AH 93-156 (ah93156-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.9 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93156-il-1000000-n5.txt Download as CSV file: xf-ah93156-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6207 0.08885 0.08578 -0.0934 0.7957 0.0083
-16.750 -0.7688 0.05978 0.05632 -0.1100 0.7954 0.0077
-16.500 -0.8215 0.04636 0.04260 -0.1199 0.7922 0.0077
-16.000 -0.8580 0.03687 0.03277 -0.1239 0.7856 0.0078
-15.750 -0.8688 0.03397 0.02974 -0.1235 0.7823 0.0078
-15.500 -0.8755 0.03172 0.02736 -0.1224 0.7790 0.0079
-15.250 -0.8804 0.02979 0.02530 -0.1207 0.7757 0.0080
-15.000 -0.8789 0.02838 0.02379 -0.1190 0.7724 0.0081
-14.750 -0.8770 0.02702 0.02233 -0.1171 0.7698 0.0082
-14.500 -0.8710 0.02595 0.02116 -0.1153 0.7670 0.0083
-14.250 -0.8643 0.02494 0.02007 -0.1134 0.7641 0.0084
-14.000 -0.8564 0.02403 0.01907 -0.1115 0.7615 0.0085
-13.750 -0.8487 0.02313 0.01807 -0.1094 0.7590 0.0086
-13.500 -0.8375 0.02241 0.01728 -0.1076 0.7567 0.0088
-13.250 -0.8260 0.02171 0.01650 -0.1058 0.7547 0.0089
-13.000 -0.8127 0.02110 0.01584 -0.1041 0.7523 0.0091
-12.750 -0.8020 0.02037 0.01502 -0.1019 0.7498 0.0092
-12.500 -0.7895 0.01976 0.01432 -0.0999 0.7474 0.0094
-12.250 -0.7765 0.01920 0.01367 -0.0979 0.7451 0.0096
-12.000 -0.7634 0.01867 0.01305 -0.0958 0.7431 0.0097
-11.750 -0.7483 0.01825 0.01256 -0.0939 0.7412 0.0099
-11.500 -0.7316 0.01777 0.01201 -0.0924 0.7396 0.0100
-11.250 -0.7127 0.01731 0.01149 -0.0912 0.7377 0.0101
-11.000 -0.6960 0.01665 0.01076 -0.0897 0.7357 0.0105
-10.750 -0.6762 0.01619 0.01023 -0.0886 0.7336 0.0107
-10.500 -0.6557 0.01575 0.00975 -0.0877 0.7316 0.0111
-10.250 -0.6345 0.01534 0.00929 -0.0868 0.7298 0.0113
-10.000 -0.6124 0.01500 0.00889 -0.0861 0.7281 0.0117
-9.750 -0.5902 0.01465 0.00848 -0.0853 0.7264 0.0120
-9.500 -0.5673 0.01430 0.00809 -0.0847 0.7250 0.0123
-9.250 -0.5441 0.01396 0.00770 -0.0841 0.7234 0.0127
-9.000 -0.5203 0.01365 0.00735 -0.0836 0.7216 0.0130
-8.750 -0.4972 0.01327 0.00693 -0.0830 0.7198 0.0135
-8.500 -0.4733 0.01295 0.00659 -0.0825 0.7180 0.0141
-8.250 -0.4490 0.01268 0.00629 -0.0821 0.7164 0.0147
-8.000 -0.4243 0.01242 0.00600 -0.0817 0.7148 0.0154
-7.750 -0.3996 0.01217 0.00571 -0.0813 0.7132 0.0159
-7.500 -0.3747 0.01195 0.00543 -0.0810 0.7115 0.0164
-7.250 -0.3499 0.01166 0.00513 -0.0806 0.7099 0.0173
-7.000 -0.3246 0.01141 0.00488 -0.0803 0.7084 0.0182
-6.750 -0.2990 0.01119 0.00465 -0.0801 0.7068 0.0192
-6.500 -0.2731 0.01099 0.00443 -0.0799 0.7053 0.0200
-6.250 -0.2473 0.01078 0.00421 -0.0797 0.7035 0.0212
-6.000 -0.2216 0.01057 0.00399 -0.0795 0.7017 0.0228
-5.750 -0.1956 0.01040 0.00380 -0.0793 0.7000 0.0243
-5.500 -0.1693 0.01025 0.00362 -0.0792 0.6983 0.0254
-5.250 -0.1434 0.01006 0.00343 -0.0790 0.6967 0.0279
-5.000 -0.1170 0.00991 0.00327 -0.0789 0.6951 0.0302
-4.750 -0.0904 0.00975 0.00312 -0.0788 0.6936 0.0325
-4.500 -0.0639 0.00958 0.00298 -0.0787 0.6919 0.0358
-4.250 -0.0370 0.00944 0.00284 -0.0787 0.6901 0.0390
-4.000 -0.0105 0.00928 0.00271 -0.0786 0.6883 0.0445
-3.750 0.0163 0.00915 0.00259 -0.0786 0.6864 0.0498
-3.500 0.0430 0.00902 0.00247 -0.0785 0.6846 0.0566
-3.250 0.0696 0.00888 0.00237 -0.0784 0.6827 0.0660
-3.000 0.0962 0.00877 0.00227 -0.0784 0.6807 0.0767
-2.750 0.1230 0.00861 0.00218 -0.0784 0.6789 0.0921
-2.500 0.1498 0.00846 0.00210 -0.0784 0.6768 0.1103
-2.250 0.1762 0.00829 0.00202 -0.0783 0.6744 0.1354
-2.000 0.2026 0.00812 0.00195 -0.0782 0.6719 0.1648
-1.750 0.2284 0.00793 0.00187 -0.0781 0.6690 0.2053
-1.500 0.2531 0.00769 0.00179 -0.0777 0.6658 0.2641
-1.250 0.2785 0.00743 0.00174 -0.0775 0.6629 0.3231
-1.000 0.3031 0.00713 0.00169 -0.0772 0.6600 0.4008
-0.750 0.3270 0.00679 0.00162 -0.0768 0.6569 0.4876
-0.500 0.3461 0.00616 0.00150 -0.0754 0.6539 0.6487
-0.250 0.3662 0.00582 0.00159 -0.0739 0.6510 0.7771
0.000 0.3932 0.00587 0.00172 -0.0737 0.6482 0.8129
0.250 0.4214 0.00594 0.00179 -0.0738 0.6448 0.8281
0.500 0.4491 0.00605 0.00190 -0.0738 0.6410 0.8390
0.750 0.4766 0.00617 0.00201 -0.0737 0.6375 0.8474
1.000 0.5043 0.00630 0.00214 -0.0737 0.6343 0.8545
1.250 0.5321 0.00641 0.00224 -0.0738 0.6304 0.8602
1.500 0.5593 0.00653 0.00236 -0.0737 0.6260 0.8637
1.750 0.5865 0.00661 0.00242 -0.0737 0.6215 0.8660
2.000 0.6146 0.00665 0.00245 -0.0739 0.6171 0.8673
2.250 0.6424 0.00669 0.00248 -0.0741 0.6115 0.8685
2.500 0.6694 0.00675 0.00251 -0.0741 0.6056 0.8697
2.750 0.6971 0.00679 0.00254 -0.0743 0.5985 0.8708
3.000 0.7234 0.00688 0.00258 -0.0743 0.5905 0.8719
3.250 0.7506 0.00694 0.00263 -0.0744 0.5826 0.8729
3.500 0.7766 0.00704 0.00269 -0.0743 0.5738 0.8737
3.750 0.8015 0.00714 0.00276 -0.0739 0.5623 0.8746
4.000 0.8260 0.00726 0.00285 -0.0735 0.5494 0.8755
4.250 0.8495 0.00742 0.00296 -0.0728 0.5352 0.8763
4.500 0.8721 0.00759 0.00309 -0.0721 0.5203 0.8771
4.750 0.8937 0.00780 0.00324 -0.0711 0.5046 0.8779
5.000 0.9142 0.00803 0.00341 -0.0700 0.4883 0.8789
5.250 0.9341 0.00826 0.00360 -0.0687 0.4728 0.8801
5.500 0.9532 0.00850 0.00379 -0.0673 0.4578 0.8812
5.750 0.9712 0.00875 0.00399 -0.0657 0.4430 0.8822
6.000 0.9870 0.00900 0.00420 -0.0636 0.4287 0.8834
6.250 0.9994 0.00925 0.00440 -0.0609 0.4153 0.8847
6.500 1.0106 0.00957 0.00468 -0.0579 0.4010 0.8862
6.750 1.0226 0.00992 0.00499 -0.0553 0.3884 0.8875
7.000 1.0337 0.01031 0.00534 -0.0526 0.3763 0.8885
7.500 1.0524 0.01123 0.00620 -0.0469 0.3489 0.8908
7.750 1.0624 0.01175 0.00669 -0.0443 0.3355 0.8921
8.000 1.0684 0.01245 0.00733 -0.0412 0.3179 0.8936
8.250 1.0750 0.01320 0.00801 -0.0383 0.2984 0.8949
8.500 1.0794 0.01408 0.00879 -0.0353 0.2757 0.8963
8.750 1.0816 0.01511 0.00970 -0.0321 0.2498 0.8976
9.000 1.0858 0.01611 0.01058 -0.0293 0.2279 0.8989
9.250 1.0895 0.01717 0.01153 -0.0265 0.2032 0.9001
9.500 1.0923 0.01832 0.01255 -0.0237 0.1786 0.9012
9.750 1.0919 0.01968 0.01373 -0.0206 0.1482 0.9025
10.000 1.1032 0.02049 0.01451 -0.0191 0.1382 0.9033
10.250 1.1032 0.02190 0.01577 -0.0163 0.1104 0.9044
10.500 1.1099 0.02300 0.01680 -0.0144 0.0936 0.9054
10.750 1.1163 0.02417 0.01790 -0.0126 0.0790 0.9063
11.000 1.1230 0.02537 0.01903 -0.0108 0.0646 0.9072
11.250 1.1303 0.02657 0.02019 -0.0092 0.0528 0.9081
11.500 1.1395 0.02771 0.02129 -0.0079 0.0441 0.9089
11.750 1.1477 0.02894 0.02250 -0.0066 0.0360 0.9098
12.000 1.1572 0.03011 0.02365 -0.0054 0.0301 0.9106
12.250 1.1663 0.03135 0.02489 -0.0043 0.0249 0.9115
12.500 1.1745 0.03269 0.02621 -0.0031 0.0194 0.9123
12.750 1.1854 0.03386 0.02741 -0.0023 0.0172 0.9132
13.000 1.1950 0.03515 0.02871 -0.0014 0.0148 0.9142
13.250 1.2050 0.03645 0.03004 -0.0006 0.0128 0.9150
13.500 1.2141 0.03786 0.03147 0.0002 0.0111 0.9158
13.750 1.2239 0.03924 0.03287 0.0009 0.0098 0.9164
14.000 1.2323 0.04075 0.03442 0.0016 0.0085 0.9170
14.250 1.2423 0.04217 0.03588 0.0021 0.0079 0.9179
14.500 1.2507 0.04377 0.03752 0.0026 0.0073 0.9188
14.750 1.2590 0.04539 0.03920 0.0031 0.0065 0.9197
15.000 1.2670 0.04708 0.04095 0.0036 0.0060 0.9205
15.250 1.2744 0.04885 0.04276 0.0040 0.0055 0.9214
15.500 1.2816 0.05069 0.04465 0.0043 0.0053 0.9223
15.750 1.2876 0.05268 0.04670 0.0046 0.0050 0.9232
16.000 1.2943 0.05464 0.04873 0.0048 0.0048 0.9242
16.250 1.3008 0.05666 0.05081 0.0049 0.0046 0.9252
16.500 1.3053 0.05895 0.05316 0.0050 0.0042 0.9262
16.750 1.3099 0.06126 0.05555 0.0050 0.0041 0.9271
17.000 1.3142 0.06365 0.05801 0.0049 0.0041 0.9281
17.250 1.3183 0.06613 0.06055 0.0047 0.0040 0.9291
17.500 1.3178 0.06919 0.06369 0.0044 0.0036 0.9301
18.000 1.3221 0.07488 0.06953 0.0035 0.0036 0.9325
18.250 1.3229 0.07797 0.07271 0.0028 0.0035 0.9338
18.500 1.3245 0.08105 0.07588 0.0021 0.0035 0.9354
18.750 1.3264 0.08415 0.07906 0.0012 0.0034 0.9371
19.000 1.3253 0.08771 0.08273 0.0002 0.0034 0.9389
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