AH 94-145 (ah94145-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 500,000 Max Cl/Cd: 132.4 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94145-il-500000-n5.txt Download as CSV file: xf-ah94145-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2489 0.11858 0.11481 -0.0500 0.6908 0.0118
-11.500 -0.2442 0.11490 0.11113 -0.0517 0.6893 0.0121
-11.000 -0.5539 0.03274 0.02824 -0.1119 0.6912 0.0126
-10.750 -0.5438 0.02927 0.02440 -0.1137 0.6891 0.0128
-10.500 -0.5273 0.02685 0.02164 -0.1148 0.6870 0.0130
-10.250 -0.5073 0.02499 0.01950 -0.1155 0.6851 0.0132
-10.000 -0.4851 0.02352 0.01777 -0.1160 0.6832 0.0134
-9.750 -0.4622 0.02218 0.01626 -0.1165 0.6813 0.0136
-9.500 -0.4372 0.02132 0.01528 -0.1170 0.6796 0.0139
-9.250 -0.4114 0.02062 0.01447 -0.1174 0.6779 0.0142
-9.000 -0.3851 0.01992 0.01366 -0.1178 0.6762 0.0146
-8.750 -0.3586 0.01917 0.01280 -0.1182 0.6744 0.0150
-8.500 -0.3318 0.01840 0.01189 -0.1186 0.6724 0.0154
-8.250 -0.3048 0.01766 0.01101 -0.1189 0.6706 0.0157
-8.000 -0.2774 0.01700 0.01021 -0.1193 0.6689 0.0161
-7.750 -0.2497 0.01641 0.00949 -0.1197 0.6672 0.0164
-7.500 -0.2222 0.01576 0.00878 -0.1201 0.6656 0.0169
-7.250 -0.1941 0.01531 0.00825 -0.1205 0.6640 0.0174
-7.000 -0.1658 0.01491 0.00777 -0.1209 0.6623 0.0179
-6.750 -0.1374 0.01451 0.00729 -0.1212 0.6606 0.0186
-6.500 -0.1086 0.01413 0.00685 -0.1217 0.6590 0.0194
-6.250 -0.0798 0.01374 0.00640 -0.1221 0.6575 0.0202
-6.000 -0.0509 0.01340 0.00605 -0.1226 0.6559 0.0212
-5.750 -0.0219 0.01310 0.00571 -0.1230 0.6541 0.0222
-5.500 0.0073 0.01282 0.00536 -0.1234 0.6524 0.0233
-5.250 0.0364 0.01251 0.00503 -0.1239 0.6506 0.0245
-5.000 0.0657 0.01227 0.00475 -0.1243 0.6490 0.0261
-4.750 0.0950 0.01207 0.00450 -0.1247 0.6475 0.0280
-4.500 0.1243 0.01186 0.00427 -0.1252 0.6461 0.0306
-4.250 0.1538 0.01169 0.00406 -0.1257 0.6446 0.0335
-4.000 0.1833 0.01149 0.00389 -0.1262 0.6430 0.0370
-3.750 0.2129 0.01132 0.00374 -0.1267 0.6413 0.0412
-3.500 0.2426 0.01118 0.00360 -0.1272 0.6395 0.0464
-3.250 0.2722 0.01105 0.00349 -0.1277 0.6379 0.0521
-3.000 0.3018 0.01093 0.00338 -0.1282 0.6363 0.0583
-2.750 0.3315 0.01083 0.00327 -0.1286 0.6348 0.0643
-2.500 0.3611 0.01073 0.00318 -0.1292 0.6333 0.0714
-2.250 0.3908 0.01064 0.00309 -0.1296 0.6317 0.0790
-2.000 0.4204 0.01058 0.00301 -0.1301 0.6301 0.0870
-1.750 0.4502 0.01049 0.00295 -0.1307 0.6285 0.0982
-1.500 0.4800 0.01038 0.00291 -0.1313 0.6269 0.1131
-1.250 0.5098 0.01025 0.00287 -0.1319 0.6251 0.1391
-1.000 0.5399 0.01007 0.00285 -0.1326 0.6232 0.1873
-0.750 0.5701 0.00982 0.00283 -0.1335 0.6214 0.2680
-0.500 0.6007 0.00952 0.00283 -0.1344 0.6197 0.3750
-0.250 0.6315 0.00919 0.00286 -0.1355 0.6181 0.5044
0.000 0.6618 0.00898 0.00292 -0.1363 0.6166 0.6023
0.250 0.6914 0.00887 0.00297 -0.1368 0.6150 0.6740
0.500 0.7203 0.00881 0.00305 -0.1371 0.6133 0.7269
0.750 0.7477 0.00874 0.00318 -0.1370 0.6115 0.7847
1.000 0.7719 0.00873 0.00333 -0.1360 0.6096 0.8488
1.250 0.7961 0.00877 0.00345 -0.1350 0.6077 0.8858
1.500 0.8207 0.00881 0.00352 -0.1342 0.6058 0.9056
1.750 0.8468 0.00885 0.00356 -0.1339 0.6039 0.9187
2.000 0.8719 0.00888 0.00359 -0.1333 0.6019 0.9289
2.250 0.8978 0.00892 0.00361 -0.1329 0.6001 0.9378
2.500 0.9241 0.00898 0.00365 -0.1326 0.5984 0.9470
2.750 0.9488 0.00898 0.00371 -0.1320 0.5962 0.9570
3.000 0.9750 0.00900 0.00376 -0.1317 0.5939 0.9679
3.250 1.0039 0.00903 0.00381 -0.1321 0.5915 0.9805
3.500 1.0350 0.00908 0.00386 -0.1330 0.5891 0.9998
3.750 1.0651 0.00917 0.00395 -0.1338 0.5869 0.9998
4.000 1.0951 0.00927 0.00404 -0.1345 0.5847 0.9998
4.250 1.1249 0.00937 0.00416 -0.1351 0.5821 0.9998
4.500 1.1543 0.00947 0.00430 -0.1358 0.5787 0.9998
4.750 1.1835 0.00955 0.00442 -0.1363 0.5747 0.9998
5.000 1.2124 0.00963 0.00447 -0.1368 0.5698 0.9998
5.250 1.2409 0.00971 0.00459 -0.1372 0.5631 0.9998
5.500 1.2689 0.00980 0.00467 -0.1375 0.5551 0.9998
5.750 1.2966 0.00991 0.00480 -0.1378 0.5461 0.9998
6.000 1.3237 0.01005 0.00493 -0.1380 0.5372 0.9998
6.250 1.3505 0.01021 0.00511 -0.1381 0.5264 0.9998
6.500 1.3770 0.01040 0.00530 -0.1382 0.5154 0.9998
6.750 1.4026 0.01063 0.00552 -0.1381 0.5042 0.9998
7.000 1.4272 0.01092 0.00578 -0.1379 0.4907 0.9998
7.250 1.4502 0.01127 0.00610 -0.1374 0.4731 0.9998
7.500 1.4690 0.01184 0.00655 -0.1363 0.4465 0.9998
7.750 1.4820 0.01269 0.00723 -0.1343 0.4094 0.9998
8.000 1.4873 0.01388 0.00821 -0.1313 0.3683 0.9998
8.250 1.4858 0.01523 0.00939 -0.1272 0.3334 0.9998
8.500 1.4842 0.01687 0.01088 -0.1238 0.3021 0.9998
8.750 1.4831 0.01875 0.01264 -0.1210 0.2738 0.9998
9.000 1.4823 0.02084 0.01462 -0.1186 0.2480 0.9998
9.250 1.4811 0.02309 0.01677 -0.1165 0.2236 0.9998
9.500 1.4811 0.02533 0.01892 -0.1146 0.2015 0.9998
9.750 1.4812 0.02756 0.02108 -0.1128 0.1817 0.9998
10.000 1.4818 0.02977 0.02321 -0.1110 0.1644 0.9998
10.500 1.4856 0.03395 0.02730 -0.1077 0.1360 0.9998
10.750 1.4894 0.03589 0.02922 -0.1062 0.1244 0.9998
11.000 1.4937 0.03779 0.03110 -0.1047 0.1147 0.9998
11.250 1.4974 0.03979 0.03308 -0.1033 0.1059 0.9998
11.500 1.5015 0.04176 0.03504 -0.1020 0.0973 0.9998
11.750 1.5073 0.04366 0.03695 -0.1009 0.0901 0.9998
12.000 1.5121 0.04565 0.03894 -0.0997 0.0832 0.9998
12.250 1.5182 0.04759 0.04089 -0.0987 0.0771 0.9998
12.500 1.5234 0.04959 0.04290 -0.0976 0.0716 0.9998
12.750 1.5290 0.05160 0.04492 -0.0967 0.0661 0.9998
13.000 1.5342 0.05368 0.04701 -0.0957 0.0614 0.9998
13.250 1.5404 0.05567 0.04903 -0.0949 0.0570 0.9998
13.500 1.5448 0.05787 0.05125 -0.0940 0.0531 0.9998
13.750 1.5514 0.05985 0.05327 -0.0932 0.0498 0.9998
14.000 1.5557 0.06211 0.05555 -0.0924 0.0465 0.9998
14.250 1.5612 0.06426 0.05774 -0.0917 0.0437 0.9998
14.500 1.5666 0.06644 0.05997 -0.0910 0.0411 0.9998
14.750 1.5701 0.06886 0.06241 -0.0904 0.0388 0.9998
15.000 1.5755 0.07106 0.06468 -0.0898 0.0368 0.9998
15.250 1.5796 0.07344 0.06712 -0.0892 0.0349 0.9998
15.500 1.5829 0.07593 0.06965 -0.0887 0.0331 0.9998
15.750 1.5859 0.07848 0.07225 -0.0882 0.0315 0.9998
16.000 1.5902 0.08092 0.07476 -0.0878 0.0300 0.9998
16.250 1.5933 0.08348 0.07738 -0.0874 0.0286 0.9998
16.500 1.5946 0.08630 0.08025 -0.0871 0.0273 0.9998
16.750 1.5969 0.08900 0.08302 -0.0868 0.0261 0.9998
17.000 1.5995 0.09172 0.08582 -0.0866 0.0251 0.9998
17.250 1.6017 0.09447 0.08864 -0.0865 0.0240 0.9998
17.500 1.6019 0.09754 0.09177 -0.0865 0.0229 0.9998
17.750 1.6016 0.10068 0.09496 -0.0865 0.0220 0.9998
18.000 1.6030 0.10361 0.09799 -0.0866 0.0212 0.9998
18.250 1.6042 0.10657 0.10104 -0.0867 0.0204 0.9998
18.500 1.6039 0.10980 0.10434 -0.0870 0.0196 0.9998
18.750 1.6030 0.11310 0.10771 -0.0874 0.0189 0.9998
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