AH 83-159 (ah83159-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 500,000 Max Cl/Cd: 106.15 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah83159-il-500000.txt Download as CSV file: xf-ah83159-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-159
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1695 0.08555 0.08229 -0.1020 0.7858 0.0209
-10.500 -0.1712 0.08062 0.07739 -0.1048 0.7834 0.0209
-10.250 -0.1771 0.07387 0.07066 -0.1095 0.7806 0.0210
-10.000 -0.1903 0.06712 0.06386 -0.1145 0.7777 0.0210
-9.750 -0.2097 0.06232 0.05897 -0.1167 0.7747 0.0210
-9.500 -0.2301 0.05868 0.05520 -0.1167 0.7718 0.0210
-9.250 -0.2459 0.05593 0.05236 -0.1153 0.7688 0.0210
-9.000 -0.2645 0.05357 0.04992 -0.1123 0.7653 0.0210
-8.750 -0.2794 0.05128 0.04748 -0.1092 0.7623 0.0211
-8.500 -0.2866 0.04876 0.04477 -0.1067 0.7597 0.0211
-8.250 -0.3071 0.04206 0.03795 -0.1045 0.7575 0.0221
-8.000 -0.2999 0.04004 0.03582 -0.1032 0.7553 0.0224
-7.750 -0.2902 0.03835 0.03408 -0.1020 0.7528 0.0230
-7.500 -0.2801 0.03641 0.03200 -0.1006 0.7502 0.0237
-7.250 -0.2687 0.03433 0.02972 -0.0991 0.7477 0.0246
-7.000 -0.2772 0.02432 0.01837 -0.0923 0.7455 0.0161
-6.750 -0.2551 0.02307 0.01688 -0.0915 0.7436 0.0158
-6.500 -0.2333 0.02126 0.01480 -0.0908 0.7417 0.0159
-6.250 -0.2102 0.01950 0.01288 -0.0903 0.7398 0.0162
-6.000 -0.1853 0.01826 0.01149 -0.0899 0.7376 0.0161
-5.750 -0.1601 0.01719 0.01032 -0.0895 0.7353 0.0160
-5.500 -0.1358 0.01604 0.00909 -0.0890 0.7331 0.0164
-5.250 -0.1120 0.01520 0.00820 -0.0885 0.7311 0.0169
-5.000 -0.0877 0.01462 0.00757 -0.0881 0.7293 0.0177
-4.750 -0.0632 0.01414 0.00703 -0.0877 0.7276 0.0187
-4.500 -0.0390 0.01372 0.00658 -0.0873 0.7256 0.0202
-4.250 -0.0162 0.01312 0.00595 -0.0866 0.7233 0.0225
-4.000 0.0088 0.01277 0.00560 -0.0864 0.7210 0.0264
-3.750 0.0337 0.01237 0.00520 -0.0861 0.7190 0.0342
-3.500 0.0592 0.01200 0.00483 -0.0860 0.7171 0.0486
-3.250 0.0834 0.01145 0.00452 -0.0858 0.7152 0.1059
-3.000 0.1038 0.01047 0.00424 -0.0854 0.7134 0.2906
-2.750 0.1210 0.00914 0.00395 -0.0847 0.7114 0.5664
-2.500 0.1405 0.00890 0.00440 -0.0828 0.7093 0.7368
-2.250 0.1675 0.00923 0.00472 -0.0823 0.7070 0.7708
-2.000 0.1958 0.00952 0.00493 -0.0823 0.7049 0.7893
-1.750 0.2227 0.00991 0.00528 -0.0817 0.7029 0.7983
-1.500 0.2493 0.01034 0.00567 -0.0810 0.7011 0.8085
-1.250 0.2760 0.01077 0.00603 -0.0803 0.6994 0.8195
-1.000 0.2995 0.01126 0.00651 -0.0787 0.6976 0.8261
-0.750 0.3252 0.01148 0.00672 -0.0782 0.6953 0.8342
-0.500 0.3485 0.01169 0.00694 -0.0769 0.6930 0.8383
-0.250 0.3751 0.01181 0.00703 -0.0766 0.6908 0.8441
0.000 0.4023 0.01184 0.00701 -0.0767 0.6887 0.8486
0.250 0.4280 0.01187 0.00702 -0.0761 0.6868 0.8512
0.500 0.4555 0.01191 0.00700 -0.0761 0.6850 0.8543
0.750 0.4839 0.01197 0.00702 -0.0766 0.6830 0.8578
1.000 0.5121 0.01199 0.00704 -0.0772 0.6805 0.8613
1.250 0.5370 0.01193 0.00700 -0.0768 0.6779 0.8630
1.500 0.5634 0.01189 0.00696 -0.0767 0.6754 0.8647
1.750 0.5911 0.01185 0.00690 -0.0769 0.6732 0.8666
2.000 0.6201 0.01183 0.00684 -0.0774 0.6711 0.8686
2.250 0.6491 0.01186 0.00684 -0.0780 0.6687 0.8708
2.500 0.6766 0.01187 0.00689 -0.0785 0.6655 0.8732
2.750 0.7052 0.01185 0.00688 -0.0791 0.6624 0.8750
3.000 0.7318 0.01173 0.00677 -0.0791 0.6595 0.8764
3.250 0.7602 0.01165 0.00666 -0.0794 0.6567 0.8776
3.500 0.7868 0.01163 0.00666 -0.0795 0.6535 0.8791
3.750 0.8122 0.01160 0.00669 -0.0793 0.6496 0.8808
4.000 0.8401 0.01156 0.00667 -0.0797 0.6462 0.8822
4.250 0.8695 0.01152 0.00662 -0.0804 0.6432 0.8836
4.500 0.8989 0.01154 0.00664 -0.0811 0.6402 0.8851
4.750 0.9251 0.01155 0.00673 -0.0813 0.6359 0.8868
5.000 0.9539 0.01154 0.00676 -0.0820 0.6319 0.8879
5.250 0.9827 0.01148 0.00670 -0.0825 0.6284 0.8889
5.500 1.0083 0.01144 0.00672 -0.0824 0.6244 0.8900
5.750 1.0323 0.01139 0.00675 -0.0820 0.6191 0.8914
6.000 1.0591 0.01132 0.00670 -0.0821 0.6142 0.8927
6.250 1.0838 0.01131 0.00676 -0.0818 0.6081 0.8939
6.500 1.1088 0.01125 0.00675 -0.0816 0.6011 0.8950
6.750 1.1330 0.01124 0.00679 -0.0813 0.5929 0.8963
7.000 1.1578 0.01122 0.00678 -0.0811 0.5842 0.8975
7.250 1.1794 0.01126 0.00691 -0.0803 0.5733 0.8992
7.500 1.2007 0.01133 0.00701 -0.0795 0.5598 0.9005
7.750 1.2186 0.01148 0.00712 -0.0780 0.5413 0.9016
8.000 1.2329 0.01165 0.00730 -0.0760 0.5213 0.9029
8.250 1.2413 0.01188 0.00751 -0.0727 0.5019 0.9045
8.500 1.2422 0.01227 0.00786 -0.0682 0.4801 0.9068
8.750 1.2417 0.01293 0.00844 -0.0638 0.4569 0.9089
9.000 1.2360 0.01392 0.00933 -0.0591 0.4286 0.9110
9.250 1.2318 0.01508 0.01038 -0.0550 0.4016 0.9130
9.500 1.2244 0.01654 0.01170 -0.0509 0.3715 0.9151
9.750 1.2141 0.01822 0.01323 -0.0465 0.3391 0.9169
10.000 1.2102 0.01972 0.01462 -0.0433 0.3121 0.9186
10.250 1.2027 0.02154 0.01629 -0.0398 0.2810 0.9202
10.500 1.1969 0.02340 0.01798 -0.0368 0.2474 0.9218
10.750 1.1908 0.02537 0.01978 -0.0339 0.2130 0.9237
11.000 1.1861 0.02737 0.02160 -0.0314 0.1807 0.9253
11.250 1.1841 0.02935 0.02342 -0.0293 0.1503 0.9265
11.500 1.1834 0.03132 0.02526 -0.0275 0.1229 0.9276
11.750 1.1810 0.03351 0.02726 -0.0257 0.0932 0.9286
12.000 1.1834 0.03543 0.02907 -0.0244 0.0734 0.9296
12.250 1.1870 0.03731 0.03089 -0.0233 0.0572 0.9307
12.500 1.1902 0.03927 0.03278 -0.0223 0.0435 0.9320
12.750 1.1948 0.04119 0.03468 -0.0214 0.0339 0.9336
13.000 1.2000 0.04316 0.03664 -0.0207 0.0264 0.9350
13.250 1.2036 0.04533 0.03882 -0.0200 0.0199 0.9363
13.500 1.2071 0.04762 0.04115 -0.0194 0.0155 0.9375
13.750 1.2058 0.05043 0.04400 -0.0186 0.0128 0.9387
14.000 1.2132 0.05247 0.04615 -0.0184 0.0113 0.9400
14.250 1.2184 0.05481 0.04855 -0.0183 0.0101 0.9413
14.500 1.2194 0.05768 0.05150 -0.0181 0.0095 0.9426
14.750 1.2156 0.06118 0.05513 -0.0180 0.0091 0.9439
15.000 1.2213 0.06377 0.05782 -0.0183 0.0089 0.9457
15.250 1.2267 0.06645 0.06061 -0.0188 0.0083 0.9478
15.500 1.2327 0.06916 0.06343 -0.0194 0.0081 0.9502
15.750 1.2339 0.07252 0.06690 -0.0200 0.0079 0.9525
16.000 1.2409 0.07534 0.06980 -0.0210 0.0075 0.9554
16.250 1.2444 0.07868 0.07323 -0.0222 0.0071 0.9616
16.500 1.2432 0.08178 0.07643 -0.0224 0.0069 1.0000
16.750 1.2423 0.08533 0.08009 -0.0230 0.0068 1.0000
17.000 1.2401 0.08909 0.08394 -0.0237 0.0066 1.0000
17.250 1.2386 0.09275 0.08770 -0.0244 0.0065 1.0000
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