AH 93-156 (ah93156-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 200,000 Max Cl/Cd: 72.1 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93156-il-200000.txt Download as CSV file: xf-ah93156-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-156
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1327 0.09473 0.09076 -0.1098 0.8884 0.0659
-11.000 -0.1503 0.09002 0.08608 -0.1144 0.8839 0.0683
-10.750 -0.1826 0.08347 0.07959 -0.1220 0.8790 0.0690
-10.500 -0.2075 0.07846 0.07455 -0.1255 0.8738 0.0691
-10.250 -0.1630 0.07748 0.07361 -0.1192 0.8729 0.0713
-10.000 -0.1515 0.07577 0.07188 -0.1181 0.8699 0.0732
-9.750 -0.1560 0.07216 0.06827 -0.1198 0.8667 0.0743
-9.500 -0.1724 0.06742 0.06356 -0.1230 0.8628 0.0757
-9.250 -0.1946 0.06336 0.05948 -0.1240 0.8580 0.0765
-9.000 -0.2202 0.06019 0.05624 -0.1224 0.8533 0.0779
-8.750 -0.2477 0.05796 0.05386 -0.1188 0.8495 0.0794
-8.500 -0.3425 0.04302 0.03770 -0.1086 0.8430 0.0462
-8.250 -0.3419 0.03982 0.03425 -0.1059 0.8399 0.0453
-8.000 -0.3387 0.03690 0.03098 -0.1030 0.8371 0.0447
-7.750 -0.3317 0.03441 0.02808 -0.1002 0.8346 0.0447
-7.500 -0.3224 0.03290 0.02622 -0.0978 0.8307 0.0458
-7.250 -0.3095 0.03196 0.02489 -0.0955 0.8274 0.0469
-7.000 -0.2936 0.02936 0.02197 -0.0940 0.8247 0.0478
-6.750 -0.2716 0.02776 0.02026 -0.0934 0.8225 0.0494
-6.500 -0.2483 0.02683 0.01920 -0.0927 0.8206 0.0514
-6.250 -0.2281 0.02635 0.01859 -0.0917 0.8179 0.0543
-6.000 -0.2102 0.02597 0.01805 -0.0903 0.8140 0.0565
-5.750 -0.1872 0.02471 0.01669 -0.0898 0.8110 0.0592
-5.500 -0.1634 0.02410 0.01610 -0.0893 0.8085 0.0630
-5.250 -0.1381 0.02365 0.01553 -0.0888 0.8066 0.0678
-5.000 -0.1127 0.02274 0.01462 -0.0884 0.8050 0.0727
-4.750 -0.0978 0.02277 0.01469 -0.0866 0.8009 0.0781
-4.500 -0.0834 0.02266 0.01457 -0.0847 0.7963 0.0844
-4.250 -0.0637 0.02237 0.01431 -0.0835 0.7935 0.0930
-4.000 -0.0413 0.02190 0.01389 -0.0826 0.7914 0.1059
-3.750 -0.0170 0.02141 0.01343 -0.0819 0.7897 0.1256
-3.500 -0.0103 0.02160 0.01379 -0.0790 0.7846 0.1476
-3.250 -0.0024 0.02157 0.01399 -0.0761 0.7793 0.1908
-3.000 0.0119 0.02074 0.01379 -0.0741 0.7765 0.3190
-2.750 0.0199 0.01944 0.01354 -0.0706 0.7745 0.5537
-2.500 0.0425 0.02000 0.01501 -0.0660 0.7734 0.8039
-2.250 0.0220 0.02136 0.01639 -0.0584 0.7632 0.8302
-2.000 0.0411 0.02196 0.01689 -0.0553 0.7606 0.8615
-1.750 0.0701 0.02242 0.01724 -0.0538 0.7592 0.8839
-1.500 0.0762 0.02320 0.01797 -0.0494 0.7538 0.9009
-1.250 0.1804 0.02301 0.01754 -0.0611 0.7581 0.9192
-1.000 0.2841 0.02304 0.01739 -0.0750 0.7584 0.9316
-0.750 0.3819 0.02274 0.01693 -0.0879 0.7584 0.9457
-0.500 0.4473 0.02236 0.01643 -0.0949 0.7576 0.9579
-0.250 0.4867 0.02281 0.01689 -0.0986 0.7508 0.9683
0.000 0.5431 0.02236 0.01638 -0.1045 0.7482 0.9768
0.250 0.5908 0.02191 0.01586 -0.1087 0.7460 0.9847
0.500 0.6361 0.02135 0.01524 -0.1123 0.7442 0.9897
0.750 0.6734 0.02094 0.01477 -0.1143 0.7424 0.9938
1.000 0.7012 0.02129 0.01517 -0.1158 0.7354 0.9981
1.250 0.7304 0.02111 0.01498 -0.1165 0.7316 1.0000
1.500 0.7553 0.02080 0.01464 -0.1160 0.7290 1.0000
1.750 0.7813 0.02046 0.01426 -0.1156 0.7269 1.0000
2.000 0.7867 0.02120 0.01507 -0.1125 0.7185 1.0000
2.250 0.8105 0.02095 0.01481 -0.1118 0.7152 1.0000
2.500 0.8374 0.02055 0.01438 -0.1115 0.7128 1.0000
2.750 0.8638 0.02025 0.01406 -0.1112 0.7104 1.0000
3.000 0.8684 0.02088 0.01478 -0.1078 0.7014 1.0000
3.250 0.8957 0.02045 0.01435 -0.1075 0.6985 1.0000
3.500 0.9259 0.01992 0.01380 -0.1078 0.6964 1.0000
3.750 0.9304 0.02048 0.01445 -0.1042 0.6875 1.0000
4.000 0.9582 0.01999 0.01397 -0.1040 0.6840 1.0000
4.250 0.9905 0.01934 0.01331 -0.1045 0.6815 1.0000
4.500 0.9964 0.01974 0.01380 -0.1009 0.6727 1.0000
4.750 1.0249 0.01922 0.01330 -0.1008 0.6688 1.0000
5.000 1.0594 0.01852 0.01258 -0.1017 0.6660 1.0000
5.250 1.0637 0.01884 0.01300 -0.0977 0.6563 1.0000
5.500 1.0966 0.01816 0.01232 -0.0983 0.6522 1.0000
5.750 1.1061 0.01826 0.01252 -0.0951 0.6434 1.0000
6.000 1.1351 0.01771 0.01198 -0.0951 0.6378 1.0000
6.250 1.1463 0.01773 0.01208 -0.0921 0.6289 1.0000
6.500 1.1748 0.01723 0.01159 -0.0920 0.6223 1.0000
6.750 1.1814 0.01733 0.01178 -0.0882 0.6119 1.0000
7.000 1.2011 0.01709 0.01156 -0.0866 0.6030 1.0000
7.250 1.2173 0.01692 0.01142 -0.0844 0.5927 1.0000
7.500 1.2212 0.01703 0.01158 -0.0800 0.5807 1.0000
7.750 1.2276 0.01707 0.01166 -0.0761 0.5686 1.0000
8.000 1.2337 0.01711 0.01169 -0.0721 0.5561 1.0000
8.250 1.2376 0.01717 0.01173 -0.0677 0.5435 1.0000
8.500 1.2356 0.01722 0.01175 -0.0622 0.5309 1.0000
8.750 1.2164 0.01743 0.01195 -0.0538 0.5190 1.0000
9.000 1.2057 0.01769 0.01219 -0.0472 0.5057 1.0000
9.250 1.2042 0.01805 0.01251 -0.0425 0.4911 1.0000
9.500 1.2079 0.01853 0.01295 -0.0390 0.4745 1.0000
9.750 1.2134 0.01912 0.01347 -0.0360 0.4567 1.0000
10.000 1.2173 0.01988 0.01419 -0.0331 0.4386 1.0000
10.250 1.2204 0.02080 0.01508 -0.0303 0.4202 1.0000
10.500 1.2236 0.02180 0.01605 -0.0277 0.4014 1.0000
10.750 1.2262 0.02290 0.01710 -0.0252 0.3822 1.0000
11.000 1.2288 0.02409 0.01823 -0.0228 0.3632 1.0000
11.250 1.2299 0.02543 0.01957 -0.0204 0.3429 1.0000
11.500 1.2316 0.02682 0.02093 -0.0183 0.3234 1.0000
11.750 1.2312 0.02840 0.02243 -0.0160 0.3028 1.0000
12.000 1.2316 0.03003 0.02404 -0.0141 0.2812 1.0000
12.250 1.2296 0.03191 0.02583 -0.0120 0.2591 1.0000
12.500 1.2286 0.03384 0.02770 -0.0103 0.2370 1.0000
12.750 1.2251 0.03606 0.02981 -0.0085 0.2140 1.0000
13.000 1.2227 0.03833 0.03202 -0.0070 0.1898 1.0000
13.250 1.2178 0.04090 0.03447 -0.0055 0.1651 1.0000
13.500 1.2109 0.04377 0.03721 -0.0041 0.1387 1.0000
13.750 1.2019 0.04698 0.04024 -0.0028 0.1108 1.0000
14.000 1.1914 0.05047 0.04356 -0.0017 0.0867 1.0000
14.250 1.1812 0.05410 0.04705 -0.0008 0.0684 1.0000
14.500 1.1724 0.05774 0.05063 -0.0001 0.0569 1.0000
14.750 1.1659 0.06127 0.05417 0.0004 0.0486 1.0000
15.000 1.1585 0.06502 0.05793 0.0007 0.0433 1.0000
15.250 1.1550 0.06842 0.06139 0.0007 0.0391 1.0000
15.500 1.1477 0.07229 0.06527 0.0008 0.0365 1.0000
15.750 1.1491 0.07529 0.06838 0.0006 0.0332 1.0000
16.000 1.1477 0.07860 0.07175 0.0003 0.0312 1.0000
16.250 1.1451 0.08197 0.07513 0.0002 0.0292 1.0000
16.500 1.1481 0.08483 0.07811 -0.0001 0.0274 1.0000
16.750 1.1509 0.08768 0.08101 -0.0004 0.0260 1.0000
17.000 1.1550 0.09025 0.08360 -0.0006 0.0249 1.0000
17.250 1.1651 0.09164 0.08493 0.0002 0.0238 1.0000
17.500 1.1705 0.09427 0.08773 -0.0001 0.0229 1.0000
17.750 1.1790 0.09634 0.08992 -0.0002 0.0224 1.0000
18.000 1.1856 0.09876 0.09247 -0.0004 0.0216 1.0000
18.250 1.1911 0.10138 0.09522 -0.0008 0.0210 1.0000
18.500 1.1961 0.10408 0.09805 -0.0013 0.0206 1.0000
18.750 1.2003 0.10683 0.10083 -0.0022 0.0199 1.0000
19.000 1.2094 0.10881 0.10285 -0.0022 0.0193 1.0000
19.250 1.2089 0.11248 0.10669 -0.0031 0.0189 1.0000
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Polar data table (+)
Polar graphs
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