AH 95-160 (ah95160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 1,000,000 Max Cl/Cd: 173.08 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah95160-il-1000000.txt Download as CSV file: xf-ah95160-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 95-160
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7377 0.03856 0.03482 -0.1059 0.7069 0.0144
-13.250 -0.7450 0.03408 0.03014 -0.1106 0.7042 0.0144
-13.000 -0.7465 0.03157 0.02747 -0.1119 0.7011 0.0145
-12.750 -0.7368 0.02973 0.02549 -0.1125 0.6990 0.0146
-12.500 -0.7229 0.02817 0.02381 -0.1129 0.6974 0.0147
-12.250 -0.7067 0.02675 0.02227 -0.1131 0.6955 0.0149
-12.000 -0.6885 0.02547 0.02086 -0.1133 0.6936 0.0151
-11.750 -0.6688 0.02429 0.01954 -0.1135 0.6917 0.0153
-11.500 -0.6481 0.02316 0.01828 -0.1136 0.6897 0.0155
-11.250 -0.6261 0.02216 0.01713 -0.1138 0.6878 0.0157
-11.000 -0.6033 0.02123 0.01606 -0.1139 0.6855 0.0160
-10.750 -0.5796 0.02042 0.01510 -0.1140 0.6829 0.0162
-10.500 -0.5547 0.01967 0.01425 -0.1142 0.6816 0.0164
-10.250 -0.5291 0.01904 0.01352 -0.1144 0.6802 0.0166
-10.000 -0.5065 0.01771 0.01204 -0.1145 0.6787 0.0169
-9.750 -0.4814 0.01687 0.01113 -0.1147 0.6771 0.0173
-9.500 -0.4547 0.01634 0.01054 -0.1149 0.6754 0.0177
-9.250 -0.4276 0.01590 0.01006 -0.1152 0.6738 0.0181
-9.000 -0.4001 0.01548 0.00958 -0.1154 0.6721 0.0185
-8.750 -0.3726 0.01506 0.00908 -0.1157 0.6703 0.0190
-8.500 -0.3451 0.01466 0.00858 -0.1159 0.6683 0.0194
-8.250 -0.3172 0.01434 0.00818 -0.1162 0.6659 0.0197
-8.000 -0.2902 0.01362 0.00740 -0.1164 0.6650 0.0203
-7.750 -0.2622 0.01316 0.00692 -0.1168 0.6639 0.0209
-7.500 -0.2337 0.01284 0.00658 -0.1171 0.6625 0.0216
-7.250 -0.2050 0.01253 0.00624 -0.1174 0.6610 0.0223
-7.000 -0.1762 0.01226 0.00591 -0.1178 0.6594 0.0230
-6.750 -0.1477 0.01185 0.00546 -0.1181 0.6577 0.0239
-6.500 -0.1189 0.01155 0.00515 -0.1185 0.6563 0.0251
-6.250 -0.0898 0.01135 0.00492 -0.1189 0.6548 0.0263
-6.000 -0.0607 0.01113 0.00465 -0.1192 0.6533 0.0276
-5.750 -0.0318 0.01087 0.00438 -0.1196 0.6515 0.0294
-5.500 -0.0026 0.01076 0.00423 -0.1200 0.6493 0.0312
-5.250 0.0268 0.01049 0.00397 -0.1205 0.6483 0.0336
-5.000 0.0563 0.01032 0.00380 -0.1209 0.6471 0.0362
-4.750 0.0858 0.01011 0.00362 -0.1213 0.6458 0.0397
-4.500 0.1154 0.00996 0.00347 -0.1218 0.6444 0.0436
-4.250 0.1450 0.00984 0.00336 -0.1223 0.6429 0.0478
-4.000 0.1746 0.00968 0.00323 -0.1227 0.6414 0.0526
-3.750 0.2043 0.00958 0.00311 -0.1232 0.6399 0.0570
-3.500 0.2340 0.00947 0.00302 -0.1237 0.6383 0.0624
-3.250 0.2637 0.00937 0.00292 -0.1241 0.6368 0.0676
-3.000 0.2933 0.00932 0.00287 -0.1246 0.6351 0.0729
-2.750 0.3229 0.00929 0.00283 -0.1251 0.6330 0.0789
-2.500 0.3528 0.00920 0.00276 -0.1256 0.6321 0.0848
-2.250 0.3826 0.00907 0.00268 -0.1261 0.6308 0.0933
-2.000 0.4124 0.00897 0.00261 -0.1266 0.6294 0.1028
-1.750 0.4423 0.00884 0.00254 -0.1272 0.6278 0.1190
-1.500 0.4721 0.00867 0.00249 -0.1278 0.6262 0.1542
-1.250 0.5020 0.00840 0.00244 -0.1285 0.6247 0.2265
-1.000 0.5319 0.00804 0.00240 -0.1294 0.6232 0.3385
-0.750 0.5618 0.00764 0.00239 -0.1302 0.6216 0.4768
-0.500 0.5916 0.00740 0.00243 -0.1309 0.6199 0.5826
-0.250 0.6212 0.00735 0.00250 -0.1314 0.6178 0.6441
0.000 0.6509 0.00732 0.00256 -0.1319 0.6164 0.6829
0.250 0.6804 0.00726 0.00260 -0.1324 0.6151 0.7168
0.500 0.7099 0.00722 0.00265 -0.1328 0.6136 0.7437
0.750 0.7393 0.00720 0.00269 -0.1332 0.6119 0.7709
1.000 0.7685 0.00719 0.00273 -0.1335 0.6101 0.7929
1.250 0.7973 0.00718 0.00278 -0.1337 0.6084 0.8192
1.500 0.8251 0.00717 0.00285 -0.1337 0.6068 0.8507
1.750 0.8526 0.00719 0.00291 -0.1337 0.6051 0.8775
2.000 0.8800 0.00724 0.00298 -0.1336 0.6030 0.8955
2.250 0.9070 0.00732 0.00307 -0.1334 0.6009 0.9110
2.500 0.9332 0.00731 0.00312 -0.1331 0.5994 0.9255
2.750 0.9588 0.00730 0.00316 -0.1326 0.5976 0.9399
3.000 0.9834 0.00729 0.00318 -0.1320 0.5956 0.9559
3.250 1.0093 0.00726 0.00318 -0.1316 0.5936 0.9760
3.500 1.0423 0.00727 0.00318 -0.1329 0.5915 0.9998
3.750 1.0728 0.00733 0.00323 -0.1337 0.5892 0.9998
4.000 1.1030 0.00746 0.00331 -0.1344 0.5862 0.9998
4.250 1.1329 0.00750 0.00338 -0.1351 0.5836 0.9998
4.500 1.1626 0.00752 0.00343 -0.1357 0.5803 0.9998
4.750 1.1920 0.00754 0.00345 -0.1363 0.5763 0.9998
5.000 1.2209 0.00762 0.00349 -0.1368 0.5718 0.9998
5.250 1.2498 0.00767 0.00357 -0.1373 0.5671 0.9998
5.500 1.2787 0.00770 0.00362 -0.1377 0.5616 0.9998
5.750 1.3066 0.00781 0.00370 -0.1380 0.5559 0.9998
6.000 1.3353 0.00788 0.00380 -0.1385 0.5511 0.9998
6.250 1.3635 0.00797 0.00391 -0.1388 0.5454 0.9998
6.500 1.3907 0.00812 0.00403 -0.1390 0.5397 0.9998
6.750 1.4189 0.00821 0.00417 -0.1394 0.5339 0.9998
7.000 1.4458 0.00836 0.00431 -0.1395 0.5271 0.9998
7.250 1.4729 0.00851 0.00448 -0.1397 0.5198 0.9998
7.500 1.4984 0.00872 0.00467 -0.1397 0.5105 0.9998
7.750 1.5240 0.00892 0.00487 -0.1396 0.4990 0.9998
8.000 1.5477 0.00922 0.00513 -0.1393 0.4847 0.9998
8.250 1.5694 0.00960 0.00546 -0.1386 0.4673 0.9998
8.500 1.5883 0.01011 0.00589 -0.1374 0.4453 0.9998
8.750 1.6018 0.01086 0.00650 -0.1355 0.4161 0.9998
9.000 1.6061 0.01186 0.00734 -0.1320 0.3815 0.9998
9.250 1.6030 0.01322 0.00852 -0.1276 0.3476 0.9998
9.500 1.5992 0.01489 0.01006 -0.1238 0.3170 0.9998
9.750 1.5949 0.01692 0.01195 -0.1206 0.2886 0.9998
10.000 1.5904 0.01921 0.01412 -0.1178 0.2632 0.9998
10.250 1.5879 0.02149 0.01631 -0.1155 0.2399 0.9998
10.500 1.5841 0.02393 0.01866 -0.1132 0.2191 0.9998
10.750 1.5816 0.02627 0.02092 -0.1110 0.2009 0.9998
11.000 1.5803 0.02852 0.02311 -0.1089 0.1847 0.9998
11.250 1.5790 0.03076 0.02530 -0.1069 0.1701 0.9998
11.500 1.5778 0.03300 0.02750 -0.1049 0.1565 0.9998
11.750 1.5774 0.03521 0.02966 -0.1031 0.1440 0.9998
12.000 1.5788 0.03732 0.03173 -0.1014 0.1327 0.9998
12.250 1.5818 0.03936 0.03375 -0.1000 0.1231 0.9998
12.500 1.5852 0.04138 0.03575 -0.0986 0.1143 0.9998
12.750 1.5868 0.04360 0.03793 -0.0972 0.1057 0.9998
13.000 1.5923 0.04549 0.03982 -0.0961 0.0988 0.9998
13.250 1.5956 0.04762 0.04194 -0.0949 0.0919 0.9998
13.500 1.6009 0.04960 0.04392 -0.0938 0.0862 0.9998
13.750 1.6055 0.05161 0.04593 -0.0928 0.0805 0.9998
14.000 1.6101 0.05370 0.04802 -0.0918 0.0756 0.9998
14.250 1.6146 0.05579 0.05011 -0.0908 0.0707 0.9998
14.500 1.6201 0.05782 0.05216 -0.0900 0.0665 0.9998
14.750 1.6228 0.06015 0.05448 -0.0890 0.0620 0.9998
15.000 1.6297 0.06204 0.05640 -0.0883 0.0587 0.9998
15.250 1.6318 0.06446 0.05883 -0.0874 0.0550 0.9998
15.500 1.6372 0.06656 0.06096 -0.0867 0.0520 0.9998
15.750 1.6414 0.06880 0.06322 -0.0860 0.0490 0.9998
16.000 1.6432 0.07135 0.06578 -0.0853 0.0460 0.9998
16.250 1.6491 0.07342 0.06790 -0.0848 0.0440 0.9998
16.500 1.6512 0.07594 0.07044 -0.0842 0.0417 0.9998
16.750 1.6529 0.07853 0.07305 -0.0836 0.0394 0.9998
17.000 1.6580 0.08075 0.07533 -0.0832 0.0378 0.9998
17.250 1.6597 0.08340 0.07802 -0.0827 0.0361 0.9998
17.500 1.6602 0.08618 0.08082 -0.0823 0.0342 0.9998
17.750 1.6632 0.08871 0.08341 -0.0820 0.0331 0.9998
18.000 1.6661 0.09123 0.08598 -0.0817 0.0318 0.9998
18.250 1.6667 0.09407 0.08886 -0.0815 0.0305 0.9998
18.500 1.6646 0.09727 0.09210 -0.0813 0.0291 0.9998
18.750 1.6678 0.09981 0.09471 -0.0812 0.0282 0.9998
19.000 1.6695 0.10260 0.09757 -0.0813 0.0272 0.9998
19.250 1.6704 0.10545 0.10046 -0.0813 0.0262 0.9998
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Polar data table (+)
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