AH 93-156 (ah93156-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 500,000 Max Cl/Cd: 94.14 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93156-il-500000-n5.txt Download as CSV file: xf-ah93156-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6025 0.05672 0.05296 -0.1129 0.8034 0.0110
-14.500 -0.6478 0.04576 0.04169 -0.1209 0.8000 0.0109
-14.250 -0.6614 0.04171 0.03748 -0.1225 0.7964 0.0110
-14.000 -0.6768 0.03823 0.03382 -0.1225 0.7928 0.0110
-13.750 -0.6866 0.03565 0.03106 -0.1214 0.7895 0.0111
-13.500 -0.6865 0.03403 0.02931 -0.1202 0.7866 0.0113
-13.250 -0.6888 0.03227 0.02742 -0.1184 0.7836 0.0114
-13.000 -0.6905 0.03061 0.02561 -0.1163 0.7807 0.0115
-12.750 -0.6894 0.02919 0.02403 -0.1141 0.7779 0.0117
-12.500 -0.6855 0.02798 0.02266 -0.1119 0.7754 0.0119
-12.250 -0.6819 0.02673 0.02124 -0.1094 0.7729 0.0120
-12.000 -0.6755 0.02563 0.02000 -0.1071 0.7704 0.0123
-11.750 -0.6676 0.02463 0.01887 -0.1048 0.7677 0.0125
-11.500 -0.6590 0.02367 0.01777 -0.1025 0.7651 0.0127
-11.250 -0.6483 0.02287 0.01681 -0.1002 0.7628 0.0129
-11.000 -0.6385 0.02204 0.01584 -0.0978 0.7606 0.0131
-10.750 -0.6264 0.02129 0.01500 -0.0957 0.7587 0.0134
-10.500 -0.6105 0.02064 0.01426 -0.0942 0.7569 0.0137
-10.250 -0.5930 0.02002 0.01357 -0.0929 0.7548 0.0140
-10.000 -0.5736 0.01953 0.01302 -0.0919 0.7526 0.0145
-9.750 -0.5538 0.01902 0.01243 -0.0909 0.7504 0.0149
-9.500 -0.5335 0.01850 0.01181 -0.0899 0.7484 0.0154
-9.250 -0.5125 0.01799 0.01121 -0.0891 0.7466 0.0160
-9.000 -0.4909 0.01752 0.01062 -0.0882 0.7449 0.0164
-8.750 -0.4710 0.01690 0.00994 -0.0872 0.7432 0.0170
-8.500 -0.4491 0.01646 0.00944 -0.0865 0.7415 0.0175
-8.250 -0.4263 0.01607 0.00901 -0.0859 0.7397 0.0182
-8.000 -0.4034 0.01567 0.00857 -0.0853 0.7376 0.0189
-7.750 -0.3801 0.01529 0.00813 -0.0847 0.7357 0.0197
-7.500 -0.3563 0.01495 0.00772 -0.0842 0.7340 0.0204
-7.250 -0.3334 0.01452 0.00728 -0.0835 0.7323 0.0216
-7.000 -0.3091 0.01423 0.00695 -0.0831 0.7305 0.0228
-6.750 -0.2847 0.01395 0.00662 -0.0827 0.7288 0.0240
-6.500 -0.2601 0.01367 0.00627 -0.0823 0.7271 0.0251
-6.250 -0.2360 0.01334 0.00591 -0.0818 0.7255 0.0265
-6.000 -0.2112 0.01307 0.00565 -0.0815 0.7238 0.0283
-5.750 -0.1860 0.01285 0.00541 -0.0812 0.7221 0.0303
-5.500 -0.1611 0.01259 0.00513 -0.0808 0.7201 0.0324
-5.250 -0.1360 0.01235 0.00489 -0.0805 0.7182 0.0350
-5.000 -0.1103 0.01216 0.00467 -0.0803 0.7163 0.0378
-4.750 -0.0850 0.01193 0.00445 -0.0800 0.7147 0.0418
-4.500 -0.0591 0.01176 0.00425 -0.0798 0.7131 0.0459
-4.250 -0.0333 0.01157 0.00405 -0.0796 0.7115 0.0514
-4.000 -0.0074 0.01141 0.00390 -0.0794 0.7097 0.0578
-3.750 0.0182 0.01122 0.00376 -0.0792 0.7078 0.0668
-3.500 0.0439 0.01104 0.00363 -0.0790 0.7058 0.0777
-3.250 0.0696 0.01086 0.00350 -0.0788 0.7037 0.0934
-3.000 0.0953 0.01068 0.00338 -0.0786 0.7017 0.1127
-2.750 0.1207 0.01047 0.00326 -0.0783 0.6999 0.1403
-2.500 0.1461 0.01025 0.00314 -0.0781 0.6980 0.1750
-2.250 0.1708 0.00997 0.00303 -0.0778 0.6962 0.2265
-2.000 0.1943 0.00965 0.00295 -0.0773 0.6941 0.2949
-1.750 0.2168 0.00927 0.00288 -0.0767 0.6915 0.3808
-1.500 0.2379 0.00880 0.00278 -0.0758 0.6890 0.4845
-1.250 0.2540 0.00807 0.00265 -0.0738 0.6865 0.6505
-1.000 0.2733 0.00792 0.00299 -0.0716 0.6840 0.7795
-0.750 0.2998 0.00808 0.00314 -0.0711 0.6813 0.8132
-0.500 0.3265 0.00821 0.00326 -0.0708 0.6781 0.8298
-0.250 0.3532 0.00835 0.00338 -0.0705 0.6748 0.8421
0.000 0.3793 0.00855 0.00358 -0.0700 0.6718 0.8513
0.250 0.4053 0.00874 0.00374 -0.0694 0.6688 0.8612
0.500 0.4308 0.00897 0.00394 -0.0687 0.6662 0.8694
0.750 0.4559 0.00912 0.00409 -0.0680 0.6631 0.8762
1.000 0.4812 0.00922 0.00421 -0.0674 0.6595 0.8801
1.250 0.5080 0.00923 0.00421 -0.0673 0.6560 0.8824
1.500 0.5356 0.00923 0.00416 -0.0674 0.6526 0.8841
1.750 0.5631 0.00924 0.00414 -0.0676 0.6493 0.8859
2.000 0.5904 0.00924 0.00416 -0.0678 0.6452 0.8874
2.250 0.6178 0.00925 0.00415 -0.0680 0.6410 0.8889
2.500 0.6444 0.00925 0.00413 -0.0679 0.6370 0.8898
2.750 0.6708 0.00926 0.00415 -0.0678 0.6326 0.8907
3.000 0.6969 0.00927 0.00418 -0.0677 0.6274 0.8918
3.250 0.7230 0.00929 0.00418 -0.0675 0.6223 0.8929
3.500 0.7488 0.00932 0.00423 -0.0673 0.6163 0.8941
3.750 0.7743 0.00935 0.00426 -0.0671 0.6093 0.8951
4.000 0.7996 0.00939 0.00430 -0.0669 0.6024 0.8964
4.250 0.8245 0.00945 0.00435 -0.0665 0.5946 0.8978
4.500 0.8491 0.00951 0.00441 -0.0662 0.5861 0.8991
4.750 0.8726 0.00960 0.00447 -0.0656 0.5760 0.9002
5.000 0.8957 0.00970 0.00456 -0.0650 0.5643 0.9014
5.250 0.9179 0.00984 0.00466 -0.0642 0.5519 0.9026
5.500 0.9376 0.00998 0.00478 -0.0629 0.5386 0.9038
5.750 0.9555 0.01015 0.00492 -0.0612 0.5244 0.9050
6.000 0.9715 0.01035 0.00509 -0.0592 0.5097 0.9061
6.250 0.9843 0.01057 0.00527 -0.0566 0.4952 0.9076
6.500 0.9940 0.01082 0.00549 -0.0534 0.4809 0.9093
6.750 1.0029 0.01117 0.00580 -0.0501 0.4660 0.9115
7.000 1.0124 0.01156 0.00616 -0.0472 0.4522 0.9132
7.250 1.0207 0.01204 0.00660 -0.0442 0.4376 0.9149
7.500 1.0290 0.01258 0.00710 -0.0413 0.4235 0.9165
8.000 1.0463 0.01368 0.00817 -0.0360 0.3968 0.9199
8.250 1.0549 0.01432 0.00879 -0.0335 0.3827 0.9215
8.500 1.0648 0.01496 0.00942 -0.0313 0.3700 0.9230
8.750 1.0717 0.01576 0.01017 -0.0287 0.3534 0.9247
9.000 1.0779 0.01664 0.01100 -0.0262 0.3357 0.9263
9.250 1.0817 0.01767 0.01195 -0.0235 0.3145 0.9280
9.500 1.0869 0.01869 0.01290 -0.0211 0.2932 0.9297
9.750 1.0901 0.01984 0.01394 -0.0185 0.2707 0.9316
10.000 1.0935 0.02104 0.01504 -0.0161 0.2467 0.9332
10.250 1.0982 0.02223 0.01615 -0.0140 0.2259 0.9348
10.500 1.1022 0.02351 0.01733 -0.0119 0.2019 0.9365
11.000 1.1145 0.02601 0.01968 -0.0085 0.1629 0.9396
11.250 1.1179 0.02753 0.02107 -0.0067 0.1394 0.9413
11.500 1.1249 0.02892 0.02239 -0.0055 0.1212 0.9428
12.000 1.1354 0.03221 0.02550 -0.0032 0.0814 0.9460
12.250 1.1415 0.03400 0.02719 -0.0024 0.0640 0.9480
12.500 1.1461 0.03602 0.02911 -0.0018 0.0463 0.9501
12.750 1.1567 0.03765 0.03074 -0.0017 0.0382 0.9521
13.000 1.1676 0.03932 0.03242 -0.0017 0.0319 0.9541
13.250 1.1780 0.04109 0.03420 -0.0018 0.0262 0.9561
13.500 1.1893 0.04289 0.03605 -0.0021 0.0223 0.9583
13.750 1.2006 0.04485 0.03804 -0.0027 0.0187 0.9610
14.000 1.2126 0.04682 0.04006 -0.0034 0.0159 0.9637
14.250 1.2240 0.04883 0.04213 -0.0041 0.0142 0.9667
14.500 1.2330 0.05085 0.04420 -0.0044 0.0127 0.9754
14.750 1.2421 0.05311 0.04653 -0.0051 0.0114 0.9937
15.000 1.2418 0.05492 0.04840 -0.0031 0.0107 1.0000
15.250 1.2463 0.05719 0.05074 -0.0029 0.0098 1.0000
15.500 1.2500 0.05958 0.05318 -0.0027 0.0092 1.0000
15.750 1.2542 0.06198 0.05566 -0.0026 0.0087 1.0000
16.000 1.2586 0.06439 0.05814 -0.0027 0.0081 1.0000
16.250 1.2612 0.06705 0.06088 -0.0028 0.0077 1.0000
16.500 1.2627 0.06990 0.06379 -0.0029 0.0072 1.0000
16.750 1.2615 0.07312 0.06710 -0.0032 0.0069 1.0000
17.000 1.2627 0.07611 0.07019 -0.0036 0.0068 1.0000
17.250 1.2649 0.07902 0.07319 -0.0041 0.0066 1.0000
17.500 1.2646 0.08231 0.07657 -0.0046 0.0061 1.0000
17.750 1.2641 0.08569 0.08005 -0.0053 0.0062 1.0000
18.000 1.2620 0.08930 0.08376 -0.0062 0.0059 1.0000
18.250 1.2602 0.09295 0.08751 -0.0071 0.0057 1.0000
18.500 1.2581 0.09671 0.09136 -0.0082 0.0057 1.0000
18.750 1.2554 0.10059 0.09533 -0.0094 0.0055 1.0000
19.000 1.2518 0.10468 0.09952 -0.0107 0.0054 1.0000
19.250 1.2467 0.10901 0.10395 -0.0122 0.0053 1.0000
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Polar data table (+)
Polar graphs
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