AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 200,000 Max Cl/Cd: 62.41 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k143-il-200000-n5.txt Download as CSV file: xf-ah79k143-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-143/18
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2955 0.09346 0.08882 -0.0925 0.8187 0.0150
-11.750 -0.3113 0.08544 0.08086 -0.0965 0.8179 0.0151
-11.500 -0.3116 0.08137 0.07681 -0.0990 0.8170 0.0146
-11.250 -0.3735 0.06080 0.05622 -0.1128 0.8161 0.0143
-11.000 -0.4124 0.05289 0.04810 -0.1164 0.8148 0.0141
-10.750 -0.4404 0.04814 0.04310 -0.1156 0.8135 0.0141
-10.500 -0.4668 0.04406 0.03875 -0.1126 0.8118 0.0143
-10.250 -0.4833 0.04107 0.03551 -0.1088 0.8100 0.0141
-10.000 -0.4988 0.03849 0.03265 -0.1042 0.8083 0.0143
-9.750 -0.5086 0.03603 0.02983 -0.0997 0.8065 0.0145
-9.500 -0.5082 0.03390 0.02736 -0.0965 0.8048 0.0146
-9.250 -0.5038 0.03195 0.02496 -0.0935 0.8033 0.0153
-9.000 -0.4932 0.03056 0.02338 -0.0914 0.8022 0.0159
-8.750 -0.4791 0.02963 0.02233 -0.0898 0.8011 0.0165
-8.500 -0.4638 0.02851 0.02104 -0.0883 0.7998 0.0169
-8.250 -0.4475 0.02734 0.01968 -0.0867 0.7980 0.0177
-8.000 -0.4293 0.02611 0.01825 -0.0855 0.7963 0.0185
-7.750 -0.4094 0.02502 0.01693 -0.0844 0.7947 0.0193
-7.500 -0.3892 0.02399 0.01577 -0.0833 0.7933 0.0200
-7.250 -0.3698 0.02319 0.01493 -0.0823 0.7917 0.0211
-7.000 -0.3492 0.02259 0.01427 -0.0813 0.7902 0.0227
-6.750 -0.3281 0.02201 0.01358 -0.0803 0.7888 0.0242
-6.500 -0.3077 0.02145 0.01296 -0.0792 0.7876 0.0264
-6.250 -0.2872 0.02104 0.01252 -0.0782 0.7860 0.0289
-6.000 -0.2676 0.02058 0.01203 -0.0770 0.7836 0.0321
-5.750 -0.2476 0.02018 0.01163 -0.0759 0.7814 0.0349
-5.500 -0.2268 0.01981 0.01118 -0.0748 0.7794 0.0383
-5.250 -0.2065 0.01938 0.01076 -0.0736 0.7774 0.0428
-5.000 -0.1850 0.01904 0.01035 -0.0726 0.7756 0.0481
-4.750 -0.1636 0.01866 0.00998 -0.0716 0.7741 0.0567
-4.500 -0.1416 0.01833 0.00966 -0.0706 0.7727 0.0689
-4.250 -0.1230 0.01810 0.00950 -0.0693 0.7693 0.0833
-4.000 -0.1024 0.01787 0.00932 -0.0682 0.7666 0.1016
-3.750 -0.0815 0.01758 0.00913 -0.0672 0.7642 0.1269
-3.250 -0.0416 0.01677 0.00872 -0.0649 0.7605 0.2289
-3.000 -0.0243 0.01616 0.00849 -0.0633 0.7590 0.3243
-2.750 -0.0146 0.01547 0.00838 -0.0604 0.7559 0.4610
-2.500 -0.0064 0.01482 0.00859 -0.0565 0.7521 0.6486
-2.250 0.0250 0.01532 0.00949 -0.0554 0.7500 0.7597
-2.000 0.0510 0.01568 0.00981 -0.0543 0.7479 0.7944
-1.750 0.0724 0.01584 0.00987 -0.0528 0.7460 0.8168
-1.500 0.0939 0.01600 0.00994 -0.0512 0.7445 0.8357
-1.250 0.1128 0.01634 0.01024 -0.0492 0.7409 0.8509
-1.000 0.1315 0.01675 0.01063 -0.0469 0.7362 0.8659
-0.750 0.1573 0.01713 0.01097 -0.0455 0.7336 0.8815
-0.500 0.1943 0.01732 0.01111 -0.0465 0.7319 0.8906
-0.250 0.2174 0.01719 0.01090 -0.0455 0.7302 0.8969
0.250 0.2650 0.01726 0.01093 -0.0443 0.7217 0.9039
0.500 0.2816 0.01711 0.01074 -0.0422 0.7188 0.9101
0.750 0.3132 0.01693 0.01051 -0.0429 0.7170 0.9120
1.000 0.3445 0.01671 0.01025 -0.0436 0.7156 0.9140
1.250 0.3616 0.01687 0.01045 -0.0420 0.7090 0.9181
1.500 0.3788 0.01672 0.01029 -0.0400 0.7055 0.9229
1.750 0.4064 0.01648 0.01003 -0.0399 0.7033 0.9253
2.000 0.4377 0.01623 0.00977 -0.0407 0.7016 0.9269
2.250 0.4566 0.01635 0.00993 -0.0393 0.6951 0.9300
2.500 0.4795 0.01622 0.00982 -0.0385 0.6912 0.9330
2.750 0.5021 0.01596 0.00956 -0.0375 0.6885 0.9358
3.000 0.5279 0.01565 0.00924 -0.0370 0.6865 0.9380
3.250 0.5465 0.01583 0.00949 -0.0358 0.6781 0.9406
3.500 0.5756 0.01560 0.00929 -0.0361 0.6746 0.9422
3.750 0.6069 0.01529 0.00900 -0.0367 0.6720 0.9438
4.000 0.6176 0.01541 0.00919 -0.0338 0.6633 0.9484
4.250 0.6402 0.01515 0.00894 -0.0327 0.6592 0.9506
4.500 0.6670 0.01507 0.00894 -0.0328 0.6528 0.9521
4.750 0.6950 0.01492 0.00883 -0.0329 0.6462 0.9536
5.000 0.7246 0.01469 0.00863 -0.0333 0.6404 0.9547
5.250 0.7467 0.01465 0.00866 -0.0324 0.6321 0.9566
5.500 0.7739 0.01446 0.00851 -0.0323 0.6250 0.9579
5.750 0.7946 0.01440 0.00850 -0.0311 0.6157 0.9604
6.000 0.8151 0.01431 0.00845 -0.0297 0.6037 0.9628
6.250 0.8428 0.01424 0.00841 -0.0299 0.5897 0.9641
6.500 0.8686 0.01415 0.00827 -0.0295 0.5682 0.9656
6.750 0.8872 0.01424 0.00829 -0.0279 0.5419 0.9678
7.000 0.9012 0.01444 0.00842 -0.0256 0.5137 0.9710
7.250 0.9098 0.01478 0.00863 -0.0225 0.4793 0.9741
7.500 0.9161 0.01548 0.00910 -0.0196 0.4326 0.9776
7.750 0.9177 0.01653 0.00989 -0.0167 0.3810 0.9821
8.000 0.9213 0.01820 0.01123 -0.0155 0.3154 0.9861
8.250 0.9225 0.01998 0.01266 -0.0141 0.2507 0.9915
8.500 0.9186 0.02166 0.01404 -0.0112 0.1954 1.0000
8.750 0.9100 0.02303 0.01514 -0.0070 0.1521 1.0000
9.000 0.9050 0.02456 0.01639 -0.0036 0.1046 1.0000
9.250 0.9023 0.02618 0.01775 -0.0009 0.0661 1.0000
9.500 0.9087 0.02738 0.01889 0.0009 0.0521 1.0000
9.750 0.9151 0.02866 0.02014 0.0025 0.0410 1.0000
10.000 0.9242 0.02983 0.02135 0.0039 0.0358 1.0000
10.250 0.9306 0.03124 0.02277 0.0054 0.0312 1.0000
10.500 0.9402 0.03248 0.02410 0.0065 0.0277 1.0000
10.750 0.9473 0.03392 0.02556 0.0076 0.0245 1.0000
11.000 0.9554 0.03534 0.02706 0.0087 0.0231 1.0000
11.250 0.9637 0.03678 0.02860 0.0096 0.0223 1.0000
11.500 0.9714 0.03834 0.03024 0.0106 0.0207 1.0000
11.750 0.9785 0.04002 0.03200 0.0114 0.0200 1.0000
12.000 0.9839 0.04189 0.03391 0.0122 0.0192 1.0000
12.250 0.9891 0.04382 0.03591 0.0130 0.0187 1.0000
12.500 0.9972 0.04553 0.03774 0.0137 0.0180 1.0000
12.750 1.0047 0.04733 0.03962 0.0144 0.0175 1.0000
13.000 1.0138 0.04901 0.04139 0.0148 0.0169 1.0000
13.250 1.0223 0.05077 0.04322 0.0152 0.0161 1.0000
13.500 1.0302 0.05263 0.04513 0.0155 0.0154 1.0000
13.750 1.0381 0.05449 0.04708 0.0159 0.0152 1.0000
14.000 1.0450 0.05645 0.04907 0.0164 0.0148 1.0000
14.250 1.0540 0.05826 0.05097 0.0170 0.0146 1.0000
14.500 1.0629 0.06018 0.05305 0.0175 0.0142 1.0000
14.750 1.0714 0.06216 0.05517 0.0179 0.0139 1.0000
15.000 1.0792 0.06427 0.05744 0.0182 0.0138 1.0000
15.250 1.0851 0.06664 0.05998 0.0185 0.0135 1.0000
15.500 1.0892 0.06930 0.06283 0.0187 0.0132 1.0000
15.750 1.0915 0.07220 0.06592 0.0187 0.0130 1.0000
16.000 1.0916 0.07540 0.06930 0.0184 0.0128 1.0000
16.250 1.0903 0.07889 0.07301 0.0180 0.0128 1.0000
16.500 1.0855 0.08291 0.07722 0.0173 0.0126 1.0000
16.750 1.0797 0.08713 0.08165 0.0163 0.0126 1.0000
17.000 1.0725 0.09165 0.08636 0.0149 0.0124 1.0000
17.250 1.0617 0.09693 0.09188 0.0131 0.0125 1.0000
17.500 1.0520 0.10212 0.09724 0.0109 0.0123 1.0000
17.750 1.0359 0.10868 0.10404 0.0080 0.0124 1.0000
18.000 1.0184 0.11583 0.11142 0.0045 0.0124 1.0000
18.250 1.0003 0.12346 0.11925 0.0003 0.0123 1.0000
18.500 0.9825 0.13147 0.12746 -0.0044 0.0123 1.0000
18.750 0.9443 0.14511 0.14139 -0.0126 0.0126 1.0000
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Polar data table (+)
Polar graphs
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