AH 83-159 (ah83159-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 200,000 Max Cl/Cd: 63.46 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83159-il-200000-n5.txt Download as CSV file: xf-ah83159-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1916 0.09033 0.08591 -0.0948 0.7952 0.0144
-10.750 -0.1949 0.08557 0.08117 -0.0971 0.7923 0.0144
-10.500 -0.1993 0.08069 0.07631 -0.0995 0.7896 0.0143
-10.250 -0.2080 0.07467 0.07030 -0.1030 0.7871 0.0145
-10.000 -0.2199 0.06786 0.06349 -0.1079 0.7845 0.0140
-9.750 -0.2436 0.06078 0.05636 -0.1120 0.7807 0.0135
-9.500 -0.2641 0.05611 0.05158 -0.1127 0.7770 0.0138
-9.250 -0.2840 0.05229 0.04761 -0.1116 0.7736 0.0135
-9.000 -0.3034 0.04910 0.04424 -0.1088 0.7708 0.0135
-8.750 -0.3176 0.04610 0.04105 -0.1059 0.7675 0.0137
-8.500 -0.3242 0.04300 0.03771 -0.1034 0.7643 0.0139
-8.250 -0.3273 0.03976 0.03414 -0.1009 0.7615 0.0142
-8.000 -0.3253 0.03672 0.03074 -0.0985 0.7590 0.0142
-7.750 -0.3193 0.03373 0.02734 -0.0963 0.7568 0.0141
-7.500 -0.3087 0.03111 0.02433 -0.0945 0.7542 0.0141
-7.250 -0.2940 0.02883 0.02169 -0.0930 0.7513 0.0142
-7.000 -0.2758 0.02681 0.01930 -0.0918 0.7488 0.0144
-6.750 -0.2548 0.02508 0.01725 -0.0909 0.7466 0.0146
-6.500 -0.2318 0.02366 0.01553 -0.0903 0.7446 0.0149
-6.250 -0.2076 0.02243 0.01407 -0.0897 0.7428 0.0153
-6.000 -0.1837 0.02127 0.01276 -0.0892 0.7410 0.0159
-5.750 -0.1613 0.02041 0.01188 -0.0887 0.7381 0.0166
-5.500 -0.1383 0.01977 0.01121 -0.0882 0.7355 0.0175
-5.250 -0.1146 0.01926 0.01063 -0.0878 0.7333 0.0194
-5.000 -0.0905 0.01879 0.01004 -0.0873 0.7312 0.0210
-4.750 -0.0688 0.01804 0.00928 -0.0866 0.7294 0.0230
-4.500 -0.0453 0.01752 0.00870 -0.0861 0.7276 0.0254
-4.250 -0.0224 0.01709 0.00820 -0.0855 0.7252 0.0287
-4.000 0.0003 0.01672 0.00783 -0.0850 0.7225 0.0355
-3.750 0.0235 0.01633 0.00745 -0.0845 0.7202 0.0454
-3.500 0.0471 0.01593 0.00711 -0.0841 0.7180 0.0650
-3.250 0.0698 0.01539 0.00679 -0.0837 0.7160 0.1196
-3.000 0.0896 0.01449 0.00645 -0.0832 0.7141 0.2609
-2.750 0.1060 0.01329 0.00614 -0.0821 0.7125 0.4839
-2.500 0.1169 0.01323 0.00704 -0.0777 0.7097 0.6844
-2.250 0.1386 0.01384 0.00771 -0.0755 0.7071 0.7468
-2.000 0.1633 0.01434 0.00812 -0.0744 0.7046 0.7786
-1.750 0.1872 0.01490 0.00858 -0.0730 0.7025 0.8010
-1.500 0.2109 0.01537 0.00896 -0.0716 0.7007 0.8186
-1.250 0.2350 0.01567 0.00919 -0.0700 0.6992 0.8270
-1.000 0.2599 0.01581 0.00923 -0.0695 0.6972 0.8349
-0.750 0.2819 0.01598 0.00939 -0.0684 0.6940 0.8399
-0.500 0.3066 0.01606 0.00940 -0.0682 0.6914 0.8462
-0.250 0.3316 0.01608 0.00936 -0.0678 0.6891 0.8493
0.000 0.3578 0.01607 0.00928 -0.0675 0.6871 0.8522
0.250 0.3852 0.01603 0.00917 -0.0677 0.6853 0.8553
0.500 0.4138 0.01600 0.00905 -0.0682 0.6838 0.8585
0.750 0.4361 0.01613 0.00919 -0.0678 0.6803 0.8617
1.000 0.4595 0.01618 0.00924 -0.0672 0.6773 0.8637
1.250 0.4849 0.01619 0.00923 -0.0671 0.6748 0.8659
1.500 0.5119 0.01617 0.00918 -0.0673 0.6727 0.8681
1.750 0.5405 0.01613 0.00909 -0.0677 0.6708 0.8703
2.000 0.5696 0.01611 0.00903 -0.0684 0.6690 0.8724
2.250 0.5908 0.01632 0.00930 -0.0679 0.6648 0.8749
2.500 0.6144 0.01636 0.00936 -0.0674 0.6616 0.8766
2.750 0.6409 0.01634 0.00934 -0.0675 0.6590 0.8780
3.000 0.6695 0.01628 0.00927 -0.0679 0.6568 0.8795
3.250 0.6985 0.01622 0.00920 -0.0684 0.6546 0.8811
3.500 0.7169 0.01646 0.00953 -0.0673 0.6496 0.8834
3.750 0.7428 0.01649 0.00959 -0.0674 0.6460 0.8849
4.000 0.7722 0.01643 0.00954 -0.0681 0.6432 0.8864
4.250 0.8043 0.01632 0.00942 -0.0692 0.6408 0.8878
4.500 0.8197 0.01656 0.00977 -0.0675 0.6347 0.8897
4.750 0.8452 0.01652 0.00977 -0.0674 0.6305 0.8908
5.000 0.8753 0.01638 0.00966 -0.0680 0.6274 0.8918
5.250 0.8935 0.01656 0.00995 -0.0668 0.6220 0.8936
5.500 0.9161 0.01663 0.01008 -0.0663 0.6172 0.8954
5.750 0.9454 0.01653 0.01003 -0.0668 0.6135 0.8967
6.000 0.9640 0.01672 0.01032 -0.0657 0.6076 0.8983
6.250 0.9869 0.01679 0.01046 -0.0653 0.6020 0.8997
6.500 1.0183 0.01665 0.01036 -0.0662 0.5980 0.9007
6.750 1.0282 0.01698 0.01085 -0.0637 0.5899 0.9028
7.000 1.0554 0.01684 0.01075 -0.0637 0.5843 0.9040
7.250 1.0617 0.01713 0.01116 -0.0604 0.5751 0.9060
7.500 1.0812 0.01713 0.01122 -0.0593 0.5669 0.9075
7.750 1.0960 0.01727 0.01143 -0.0574 0.5567 0.9092
8.000 1.1048 0.01765 0.01189 -0.0548 0.5445 0.9117
8.250 1.1170 0.01799 0.01227 -0.0528 0.5303 0.9138
8.500 1.1315 0.01831 0.01260 -0.0512 0.5140 0.9154
8.750 1.1421 0.01879 0.01309 -0.0492 0.4946 0.9171
9.000 1.1522 0.01935 0.01359 -0.0471 0.4715 0.9188
9.250 1.1585 0.02015 0.01431 -0.0446 0.4435 0.9209
9.500 1.1602 0.02125 0.01526 -0.0418 0.4124 0.9235
9.750 1.1588 0.02265 0.01650 -0.0389 0.3804 0.9259
10.000 1.1574 0.02421 0.01792 -0.0363 0.3505 0.9279
10.750 1.1558 0.02933 0.02275 -0.0299 0.2692 0.9338
11.000 1.1547 0.03127 0.02459 -0.0281 0.2410 0.9364
11.250 1.1531 0.03339 0.02659 -0.0265 0.2114 0.9390
11.500 1.1519 0.03562 0.02869 -0.0251 0.1824 0.9415
12.000 1.1505 0.04041 0.03323 -0.0230 0.1249 0.9463
12.250 1.1509 0.04287 0.03556 -0.0223 0.0994 0.9493
12.500 1.1524 0.04533 0.03791 -0.0217 0.0774 0.9528
13.000 1.1584 0.05006 0.04255 -0.0211 0.0470 0.9674
13.500 1.1633 0.05465 0.04713 -0.0199 0.0314 1.0000
13.750 1.1679 0.05702 0.04955 -0.0197 0.0261 1.0000
14.000 1.1718 0.05954 0.05214 -0.0196 0.0225 1.0000
14.250 1.1759 0.06209 0.05479 -0.0195 0.0195 1.0000
14.500 1.1773 0.06502 0.05778 -0.0195 0.0172 1.0000
14.750 1.1806 0.06778 0.06067 -0.0196 0.0154 1.0000
15.000 1.1833 0.07066 0.06364 -0.0199 0.0139 1.0000
15.250 1.1833 0.07393 0.06698 -0.0202 0.0124 1.0000
15.500 1.1853 0.07704 0.07023 -0.0206 0.0117 1.0000
15.750 1.1876 0.08015 0.07346 -0.0211 0.0107 1.0000
16.000 1.1888 0.08345 0.07688 -0.0218 0.0102 1.0000
16.250 1.1878 0.08712 0.08064 -0.0226 0.0096 1.0000
16.500 1.1857 0.09101 0.08464 -0.0235 0.0093 1.0000
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Polar data table (+)
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