AH 95-160 (ah95160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 1,000,000 Max Cl/Cd: 163.17 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah95160-il-1000000-n5.txt Download as CSV file: xf-ah95160-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8635 0.04514 0.04125 -0.0962 0.6884 0.0108
-14.750 -0.8914 0.03562 0.03144 -0.1070 0.6863 0.0108
-14.500 -0.8953 0.03199 0.02763 -0.1101 0.6838 0.0109
-14.250 -0.8948 0.02976 0.02525 -0.1108 0.6819 0.0109
-14.000 -0.8837 0.02811 0.02346 -0.1112 0.6803 0.0110
-13.750 -0.8690 0.02672 0.02194 -0.1114 0.6784 0.0110
-13.500 -0.8517 0.02551 0.02061 -0.1115 0.6765 0.0111
-13.250 -0.8341 0.02426 0.01924 -0.1116 0.6745 0.0112
-13.000 -0.8156 0.02302 0.01788 -0.1117 0.6724 0.0114
-12.750 -0.7949 0.02201 0.01676 -0.1118 0.6703 0.0115
-12.500 -0.7725 0.02116 0.01581 -0.1119 0.6681 0.0117
-12.000 -0.7249 0.01970 0.01420 -0.1122 0.6648 0.0120
-11.750 -0.7001 0.01906 0.01348 -0.1123 0.6634 0.0122
-11.500 -0.6748 0.01845 0.01280 -0.1125 0.6619 0.0124
-11.250 -0.6492 0.01788 0.01216 -0.1126 0.6603 0.0126
-11.000 -0.6232 0.01733 0.01153 -0.1128 0.6587 0.0128
-10.750 -0.5969 0.01681 0.01093 -0.1130 0.6570 0.0130
-10.500 -0.5703 0.01633 0.01037 -0.1132 0.6552 0.0132
-10.250 -0.5434 0.01589 0.00986 -0.1134 0.6534 0.0134
-10.000 -0.5163 0.01549 0.00938 -0.1136 0.6516 0.0136
-9.750 -0.4891 0.01505 0.00887 -0.1139 0.6498 0.0139
-9.500 -0.4620 0.01455 0.00832 -0.1141 0.6486 0.0142
-9.250 -0.4343 0.01414 0.00787 -0.1144 0.6475 0.0145
-9.000 -0.4064 0.01377 0.00747 -0.1147 0.6462 0.0149
-8.750 -0.3783 0.01343 0.00709 -0.1150 0.6448 0.0152
-8.500 -0.3500 0.01311 0.00673 -0.1153 0.6433 0.0156
-8.250 -0.3216 0.01281 0.00638 -0.1156 0.6416 0.0160
-8.000 -0.2931 0.01253 0.00605 -0.1159 0.6399 0.0164
-7.750 -0.2645 0.01226 0.00573 -0.1162 0.6384 0.0167
-7.500 -0.2360 0.01194 0.00538 -0.1166 0.6370 0.0173
-7.250 -0.2073 0.01169 0.00510 -0.1169 0.6355 0.0180
-7.000 -0.1784 0.01147 0.00485 -0.1173 0.6339 0.0186
-6.750 -0.1494 0.01126 0.00461 -0.1176 0.6324 0.0194
-6.500 -0.1203 0.01103 0.00436 -0.1180 0.6313 0.0202
-6.250 -0.0911 0.01081 0.00414 -0.1184 0.6299 0.0213
-6.000 -0.0618 0.01061 0.00393 -0.1188 0.6286 0.0225
-5.750 -0.0325 0.01044 0.00374 -0.1192 0.6273 0.0235
-5.500 -0.0031 0.01024 0.00354 -0.1196 0.6258 0.0252
-5.250 0.0263 0.01009 0.00337 -0.1201 0.6242 0.0268
-5.000 0.0557 0.00993 0.00321 -0.1205 0.6226 0.0289
-4.750 0.0851 0.00979 0.00306 -0.1209 0.6210 0.0313
-4.500 0.1146 0.00965 0.00293 -0.1213 0.6195 0.0344
-4.250 0.1440 0.00954 0.00280 -0.1218 0.6180 0.0377
-4.000 0.1736 0.00943 0.00270 -0.1222 0.6167 0.0413
-3.750 0.2033 0.00931 0.00260 -0.1227 0.6156 0.0452
-3.500 0.2331 0.00921 0.00251 -0.1232 0.6142 0.0494
-3.250 0.2628 0.00910 0.00243 -0.1237 0.6127 0.0541
-3.000 0.2926 0.00901 0.00236 -0.1242 0.6112 0.0586
-2.750 0.3224 0.00893 0.00229 -0.1246 0.6097 0.0634
-2.500 0.3521 0.00885 0.00222 -0.1251 0.6082 0.0686
-2.250 0.3818 0.00878 0.00217 -0.1256 0.6067 0.0739
-2.000 0.4115 0.00871 0.00211 -0.1261 0.6051 0.0808
-1.750 0.4411 0.00866 0.00206 -0.1266 0.6033 0.0869
-1.500 0.4707 0.00861 0.00203 -0.1271 0.6015 0.0963
-1.250 0.5005 0.00853 0.00200 -0.1276 0.6003 0.1089
-0.750 0.5603 0.00830 0.00195 -0.1288 0.5975 0.1636
-0.500 0.5901 0.00814 0.00194 -0.1294 0.5957 0.2117
-0.250 0.6200 0.00795 0.00193 -0.1301 0.5939 0.2786
0.000 0.6498 0.00776 0.00193 -0.1308 0.5922 0.3518
0.250 0.6797 0.00753 0.00195 -0.1316 0.5905 0.4434
0.500 0.7094 0.00737 0.00198 -0.1322 0.5888 0.5184
0.750 0.7390 0.00726 0.00203 -0.1328 0.5870 0.5852
1.000 0.7686 0.00722 0.00208 -0.1333 0.5852 0.6252
1.250 0.7983 0.00715 0.00215 -0.1339 0.5836 0.6720
1.500 0.8276 0.00705 0.00223 -0.1343 0.5820 0.7326
1.750 0.8564 0.00699 0.00232 -0.1346 0.5802 0.7815
2.250 0.9140 0.00702 0.00246 -0.1352 0.5759 0.8280
2.500 0.9427 0.00705 0.00252 -0.1355 0.5737 0.8437
2.750 0.9710 0.00710 0.00259 -0.1357 0.5716 0.8571
3.000 0.9993 0.00715 0.00266 -0.1359 0.5696 0.8689
3.250 1.0279 0.00718 0.00274 -0.1362 0.5676 0.8805
3.500 1.0561 0.00722 0.00282 -0.1364 0.5652 0.8926
3.750 1.0836 0.00726 0.00289 -0.1364 0.5623 0.9040
4.000 1.1108 0.00731 0.00296 -0.1364 0.5591 0.9156
4.750 1.1880 0.00744 0.00317 -0.1354 0.5447 0.9626
5.000 1.2167 0.00751 0.00323 -0.1359 0.5379 0.9998
5.250 1.2450 0.00763 0.00334 -0.1362 0.5289 0.9998
5.500 1.2726 0.00780 0.00347 -0.1365 0.5190 0.9998
5.750 1.2993 0.00800 0.00363 -0.1367 0.5077 0.9998
6.000 1.3259 0.00821 0.00381 -0.1368 0.4963 0.9998
6.250 1.3521 0.00844 0.00400 -0.1368 0.4841 0.9998
6.500 1.3772 0.00873 0.00424 -0.1367 0.4699 0.9998
6.750 1.4011 0.00908 0.00453 -0.1364 0.4534 0.9998
7.000 1.4226 0.00955 0.00490 -0.1357 0.4329 0.9998
7.250 1.4416 0.01013 0.00537 -0.1346 0.4061 0.9998
7.500 1.4555 0.01094 0.00601 -0.1328 0.3738 0.9998
7.750 1.4649 0.01190 0.00679 -0.1302 0.3410 0.9998
8.000 1.4676 0.01295 0.00770 -0.1266 0.3110 0.9998
8.250 1.4693 0.01426 0.00888 -0.1233 0.2821 0.9998
8.500 1.4715 0.01576 0.01026 -0.1205 0.2568 0.9998
8.750 1.4738 0.01746 0.01186 -0.1182 0.2338 0.9998
9.000 1.4774 0.01922 0.01354 -0.1163 0.2140 0.9998
9.250 1.4815 0.02103 0.01528 -0.1145 0.1962 0.9998
9.500 1.4850 0.02291 0.01710 -0.1128 0.1796 0.9998
9.750 1.4888 0.02480 0.01894 -0.1111 0.1649 0.9998
10.000 1.4923 0.02669 0.02078 -0.1095 0.1515 0.9998
10.250 1.4962 0.02856 0.02261 -0.1079 0.1398 0.9998
10.500 1.4997 0.03046 0.02447 -0.1062 0.1292 0.9998
10.750 1.5037 0.03230 0.02629 -0.1047 0.1193 0.9998
11.000 1.5094 0.03402 0.02799 -0.1033 0.1111 0.9998
11.250 1.5136 0.03589 0.02984 -0.1018 0.1033 0.9998
11.500 1.5204 0.03758 0.03152 -0.1006 0.0969 0.9998
11.750 1.5266 0.03937 0.03331 -0.0994 0.0912 0.9998
12.000 1.5335 0.04111 0.03506 -0.0983 0.0854 0.9998
12.250 1.5398 0.04292 0.03686 -0.0971 0.0800 0.9998
12.500 1.5467 0.04470 0.03865 -0.0961 0.0753 0.9998
12.750 1.5535 0.04649 0.04044 -0.0951 0.0707 0.9998
13.000 1.5606 0.04832 0.04228 -0.0942 0.0668 0.9998
13.250 1.5660 0.05029 0.04424 -0.0931 0.0622 0.9998
13.500 1.5740 0.05202 0.04600 -0.0923 0.0588 0.9998
13.750 1.5790 0.05408 0.04806 -0.0913 0.0551 0.9998
14.000 1.5862 0.05592 0.04993 -0.0905 0.0520 0.9998
14.250 1.5926 0.05788 0.05190 -0.0897 0.0489 0.9998
14.500 1.5974 0.06002 0.05405 -0.0889 0.0459 0.9998
14.750 1.6046 0.06188 0.05594 -0.0882 0.0434 0.9998
15.000 1.6091 0.06407 0.05815 -0.0874 0.0409 0.9998
15.250 1.6147 0.06617 0.06027 -0.0867 0.0388 0.9998
15.500 1.6211 0.06817 0.06231 -0.0861 0.0368 0.9998
15.750 1.6246 0.07054 0.06471 -0.0855 0.0347 0.9998
16.000 1.6299 0.07269 0.06689 -0.0849 0.0332 0.9998
16.250 1.6354 0.07483 0.06907 -0.0844 0.0318 0.9998
16.500 1.6389 0.07723 0.07150 -0.0839 0.0303 0.9998
16.750 1.6425 0.07961 0.07392 -0.0833 0.0289 0.9998
17.000 1.6469 0.08195 0.07631 -0.0830 0.0278 0.9998
17.250 1.6506 0.08437 0.07878 -0.0826 0.0266 0.9998
17.500 1.6539 0.08684 0.08128 -0.0822 0.0254 0.9998
17.750 1.6552 0.08956 0.08405 -0.0819 0.0244 0.9998
18.000 1.6592 0.09196 0.08650 -0.0817 0.0235 0.9998
18.250 1.6613 0.09464 0.08924 -0.0815 0.0226 0.9998
18.500 1.6629 0.09737 0.09202 -0.0814 0.0216 0.9998
18.750 1.6636 0.10024 0.09493 -0.0813 0.0207 0.9998
19.000 1.6655 0.10299 0.09774 -0.0813 0.0201 0.9998
19.250 1.6677 0.10568 0.10049 -0.0814 0.0193 0.9998
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