AH 94-145 (ah94145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 1,000,000 Max Cl/Cd: 177.42 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94145-il-1000000.txt Download as CSV file: xf-ah94145-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1234 0.10524 0.10239 -0.0627 0.6864 0.0171
-11.250 -0.5610 0.03498 0.03151 -0.1101 0.6974 0.0132
-11.000 -0.5563 0.03101 0.02720 -0.1129 0.6949 0.0133
-10.750 -0.5413 0.02865 0.02458 -0.1142 0.6930 0.0134
-10.500 -0.5349 0.02399 0.01943 -0.1159 0.6915 0.0136
-10.250 -0.5149 0.02202 0.01725 -0.1165 0.6898 0.0138
-10.000 -0.4910 0.02088 0.01599 -0.1170 0.6878 0.0141
-9.750 -0.4658 0.01996 0.01497 -0.1174 0.6859 0.0143
-9.500 -0.4400 0.01915 0.01405 -0.1178 0.6840 0.0145
-9.250 -0.4138 0.01836 0.01313 -0.1182 0.6821 0.0148
-9.000 -0.3873 0.01760 0.01224 -0.1186 0.6802 0.0151
-8.750 -0.3604 0.01691 0.01141 -0.1190 0.6780 0.0154
-8.500 -0.3331 0.01623 0.01062 -0.1194 0.6765 0.0158
-8.250 -0.3052 0.01563 0.00992 -0.1197 0.6751 0.0161
-8.000 -0.2769 0.01517 0.00936 -0.1201 0.6735 0.0163
-7.750 -0.2499 0.01410 0.00817 -0.1206 0.6718 0.0170
-7.500 -0.2215 0.01364 0.00768 -0.1210 0.6702 0.0175
-7.250 -0.1929 0.01326 0.00725 -0.1215 0.6686 0.0180
-7.000 -0.1641 0.01287 0.00680 -0.1219 0.6670 0.0185
-6.750 -0.1352 0.01251 0.00636 -0.1223 0.6652 0.0191
-6.500 -0.1062 0.01221 0.00599 -0.1227 0.6633 0.0196
-6.250 -0.0773 0.01173 0.00543 -0.1231 0.6610 0.0203
-6.000 -0.0480 0.01136 0.00505 -0.1237 0.6600 0.0212
-5.750 -0.0185 0.01109 0.00477 -0.1241 0.6588 0.0222
-5.500 0.0111 0.01086 0.00451 -0.1246 0.6573 0.0232
-5.250 0.0407 0.01052 0.00414 -0.1251 0.6557 0.0246
-5.000 0.0704 0.01031 0.00392 -0.1256 0.6541 0.0263
-4.750 0.1001 0.01014 0.00372 -0.1261 0.6525 0.0278
-4.500 0.1300 0.00986 0.00344 -0.1266 0.6510 0.0305
-4.250 0.1598 0.00973 0.00328 -0.1271 0.6495 0.0329
-4.000 0.1896 0.00954 0.00310 -0.1277 0.6478 0.0371
-3.750 0.2194 0.00944 0.00299 -0.1282 0.6459 0.0422
-3.500 0.2493 0.00932 0.00289 -0.1287 0.6444 0.0481
-3.250 0.2793 0.00922 0.00281 -0.1292 0.6432 0.0535
-3.000 0.3093 0.00908 0.00271 -0.1298 0.6417 0.0610
-2.750 0.3393 0.00897 0.00262 -0.1303 0.6401 0.0679
-2.500 0.3693 0.00890 0.00256 -0.1309 0.6385 0.0737
-2.250 0.3993 0.00878 0.00247 -0.1314 0.6368 0.0825
-2.000 0.4293 0.00870 0.00239 -0.1320 0.6352 0.0901
-1.750 0.4593 0.00862 0.00233 -0.1325 0.6336 0.1012
-1.500 0.4895 0.00851 0.00228 -0.1332 0.6320 0.1245
-1.250 0.5198 0.00837 0.00228 -0.1339 0.6300 0.1758
-1.000 0.5507 0.00806 0.00228 -0.1350 0.6286 0.2802
-0.750 0.5822 0.00762 0.00228 -0.1363 0.6273 0.4294
-0.500 0.6138 0.00724 0.00231 -0.1375 0.6257 0.5776
-0.250 0.6445 0.00706 0.00235 -0.1383 0.6240 0.6627
0.000 0.6747 0.00694 0.00240 -0.1389 0.6223 0.7224
0.250 0.7042 0.00686 0.00245 -0.1392 0.6207 0.7753
0.500 0.7330 0.00684 0.00251 -0.1395 0.6191 0.8134
0.750 0.7614 0.00686 0.00257 -0.1396 0.6173 0.8422
1.000 0.7897 0.00694 0.00265 -0.1397 0.6153 0.8617
1.250 0.8173 0.00702 0.00275 -0.1396 0.6133 0.8823
1.500 0.8443 0.00705 0.00282 -0.1394 0.6118 0.9032
1.750 0.8692 0.00706 0.00289 -0.1386 0.6100 0.9202
2.000 0.8949 0.00708 0.00293 -0.1381 0.6081 0.9325
2.250 0.9192 0.00708 0.00295 -0.1373 0.6061 0.9425
2.500 0.9442 0.00708 0.00296 -0.1367 0.6042 0.9514
3.000 0.9927 0.00712 0.00299 -0.1352 0.6000 0.9700
3.250 1.0178 0.00713 0.00301 -0.1347 0.5977 0.9815
3.500 1.0489 0.00710 0.00302 -0.1356 0.5956 0.9998
3.750 1.0802 0.00715 0.00307 -0.1365 0.5929 0.9998
4.000 1.1112 0.00718 0.00311 -0.1374 0.5897 0.9998
4.250 1.1418 0.00723 0.00314 -0.1383 0.5857 0.9998
4.500 1.1722 0.00729 0.00320 -0.1391 0.5812 0.9998
4.750 1.2025 0.00730 0.00324 -0.1398 0.5761 0.9998
5.000 1.2323 0.00736 0.00328 -0.1405 0.5706 0.9998
5.250 1.2621 0.00743 0.00337 -0.1412 0.5654 0.9998
5.500 1.2917 0.00749 0.00345 -0.1418 0.5592 0.9998
5.750 1.3204 0.00762 0.00354 -0.1423 0.5532 0.9998
6.000 1.3499 0.00769 0.00366 -0.1429 0.5477 0.9998
6.250 1.3784 0.00781 0.00378 -0.1433 0.5413 0.9998
6.500 1.4069 0.00793 0.00392 -0.1438 0.5345 0.9998
6.750 1.4343 0.00811 0.00407 -0.1440 0.5245 0.9998
7.000 1.4616 0.00828 0.00425 -0.1443 0.5121 0.9998
7.250 1.4880 0.00851 0.00446 -0.1444 0.4988 0.9998
7.500 1.5133 0.00880 0.00471 -0.1443 0.4831 0.9998
7.750 1.5363 0.00923 0.00505 -0.1439 0.4603 0.9998
8.000 1.5549 0.00992 0.00557 -0.1428 0.4242 0.9998
8.250 1.5666 0.01099 0.00638 -0.1406 0.3761 0.9998
8.500 1.5739 0.01221 0.00735 -0.1378 0.3303 0.9998
8.750 1.5766 0.01339 0.00834 -0.1342 0.2942 0.9998
9.000 1.5770 0.01473 0.00953 -0.1305 0.2635 0.9998
9.250 1.5770 0.01633 0.01099 -0.1274 0.2357 0.9998
9.500 1.5778 0.01811 0.01267 -0.1248 0.2105 0.9998
9.750 1.5788 0.02008 0.01453 -0.1226 0.1882 0.9998
10.000 1.5807 0.02207 0.01645 -0.1207 0.1688 0.9998
10.250 1.5827 0.02412 0.01843 -0.1189 0.1521 0.9998
10.500 1.5853 0.02614 0.02039 -0.1172 0.1378 0.9998
10.750 1.5878 0.02816 0.02237 -0.1155 0.1244 0.9998
11.000 1.5902 0.03017 0.02434 -0.1138 0.1125 0.9998
11.250 1.5938 0.03209 0.02624 -0.1122 0.1026 0.9998
11.500 1.5971 0.03404 0.02817 -0.1106 0.0940 0.9998
11.750 1.5999 0.03603 0.03013 -0.1090 0.0863 0.9998
12.000 1.6053 0.03782 0.03193 -0.1076 0.0797 0.9998
12.250 1.6081 0.03991 0.03400 -0.1062 0.0728 0.9998
12.500 1.6142 0.04171 0.03581 -0.1050 0.0677 0.9998
12.750 1.6179 0.04377 0.03787 -0.1037 0.0623 0.9998
13.000 1.6246 0.04558 0.03970 -0.1027 0.0581 0.9998
13.250 1.6278 0.04777 0.04188 -0.1015 0.0533 0.9998
13.500 1.6347 0.04959 0.04373 -0.1005 0.0499 0.9998
13.750 1.6375 0.05184 0.04598 -0.0994 0.0460 0.9998
14.000 1.6443 0.05373 0.04791 -0.0985 0.0434 0.9998
14.250 1.6488 0.05587 0.05006 -0.0975 0.0406 0.9998
14.500 1.6521 0.05816 0.05237 -0.0966 0.0378 0.9998
14.750 1.6591 0.06006 0.05432 -0.0958 0.0361 0.9998
15.000 1.6625 0.06238 0.05667 -0.0950 0.0341 0.9998
15.250 1.6645 0.06486 0.05916 -0.0941 0.0319 0.9998
15.500 1.6712 0.06688 0.06124 -0.0935 0.0307 0.9998
15.750 1.6755 0.06917 0.06359 -0.0929 0.0293 0.9998
16.000 1.6780 0.07163 0.06607 -0.0922 0.0278 0.9998
16.250 1.6787 0.07437 0.06886 -0.0915 0.0264 0.9998
16.500 1.6848 0.07648 0.07104 -0.0910 0.0255 0.9998
16.750 1.6878 0.07900 0.07361 -0.0906 0.0244 0.9998
17.000 1.6896 0.08167 0.07631 -0.0901 0.0233 0.9998
17.250 1.6875 0.08483 0.07952 -0.0896 0.0221 0.9998
17.500 1.6914 0.08726 0.08203 -0.0893 0.0215 0.9998
17.750 1.6944 0.08983 0.08467 -0.0891 0.0207 0.9998
18.000 1.6952 0.09270 0.08760 -0.0889 0.0199 0.9998
18.250 1.6948 0.09575 0.09069 -0.0887 0.0191 0.9998
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