AH 94-145 (ah94145-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 200,000 Max Cl/Cd: 75.69 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94145-il-200000.txt Download as CSV file: xf-ah94145-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1599 0.10559 0.10134 -0.0694 0.7882 0.0519
-9.750 -0.1716 0.10162 0.09743 -0.0778 0.7853 0.0534
-9.500 -0.1695 0.09704 0.09286 -0.0805 0.7827 0.0538
-9.250 -0.1517 0.09441 0.09019 -0.0776 0.7804 0.0547
-9.000 -0.1383 0.09217 0.08792 -0.0770 0.7782 0.0560
-8.750 -0.1292 0.08955 0.08528 -0.0782 0.7761 0.0579
-8.500 -0.1238 0.08618 0.08195 -0.0816 0.7736 0.0605
-8.250 -0.1397 0.07969 0.07556 -0.0980 0.7702 0.0628
-8.000 -0.1359 0.07395 0.06982 -0.1025 0.7676 0.0636
-7.750 -0.1211 0.07280 0.06868 -0.0972 0.7653 0.0644
-7.500 -0.1085 0.07052 0.06637 -0.0973 0.7630 0.0656
-7.250 -0.0974 0.06728 0.06309 -0.1007 0.7610 0.0672
-7.000 -0.0860 0.06296 0.05872 -0.1069 0.7588 0.0699
-6.750 -0.0814 0.05390 0.04920 -0.1211 0.7560 0.0750
-6.500 -0.0635 0.05141 0.04679 -0.1211 0.7533 0.0762
-6.250 -0.0525 0.03849 0.03282 -0.1271 0.7509 0.0527
-6.000 -0.0314 0.03493 0.02896 -0.1282 0.7485 0.0520
-5.750 -0.0083 0.03131 0.02489 -0.1291 0.7465 0.0506
-5.500 0.0171 0.02813 0.02117 -0.1298 0.7447 0.0501
-5.250 0.0441 0.02610 0.01868 -0.1302 0.7429 0.0511
-5.000 0.0722 0.02514 0.01731 -0.1306 0.7402 0.0535
-4.750 0.0984 0.02386 0.01604 -0.1311 0.7373 0.0564
-4.500 0.1262 0.02313 0.01519 -0.1313 0.7346 0.0594
-4.250 0.1547 0.02249 0.01429 -0.1315 0.7324 0.0633
-4.000 0.1821 0.02178 0.01363 -0.1318 0.7304 0.0685
-3.750 0.2108 0.02146 0.01312 -0.1319 0.7287 0.0740
-3.500 0.2383 0.02084 0.01254 -0.1321 0.7271 0.0820
-3.250 0.2648 0.02050 0.01224 -0.1324 0.7241 0.0903
-3.000 0.2918 0.02045 0.01220 -0.1327 0.7209 0.1004
-2.750 0.3190 0.02012 0.01195 -0.1330 0.7183 0.1123
-2.500 0.3471 0.01986 0.01174 -0.1334 0.7161 0.1259
-2.250 0.3757 0.01961 0.01152 -0.1338 0.7142 0.1424
-2.000 0.4048 0.01936 0.01131 -0.1343 0.7123 0.1661
-1.750 0.4346 0.01887 0.01116 -0.1351 0.7107 0.2359
-1.500 0.4587 0.01796 0.01178 -0.1358 0.7074 0.6277
-1.250 0.4739 0.01818 0.01247 -0.1331 0.7041 0.7660
-1.000 0.4884 0.01850 0.01291 -0.1299 0.7013 0.8389
-0.750 0.5041 0.01870 0.01311 -0.1269 0.6989 0.8855
-0.500 0.5188 0.01873 0.01309 -0.1234 0.6970 0.9226
-0.250 0.5377 0.01868 0.01296 -0.1208 0.6953 0.9595
0.000 0.5815 0.01867 0.01283 -0.1239 0.6939 0.9990
0.250 0.5978 0.01988 0.01409 -0.1238 0.6884 0.9998
0.500 0.6236 0.02039 0.01455 -0.1244 0.6849 0.9998
0.750 0.6531 0.02061 0.01468 -0.1251 0.6826 0.9998
1.000 0.6838 0.02075 0.01473 -0.1259 0.6808 0.9998
1.250 0.7149 0.02089 0.01478 -0.1266 0.6794 0.9998
1.500 0.7460 0.02104 0.01485 -0.1274 0.6780 0.9998
1.750 0.7578 0.02285 0.01677 -0.1270 0.6704 0.9998
2.000 0.7839 0.02338 0.01727 -0.1274 0.6674 0.9998
2.250 0.8138 0.02353 0.01737 -0.1280 0.6654 0.9998
2.500 0.8454 0.02352 0.01732 -0.1286 0.6639 0.9998
2.750 0.8776 0.02351 0.01725 -0.1293 0.6627 0.9998
3.000 0.9088 0.02361 0.01731 -0.1299 0.6615 0.9998
3.250 0.9073 0.02638 0.02024 -0.1283 0.6509 0.9998
3.500 0.9379 0.02640 0.02024 -0.1288 0.6491 0.9998
3.750 0.9705 0.02625 0.02008 -0.1294 0.6478 0.9998
4.000 1.0043 0.02602 0.01981 -0.1301 0.6467 0.9998
4.250 1.0373 0.02588 0.01965 -0.1307 0.6456 0.9998
4.500 1.0281 0.02902 0.02296 -0.1281 0.6337 0.9998
4.750 1.0624 0.02864 0.02258 -0.1287 0.6324 0.9998
5.000 1.0983 0.02811 0.02205 -0.1295 0.6314 0.9998
5.250 1.0880 0.03121 0.02527 -0.1266 0.6198 0.9998
5.500 1.1234 0.03061 0.02469 -0.1272 0.6183 0.9998
5.750 1.1615 0.02976 0.02387 -0.1280 0.6173 0.9998
6.000 1.2025 0.02866 0.02277 -0.1291 0.6164 0.9998
6.250 1.2450 0.02736 0.02148 -0.1304 0.6152 0.9998
6.500 1.2883 0.02596 0.02006 -0.1317 0.6135 0.9998
6.750 1.2908 0.02736 0.02161 -0.1291 0.6032 0.9998
7.000 1.3400 0.02527 0.01952 -0.1308 0.6012 0.9998
7.250 1.3886 0.02336 0.01755 -0.1328 0.5989 0.9998
7.500 1.3962 0.02423 0.01860 -0.1303 0.5894 0.9998
7.750 1.4384 0.02279 0.01715 -0.1317 0.5857 0.9998
8.000 1.4599 0.02274 0.01721 -0.1307 0.5787 0.9998
8.250 1.4892 0.02213 0.01667 -0.1307 0.5723 0.9998
8.500 1.5180 0.02155 0.01615 -0.1305 0.5654 0.9998
8.750 1.5417 0.02114 0.01582 -0.1296 0.5563 0.9998
9.000 1.5574 0.02120 0.01600 -0.1278 0.5456 0.9998
9.250 1.5773 0.02100 0.01586 -0.1264 0.5343 0.9998
9.500 1.5917 0.02103 0.01594 -0.1242 0.5213 0.9998
9.750 1.5992 0.02150 0.01647 -0.1214 0.5059 0.9998
10.000 1.6034 0.02235 0.01738 -0.1185 0.4876 0.9998
10.250 1.6091 0.02325 0.01823 -0.1159 0.4648 0.9998
10.500 1.6079 0.02481 0.01971 -0.1131 0.4360 0.9998
10.750 1.6021 0.02686 0.02158 -0.1100 0.4016 0.9998
11.000 1.5900 0.02958 0.02409 -0.1067 0.3652 0.9998
11.250 1.5741 0.03278 0.02707 -0.1034 0.3313 0.9998
11.500 1.5575 0.03618 0.03027 -0.1003 0.3002 0.9998
11.750 1.5418 0.03962 0.03355 -0.0975 0.2714 0.9998
12.000 1.5278 0.04308 0.03686 -0.0951 0.2450 0.9998
12.250 1.5149 0.04661 0.04024 -0.0929 0.2214 0.9998
12.500 1.5059 0.04991 0.04343 -0.0911 0.1990 0.9998
12.750 1.4973 0.05327 0.04667 -0.0895 0.1800 0.9998
13.000 1.4903 0.05656 0.04986 -0.0880 0.1637 0.9998
13.250 1.4854 0.05969 0.05290 -0.0867 0.1493 0.9998
13.500 1.4824 0.06269 0.05586 -0.0856 0.1365 0.9998
13.750 1.4813 0.06554 0.05869 -0.0846 0.1252 0.9998
14.000 1.4807 0.06834 0.06150 -0.0836 0.1155 0.9998
14.250 1.4783 0.07135 0.06444 -0.0826 0.1076 0.9998
14.500 1.4798 0.07402 0.06715 -0.0819 0.0998 0.9998
14.750 1.4803 0.07674 0.06986 -0.0811 0.0934 0.9998
15.000 1.4818 0.07945 0.07261 -0.0805 0.0874 0.9998
15.250 1.4831 0.08204 0.07519 -0.0797 0.0822 0.9998
15.500 1.4862 0.08463 0.07786 -0.0792 0.0774 0.9998
15.750 1.4878 0.08703 0.08016 -0.0783 0.0730 0.9998
16.000 1.4919 0.08960 0.08291 -0.0780 0.0693 0.9998
16.250 1.4949 0.09221 0.08556 -0.0777 0.0658 0.9998
16.500 1.4998 0.09411 0.08738 -0.0767 0.0624 0.9998
16.750 1.5031 0.09682 0.09027 -0.0766 0.0597 0.9998
17.000 1.5066 0.09937 0.09289 -0.0765 0.0569 0.9998
17.250 1.5117 0.10144 0.09491 -0.0760 0.0544 0.9998
17.500 1.5168 0.10361 0.09721 -0.0755 0.0521 0.9998
17.750 1.5193 0.10642 0.10016 -0.0756 0.0499 0.9998
18.000 1.5226 0.10903 0.10283 -0.0757 0.0479 0.9998
18.250 1.5305 0.11053 0.10426 -0.0751 0.0458 0.9998
18.500 1.5329 0.11323 0.10712 -0.0751 0.0442 0.9998
18.750 1.5329 0.11651 0.11059 -0.0757 0.0426 0.9998
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