
2.250 0.7691 0.02690 0.01818 -0.1201 0.6481 0.9998
2.500 0.7988 0.02706 0.01828 -0.1206 0.6465 0.9998
2.750 0.8296 0.02714 0.01831 -0.1211 0.6452 0.9998
3.250 0.8525 0.02998 0.02124 -0.1190 0.6329 0.9998
3.500 0.8820 0.03010 0.02134 -0.1194 0.6313 0.9998
3.750 0.9126 0.03015 0.02136 -0.1198 0.6299 0.9998
4.250 0.9295 0.03334 0.02467 -0.1172 0.6166 0.9998
4.500 0.9598 0.03334 0.02467 -0.1175 0.6152 0.9998
4.750 0.9892 0.03340 0.02474 -0.1177 0.6135 0.9998
5.250 0.9884 0.03781 0.02928 -0.1138 0.5965 0.9998
5.500 1.0339 0.03637 0.02786 -0.1148 0.5984 0.9998
6.000 1.0438 0.04017 0.03178 -0.1120 0.5824 0.9998
6.500 1.0429 0.04489 0.03664 -0.1088 0.5626 0.9998
6.750 1.1036 0.04180 0.03361 -0.1102 0.5685 0.9998
7.250 1.1215 0.04463 0.03659 -0.1077 0.5525 0.9998
7.750 1.1565 0.04567 0.03778 -0.1060 0.5397 0.9998
8.250 1.1889 0.04673 0.03902 -0.1039 0.5251 0.9998
8.750 1.2249 0.04719 0.03966 -0.1019 0.5100 0.9998
9.250 1.2369 0.05016 0.04284 -0.0991 0.4865 0.9998
9.500 1.2683 0.04888 0.04165 -0.0985 0.4806 0.9998
9.750 1.2740 0.05046 0.04332 -0.0972 0.4673 0.9998
10.000 1.2841 0.05156 0.04454 -0.0960 0.4543 0.9998
10.250 1.2980 0.05227 0.04533 -0.0949 0.4412 0.9998
10.500 1.3136 0.05277 0.04591 -0.0938 0.4267 0.9998
10.750 1.3310 0.05304 0.04623 -0.0928 0.4106 0.9998
11.000 1.3529 0.05272 0.04593 -0.0917 0.3918 0.9998
11.250 1.3719 0.05270 0.04584 -0.0905 0.3677 0.9998
11.500 1.3882 0.05289 0.04588 -0.0890 0.3390 0.9998
11.750 1.3957 0.05413 0.04694 -0.0874 0.3094 0.9998
12.000 1.3977 0.05610 0.04873 -0.0858 0.2816 0.9998
12.250 1.3967 0.05856 0.05107 -0.0844 0.2559 0.9998
12.500 1.3951 0.06118 0.05356 -0.0830 0.2330 0.9998
12.750 1.3935 0.06392 0.05621 -0.0819 0.2122 0.9998
13.000 1.3921 0.06671 0.05892 -0.0808 0.1939 0.9998
13.250 1.3907 0.06956 0.06169 -0.0799 0.1777 0.9998
13.500 1.3904 0.07236 0.06447 -0.0791 0.1629 0.9998
13.750 1.3904 0.07519 0.06727 -0.0783 0.1500 0.9998
14.000 1.3914 0.07794 0.07003 -0.0777 0.1381 0.9998
14.250 1.3926 0.08069 0.07280 -0.0772 0.1277 0.9998
14.500 1.3935 0.08350 0.07561 -0.0766 0.1188 0.9998
14.750 1.3941 0.08639 0.07851 -0.0762 0.1108 0.9998
15.000 1.3965 0.08909 0.08128 -0.0759 0.1033 0.9998
15.250 1.3966 0.09210 0.08428 -0.0756 0.0972 0.9998
15.500 1.3999 0.09471 0.08700 -0.0753 0.0911 0.9998
15.750 1.4006 0.09768 0.09000 -0.0752 0.0860 0.9998
16.000 1.4032 0.10041 0.09279 -0.0751 0.0812 0.9998
16.250 1.4056 0.10320 0.09568 -0.0751 0.0767 0.9998
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Polar data table (+)
Polar graphs
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