AH 94-145 (ah94145-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 200,000 Max Cl/Cd: 81.3 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94145-il-200000-n5.txt Download as CSV file: xf-ah94145-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1891 0.08954 0.08472 -0.0710 0.7215 0.0229
-9.250 -0.1884 0.08487 0.08007 -0.0740 0.7195 0.0230
-9.000 -0.1873 0.08034 0.07555 -0.0770 0.7175 0.0229
-8.750 -0.1873 0.07545 0.07067 -0.0806 0.7155 0.0228
-8.500 -0.1896 0.06974 0.06498 -0.0854 0.7135 0.0226
-8.250 -0.1977 0.06184 0.05708 -0.0949 0.7116 0.0224
-8.000 -0.2405 0.03563 0.02978 -0.1173 0.7103 0.0222
-7.750 -0.2300 0.02895 0.02215 -0.1198 0.7081 0.0229
-7.500 -0.2080 0.02626 0.01894 -0.1207 0.7058 0.0239
-7.250 -0.1822 0.02556 0.01818 -0.1212 0.7036 0.0246
-7.000 -0.1563 0.02454 0.01697 -0.1217 0.7016 0.0256
-6.750 -0.1302 0.02316 0.01529 -0.1221 0.6996 0.0266
-6.500 -0.1036 0.02182 0.01360 -0.1224 0.6977 0.0276
-6.250 -0.0766 0.02088 0.01250 -0.1228 0.6959 0.0285
-6.000 -0.0492 0.02027 0.01180 -0.1231 0.6942 0.0296
-5.750 -0.0214 0.01970 0.01112 -0.1234 0.6921 0.0313
-5.500 0.0065 0.01906 0.01035 -0.1237 0.6900 0.0333
-5.250 0.0344 0.01863 0.00992 -0.1242 0.6880 0.0351
-5.000 0.0625 0.01813 0.00934 -0.1245 0.6859 0.0373
-4.750 0.0907 0.01766 0.00880 -0.1248 0.6838 0.0399
-4.500 0.1192 0.01737 0.00847 -0.1251 0.6818 0.0433
-4.250 0.1477 0.01699 0.00803 -0.1255 0.6801 0.0470
-4.000 0.1764 0.01673 0.00772 -0.1258 0.6786 0.0516
-3.750 0.2052 0.01648 0.00744 -0.1262 0.6772 0.0569
-3.500 0.2338 0.01630 0.00724 -0.1266 0.6750 0.0631
-3.250 0.2623 0.01608 0.00707 -0.1271 0.6728 0.0702
-3.000 0.2911 0.01588 0.00688 -0.1275 0.6705 0.0781
-2.750 0.3199 0.01576 0.00671 -0.1279 0.6684 0.0869
-2.500 0.3489 0.01556 0.00654 -0.1284 0.6666 0.0971
-2.250 0.3781 0.01540 0.00639 -0.1289 0.6650 0.1089
-2.000 0.4074 0.01524 0.00625 -0.1294 0.6635 0.1251
-1.750 0.4368 0.01507 0.00613 -0.1300 0.6620 0.1512
-1.500 0.4661 0.01483 0.00609 -0.1307 0.6602 0.2066
-1.250 0.4949 0.01445 0.00616 -0.1316 0.6577 0.3288
-1.000 0.5236 0.01398 0.00629 -0.1324 0.6555 0.5044
-0.750 0.5500 0.01372 0.00646 -0.1322 0.6535 0.6412
-0.500 0.5741 0.01363 0.00661 -0.1312 0.6514 0.7248
-0.250 0.5959 0.01361 0.00673 -0.1295 0.6495 0.7880
0.000 0.6182 0.01365 0.00679 -0.1280 0.6478 0.8342
0.250 0.6398 0.01371 0.00684 -0.1264 0.6463 0.8741
0.500 0.6556 0.01373 0.00687 -0.1233 0.6449 0.9211
0.750 0.6752 0.01370 0.00692 -0.1212 0.6423 0.9696
1.000 0.7098 0.01378 0.00698 -0.1230 0.6397 0.9998
1.250 0.7389 0.01394 0.00710 -0.1236 0.6373 0.9998
1.500 0.7683 0.01409 0.00720 -0.1243 0.6352 0.9998
1.750 0.7980 0.01423 0.00729 -0.1250 0.6334 0.9998
2.000 0.8280 0.01436 0.00737 -0.1257 0.6318 0.9998
2.250 0.8583 0.01447 0.00742 -0.1264 0.6302 0.9998
2.500 0.8870 0.01468 0.00762 -0.1270 0.6280 0.9998
2.750 0.9142 0.01497 0.00797 -0.1274 0.6250 0.9998
3.000 0.9421 0.01521 0.00822 -0.1278 0.6223 0.9998
3.250 0.9707 0.01539 0.00840 -0.1283 0.6199 0.9998
3.500 0.9997 0.01553 0.00855 -0.1288 0.6178 0.9998
3.750 1.0292 0.01565 0.00865 -0.1294 0.6160 0.9998
4.000 1.0592 0.01575 0.00872 -0.1300 0.6143 0.9998
4.250 1.0848 0.01610 0.00917 -0.1301 0.6111 0.9998
4.500 1.1106 0.01641 0.00955 -0.1302 0.6077 0.9998
4.750 1.1379 0.01661 0.00979 -0.1305 0.6047 0.9998
5.000 1.1663 0.01672 0.00994 -0.1308 0.6022 0.9998
5.250 1.1959 0.01676 0.00998 -0.1313 0.6000 0.9998
5.500 1.2224 0.01697 0.01025 -0.1314 0.5966 0.9998
5.750 1.2458 0.01729 0.01069 -0.1311 0.5915 0.9998
6.000 1.2734 0.01730 0.01073 -0.1313 0.5873 0.9998
6.250 1.3039 0.01707 0.01049 -0.1317 0.5832 0.9998
6.500 1.3241 0.01736 0.01092 -0.1308 0.5747 0.9998
6.750 1.3537 0.01705 0.01059 -0.1310 0.5685 0.9998
7.000 1.3731 0.01736 0.01103 -0.1300 0.5587 0.9998
7.250 1.3979 0.01737 0.01108 -0.1296 0.5506 0.9998
7.500 1.4202 0.01752 0.01130 -0.1289 0.5412 0.9998
7.750 1.4405 0.01779 0.01165 -0.1280 0.5312 0.9998
8.000 1.4617 0.01798 0.01189 -0.1272 0.5209 0.9998
8.250 1.4813 0.01823 0.01216 -0.1260 0.5090 0.9998
8.500 1.4964 0.01864 0.01261 -0.1243 0.4944 0.9998
8.750 1.5070 0.01921 0.01319 -0.1219 0.4768 0.9998
9.000 1.5152 0.02001 0.01394 -0.1195 0.4540 0.9998
9.250 1.5189 0.02116 0.01500 -0.1167 0.4263 0.9998
9.500 1.5162 0.02289 0.01657 -0.1136 0.3944 0.9998
9.750 1.5082 0.02523 0.01873 -0.1105 0.3619 0.9998
10.000 1.4983 0.02794 0.02128 -0.1075 0.3312 0.9998
10.250 1.4883 0.03081 0.02401 -0.1048 0.3028 0.9998
10.500 1.4792 0.03370 0.02678 -0.1024 0.2770 0.9998
10.750 1.4706 0.03661 0.02957 -0.1000 0.2530 0.9998
11.000 1.4642 0.03939 0.03226 -0.0980 0.2308 0.9998
11.250 1.4589 0.04213 0.03493 -0.0960 0.2107 0.9998
11.500 1.4547 0.04488 0.03760 -0.0944 0.1923 0.9998
11.750 1.4528 0.04750 0.04017 -0.0929 0.1753 0.9998
12.000 1.4518 0.05009 0.04270 -0.0916 0.1597 0.9998
12.250 1.4519 0.05264 0.04521 -0.0903 0.1460 0.9998
12.500 1.4523 0.05520 0.04775 -0.0892 0.1337 0.9998
12.750 1.4536 0.05771 0.05024 -0.0882 0.1225 0.9998
13.000 1.4563 0.06011 0.05266 -0.0873 0.1128 0.9998
13.250 1.4590 0.06255 0.05511 -0.0865 0.1044 0.9998
13.500 1.4604 0.06517 0.05772 -0.0857 0.0968 0.9998
13.750 1.4647 0.06750 0.06010 -0.0850 0.0899 0.9998
14.000 1.4659 0.07019 0.06280 -0.0843 0.0840 0.9998
14.250 1.4702 0.07255 0.06524 -0.0837 0.0782 0.9998
14.750 1.4754 0.07779 0.07057 -0.0827 0.0687 0.9998
15.000 1.4771 0.08055 0.07336 -0.0822 0.0646 0.9998
15.250 1.4790 0.08330 0.07618 -0.0818 0.0610 0.9998
15.500 1.4821 0.08593 0.07888 -0.0815 0.0573 0.9998
15.750 1.4821 0.08900 0.08200 -0.0813 0.0543 0.9998
16.000 1.4845 0.09176 0.08485 -0.0811 0.0517 0.9998
16.250 1.4867 0.09459 0.08777 -0.0810 0.0489 0.9998
16.500 1.4870 0.09769 0.09092 -0.0810 0.0466 0.9998
16.750 1.4864 0.10092 0.09421 -0.0810 0.0447 0.9998
17.000 1.4890 0.10374 0.09715 -0.0811 0.0426 0.9998
17.250 1.4897 0.10685 0.10036 -0.0813 0.0407 0.9998
17.500 1.4889 0.11022 0.10379 -0.0817 0.0391 0.9998
17.750 1.4875 0.11368 0.10731 -0.0821 0.0377 0.9998
18.000 1.4894 0.11668 0.11045 -0.0826 0.0362 0.9998
18.250 1.4899 0.11992 0.11379 -0.0832 0.0347 0.9998
18.500 1.4893 0.12335 0.11731 -0.0839 0.0335 0.9998
18.750 1.4871 0.12704 0.12106 -0.0849 0.0324 0.9998
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