AH 93-157 (ah93157-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 200,000 Max Cl/Cd: 74.88 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93157-il-200000.txt Download as CSV file: xf-ah93157-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1738 0.11115 0.10750 -0.0925 0.9435 0.0561
-12.000 -0.1657 0.10651 0.10282 -0.0979 0.9381 0.0592
-11.750 -0.1824 0.09982 0.09615 -0.1094 0.9302 0.0612
-11.500 -0.1645 0.09492 0.09120 -0.1101 0.9268 0.0625
-11.250 -0.1406 0.09342 0.08965 -0.1092 0.9216 0.0646
-11.000 -0.1309 0.09036 0.08657 -0.1111 0.9159 0.0669
-10.750 -0.1268 0.08652 0.08269 -0.1142 0.9110 0.0691
-10.500 -0.1629 0.07952 0.07574 -0.1229 0.9018 0.0728
-10.250 -0.1966 0.07344 0.06958 -0.1285 0.8942 0.0730
-10.000 -0.2314 0.07066 0.06671 -0.1274 0.8860 0.0732
-9.750 -0.2588 0.06881 0.06471 -0.1242 0.8798 0.0733
-9.500 -0.2010 0.06280 0.05893 -0.1276 0.8801 0.0761
-9.250 -0.2096 0.06038 0.05649 -0.1263 0.8748 0.0770
-9.000 -0.2231 0.05816 0.05422 -0.1239 0.8690 0.0779
-8.750 -0.3260 0.04598 0.04098 -0.1135 0.8608 0.0503
-8.500 -0.3263 0.04255 0.03744 -0.1112 0.8564 0.0487
-8.250 -0.3306 0.03887 0.03342 -0.1077 0.8520 0.0464
-8.000 -0.3300 0.03568 0.02977 -0.1043 0.8485 0.0459
-7.750 -0.3224 0.03370 0.02748 -0.1017 0.8446 0.0466
-7.500 -0.3125 0.03175 0.02520 -0.0993 0.8405 0.0471
-7.250 -0.2981 0.02977 0.02284 -0.0972 0.8369 0.0477
-7.000 -0.2793 0.02807 0.02079 -0.0957 0.8339 0.0486
-6.750 -0.2577 0.02693 0.01929 -0.0945 0.8315 0.0502
-6.500 -0.2403 0.02562 0.01782 -0.0932 0.8271 0.0522
-6.250 -0.2184 0.02480 0.01700 -0.0925 0.8234 0.0547
-6.000 -0.1936 0.02398 0.01605 -0.0920 0.8203 0.0572
-5.750 -0.1679 0.02331 0.01521 -0.0915 0.8178 0.0604
-5.500 -0.1414 0.02226 0.01413 -0.0914 0.8158 0.0647
-5.250 -0.1245 0.02204 0.01394 -0.0898 0.8106 0.0686
-5.000 -0.1022 0.02174 0.01354 -0.0889 0.8067 0.0732
-4.750 -0.0791 0.02096 0.01286 -0.0882 0.8039 0.0806
-4.500 -0.0548 0.02040 0.01226 -0.0875 0.8015 0.0889
-4.250 -0.0334 0.02014 0.01200 -0.0865 0.7985 0.0999
-4.000 -0.0217 0.02005 0.01203 -0.0841 0.7926 0.1117
-3.750 -0.0018 0.01967 0.01173 -0.0829 0.7891 0.1328
-3.500 0.0193 0.01904 0.01132 -0.0818 0.7865 0.1740
-3.250 0.0371 0.01820 0.01099 -0.0802 0.7843 0.2807
-3.000 0.0352 0.01805 0.01147 -0.0758 0.7769 0.4103
-2.750 0.0384 0.01715 0.01191 -0.0703 0.7729 0.6923
-2.500 0.0671 0.01813 0.01306 -0.0676 0.7709 0.8174
-2.250 0.0918 0.01872 0.01352 -0.0655 0.7689 0.8502
-2.000 0.0963 0.01970 0.01448 -0.0608 0.7618 0.8696
-1.750 0.1149 0.02021 0.01491 -0.0581 0.7577 0.8890
-1.500 0.1611 0.02053 0.01510 -0.0603 0.7560 0.9048
-1.250 0.2513 0.02076 0.01514 -0.0711 0.7558 0.9190
-1.000 0.3333 0.02071 0.01493 -0.0810 0.7550 0.9316
-0.750 0.4182 0.02047 0.01455 -0.0917 0.7541 0.9458
-0.500 0.4777 0.02014 0.01410 -0.0979 0.7525 0.9562
-0.250 0.5246 0.02008 0.01401 -0.1023 0.7479 0.9654
0.000 0.5701 0.01986 0.01375 -0.1063 0.7435 0.9749
0.250 0.6128 0.01954 0.01337 -0.1096 0.7404 0.9832
0.500 0.6579 0.01900 0.01276 -0.1133 0.7378 0.9879
0.750 0.6932 0.01874 0.01246 -0.1152 0.7349 0.9922
1.000 0.7230 0.01878 0.01254 -0.1166 0.7282 0.9964
1.250 0.7586 0.01843 0.01216 -0.1185 0.7245 0.9997
1.500 0.7852 0.01815 0.01182 -0.1184 0.7215 1.0000
1.750 0.8008 0.01837 0.01208 -0.1167 0.7155 1.0000
2.000 0.8205 0.01836 0.01208 -0.1155 0.7103 1.0000
2.250 0.8456 0.01809 0.01177 -0.1150 0.7070 1.0000
2.500 0.8687 0.01796 0.01163 -0.1143 0.7031 1.0000
2.750 0.8828 0.01817 0.01190 -0.1122 0.6958 1.0000
3.000 0.9082 0.01787 0.01159 -0.1118 0.6920 1.0000
3.250 0.9368 0.01752 0.01119 -0.1119 0.6892 1.0000
3.500 0.9461 0.01788 0.01166 -0.1090 0.6807 1.0000
3.750 0.9724 0.01756 0.01133 -0.1086 0.6766 1.0000
4.000 0.9950 0.01743 0.01121 -0.1078 0.6718 1.0000
4.250 1.0106 0.01749 0.01133 -0.1058 0.6644 1.0000
4.500 1.0385 0.01713 0.01095 -0.1057 0.6603 1.0000
4.750 1.0529 0.01725 0.01115 -0.1034 0.6527 1.0000
5.000 1.0765 0.01701 0.01092 -0.1026 0.6468 1.0000
5.250 1.0982 0.01688 0.01082 -0.1016 0.6406 1.0000
5.500 1.1151 0.01685 0.01086 -0.0997 0.6328 1.0000
5.750 1.1407 0.01662 0.01062 -0.0992 0.6269 1.0000
6.000 1.1534 0.01671 0.01079 -0.0966 0.6179 1.0000
6.250 1.1746 0.01658 0.01068 -0.0954 0.6104 1.0000
6.500 1.1907 0.01657 0.01072 -0.0932 0.6013 1.0000
6.750 1.2043 0.01663 0.01083 -0.0907 0.5918 1.0000
7.000 1.2278 0.01646 0.01064 -0.0898 0.5831 1.0000
7.250 1.2333 0.01668 0.01095 -0.0859 0.5720 1.0000
7.500 1.2446 0.01678 0.01109 -0.0829 0.5614 1.0000
7.750 1.2587 0.01681 0.01111 -0.0804 0.5504 1.0000
8.000 1.2655 0.01696 0.01126 -0.0766 0.5384 1.0000
8.250 1.2637 0.01720 0.01155 -0.0712 0.5264 1.0000
8.500 1.2629 0.01741 0.01177 -0.0661 0.5148 1.0000
8.750 1.2579 0.01754 0.01189 -0.0601 0.5032 1.0000
9.000 1.2471 0.01766 0.01195 -0.0530 0.4912 1.0000
9.250 1.2283 0.01793 0.01224 -0.0450 0.4790 1.0000
9.500 1.2231 0.01834 0.01261 -0.0397 0.4635 1.0000
9.750 1.2237 0.01890 0.01310 -0.0359 0.4462 1.0000
10.000 1.2266 0.01959 0.01374 -0.0326 0.4290 1.0000
10.250 1.2298 0.02042 0.01456 -0.0298 0.4124 1.0000
10.500 1.2332 0.02136 0.01550 -0.0271 0.3954 1.0000
10.750 1.2369 0.02238 0.01651 -0.0246 0.3784 1.0000
11.000 1.2402 0.02350 0.01761 -0.0223 0.3610 1.0000
11.250 1.2427 0.02474 0.01883 -0.0200 0.3429 1.0000
11.500 1.2440 0.02611 0.02015 -0.0178 0.3244 1.0000
11.750 1.2454 0.02756 0.02156 -0.0157 0.3065 1.0000
12.000 1.2463 0.02912 0.02311 -0.0137 0.2876 1.0000
12.250 1.2454 0.03089 0.02484 -0.0117 0.2667 1.0000
12.500 1.2430 0.03285 0.02673 -0.0098 0.2462 1.0000
12.750 1.2402 0.03497 0.02880 -0.0081 0.2224 1.0000
13.000 1.2348 0.03742 0.03114 -0.0063 0.1982 1.0000
13.250 1.2266 0.04023 0.03382 -0.0047 0.1702 1.0000
13.500 1.2162 0.04340 0.03682 -0.0032 0.1400 1.0000
13.750 1.2029 0.04701 0.04023 -0.0018 0.1097 1.0000
14.000 1.1899 0.05077 0.04382 -0.0007 0.0862 1.0000
14.250 1.1785 0.05457 0.04750 0.0002 0.0711 1.0000
14.500 1.1713 0.05807 0.05098 0.0008 0.0618 1.0000
14.750 1.1637 0.06173 0.05464 0.0011 0.0554 1.0000
15.000 1.1597 0.06510 0.05806 0.0013 0.0504 1.0000
15.250 1.1538 0.06872 0.06170 0.0014 0.0468 1.0000
15.500 1.1535 0.07180 0.06487 0.0013 0.0432 1.0000
15.750 1.1498 0.07525 0.06831 0.0012 0.0405 1.0000
16.000 1.1506 0.07819 0.07131 0.0012 0.0382 1.0000
16.250 1.1540 0.08089 0.07410 0.0011 0.0362 1.0000
16.500 1.1557 0.08381 0.07704 0.0007 0.0341 1.0000
16.750 1.1608 0.08594 0.07912 0.0011 0.0321 1.0000
17.000 1.1672 0.08832 0.08163 0.0009 0.0308 1.0000
17.250 1.1737 0.09065 0.08407 0.0007 0.0295 1.0000
17.500 1.1808 0.09286 0.08633 0.0006 0.0283 1.0000
17.750 1.1905 0.09455 0.08799 0.0006 0.0270 1.0000
18.000 1.2019 0.09608 0.08959 0.0011 0.0259 1.0000
18.250 1.2049 0.09911 0.09281 0.0005 0.0252 1.0000
18.500 1.2074 0.10220 0.09607 -0.0003 0.0245 1.0000
18.750 1.2103 0.10524 0.09925 -0.0011 0.0238 1.0000
19.000 1.2124 0.10841 0.10255 -0.0020 0.0231 1.0000
19.250 1.2142 0.11163 0.10592 -0.0030 0.0228 1.0000
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Polar data table (+)
Polar graphs
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