AH 83-159 (ah83159-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 200,000 Max Cl/Cd: 64.52 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah83159-il-200000.txt Download as CSV file: xf-ah83159-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1098 0.09594 0.09226 -0.0960 0.8458 0.0486
-11.000 -0.1167 0.09172 0.08804 -0.0988 0.8440 0.0489
-10.750 -0.1223 0.08712 0.08348 -0.1019 0.8416 0.0490
-10.500 -0.1089 0.08266 0.07903 -0.0997 0.8389 0.0507
-10.250 -0.0926 0.08120 0.07755 -0.0983 0.8358 0.0537
-10.000 -0.0928 0.07755 0.07389 -0.0994 0.8332 0.0551
-9.750 -0.0971 0.07338 0.06973 -0.1012 0.8310 0.0575
-9.500 -0.1797 0.07144 0.06764 -0.1181 0.8388 0.0514
-9.250 -0.1880 0.06798 0.06415 -0.1192 0.8348 0.0519
-9.000 -0.1962 0.06502 0.06115 -0.1193 0.8312 0.0527
-8.750 -0.2076 0.06231 0.05839 -0.1185 0.8276 0.0536
-8.500 -0.2233 0.06010 0.05615 -0.1168 0.8231 0.0543
-8.250 -0.2329 0.05797 0.05392 -0.1151 0.8194 0.0566
-8.000 -0.2415 0.05548 0.05125 -0.1132 0.8164 0.0582
-7.750 -0.2647 0.05758 0.05264 -0.1081 0.8119 0.0618
-7.500 -0.2546 0.05013 0.04549 -0.1093 0.8089 0.0646
-7.250 -0.2425 0.04819 0.04353 -0.1085 0.8058 0.0670
-7.000 -0.2348 0.04643 0.04154 -0.1068 0.8032 0.0719
-6.750 -0.2200 0.02938 0.02467 -0.1004 0.7934 0.0785
-6.500 -0.2062 0.02729 0.02253 -0.0996 0.7906 0.0815
-6.250 -0.2018 0.02505 0.01987 -0.0973 0.7880 0.0916
-6.000 -0.1877 0.03177 0.02484 -0.0971 0.7910 0.0363
-5.750 -0.1669 0.02921 0.02198 -0.0960 0.7889 0.0345
-5.500 -0.1430 0.02726 0.01970 -0.0951 0.7871 0.0338
-5.250 -0.1172 0.02573 0.01790 -0.0944 0.7855 0.0340
-5.000 -0.0963 0.02495 0.01702 -0.0935 0.7814 0.0347
-4.750 -0.0733 0.02437 0.01632 -0.0928 0.7780 0.0367
-4.500 -0.0504 0.02321 0.01514 -0.0920 0.7756 0.0401
-4.250 -0.0273 0.02244 0.01438 -0.0912 0.7737 0.0437
-4.000 -0.0035 0.02182 0.01366 -0.0904 0.7720 0.0486
-3.750 0.0146 0.02124 0.01315 -0.0891 0.7694 0.0591
-3.500 0.0268 0.02122 0.01320 -0.0873 0.7641 0.0735
-3.250 0.0413 0.02026 0.01274 -0.0858 0.7612 0.1577
-3.000 0.0377 0.01808 0.01286 -0.0807 0.7587 0.6438
-2.750 0.0545 0.01930 0.01428 -0.0755 0.7572 0.7677
-2.500 0.0636 0.02072 0.01564 -0.0719 0.7522 0.7958
-2.250 0.0746 0.02182 0.01667 -0.0685 0.7476 0.8178
-2.000 0.0924 0.02246 0.01722 -0.0651 0.7452 0.8346
-1.750 0.1119 0.02295 0.01763 -0.0614 0.7437 0.8523
-1.500 0.1324 0.02329 0.01787 -0.0581 0.7425 0.8742
-1.250 0.1113 0.02463 0.01928 -0.0506 0.7331 0.8881
-1.000 0.1647 0.02483 0.01937 -0.0529 0.7324 0.9098
-0.750 0.2153 0.02475 0.01915 -0.0569 0.7313 0.9193
-0.500 0.2719 0.02461 0.01887 -0.0625 0.7305 0.9237
-0.250 0.2976 0.02440 0.01857 -0.0622 0.7290 0.9305
0.000 0.3537 0.02407 0.01812 -0.0677 0.7283 0.9326
0.250 0.4002 0.02377 0.01772 -0.0715 0.7275 0.9353
0.500 0.3704 0.02534 0.01939 -0.0633 0.7168 0.9453
0.750 0.4147 0.02504 0.01902 -0.0667 0.7156 0.9473
1.000 0.4537 0.02476 0.01868 -0.0690 0.7145 0.9497
1.250 0.4890 0.02444 0.01829 -0.0705 0.7135 0.9524
1.500 0.5161 0.02413 0.01793 -0.0703 0.7125 0.9554
1.750 0.5025 0.02578 0.01967 -0.0656 0.7011 0.9612
2.000 0.5419 0.02538 0.01923 -0.0678 0.7001 0.9627
2.250 0.5803 0.02496 0.01878 -0.0698 0.6992 0.9643
2.500 0.6169 0.02452 0.01831 -0.0714 0.6984 0.9658
2.750 0.5879 0.02633 0.02020 -0.0638 0.6863 0.9722
3.000 0.5853 0.02786 0.02178 -0.0610 0.6767 0.9768
3.250 0.6155 0.02765 0.02157 -0.0617 0.6740 0.9784
3.500 0.6533 0.02709 0.02102 -0.0632 0.6728 0.9793
3.750 0.6937 0.02642 0.02035 -0.0652 0.6720 0.9802
4.000 0.7349 0.02569 0.01962 -0.0673 0.6712 0.9810
4.250 0.7758 0.02493 0.01889 -0.0692 0.6704 0.9815
4.500 0.8169 0.02417 0.01813 -0.0712 0.6695 0.9820
4.750 0.8102 0.02577 0.01984 -0.0677 0.6580 0.9864
5.000 0.8539 0.02494 0.01905 -0.0701 0.6571 0.9867
5.250 0.8760 0.02509 0.01926 -0.0698 0.6526 0.9886
5.500 0.9365 0.02348 0.01767 -0.0744 0.6546 0.9876
5.750 0.9316 0.02469 0.01901 -0.0705 0.6440 0.9922
6.000 0.9767 0.02373 0.01810 -0.0730 0.6428 0.9925
6.250 1.0224 0.02278 0.01721 -0.0758 0.6416 0.9927
6.500 1.0193 0.02384 0.01838 -0.0720 0.6313 0.9969
6.750 1.0656 0.02273 0.01736 -0.0746 0.6294 0.9969
7.000 1.1163 0.02143 0.01612 -0.0779 0.6275 0.9966
7.250 1.1176 0.02198 0.01679 -0.0743 0.6178 1.0000
7.500 1.1743 0.02044 0.01533 -0.0784 0.6142 1.0000
7.750 1.1542 0.02081 0.01578 -0.0703 0.6052 1.0000
8.000 1.2134 0.01919 0.01420 -0.0748 0.5989 1.0000
8.250 1.1721 0.01981 0.01489 -0.0630 0.5897 1.0000
8.500 1.1938 0.01902 0.01414 -0.0615 0.5813 1.0000
8.750 1.1932 0.01873 0.01388 -0.0564 0.5711 1.0000
9.000 1.1924 0.01888 0.01411 -0.0522 0.5579 1.0000
9.250 1.2078 0.01872 0.01397 -0.0505 0.5417 1.0000
9.500 1.2115 0.01934 0.01464 -0.0478 0.5231 1.0000
9.750 1.2226 0.01978 0.01508 -0.0460 0.5014 1.0000
10.000 1.2325 0.02044 0.01572 -0.0443 0.4781 1.0000
10.250 1.2407 0.02127 0.01648 -0.0424 0.4509 1.0000
10.500 1.2450 0.02242 0.01752 -0.0403 0.4211 1.0000
10.750 1.2455 0.02389 0.01884 -0.0380 0.3898 1.0000
11.000 1.2424 0.02566 0.02049 -0.0355 0.3575 1.0000
11.250 1.2368 0.02772 0.02237 -0.0330 0.3251 1.0000
11.500 1.2295 0.03001 0.02450 -0.0307 0.2913 1.0000
11.750 1.2210 0.03257 0.02688 -0.0285 0.2556 1.0000
12.000 1.2114 0.03540 0.02950 -0.0265 0.2179 1.0000
12.250 1.2008 0.03849 0.03234 -0.0248 0.1797 1.0000
12.500 1.1907 0.04170 0.03531 -0.0232 0.1422 1.0000
12.750 1.1813 0.04502 0.03838 -0.0219 0.1075 1.0000
13.000 1.1734 0.04834 0.04150 -0.0208 0.0808 1.0000
13.250 1.1667 0.05169 0.04469 -0.0200 0.0631 1.0000
13.500 1.1625 0.05492 0.04788 -0.0193 0.0511 1.0000
13.750 1.1582 0.05826 0.05121 -0.0188 0.0426 1.0000
14.000 1.1574 0.06135 0.05438 -0.0184 0.0359 1.0000
14.250 1.1509 0.06510 0.05813 -0.0180 0.0317 1.0000
14.500 1.1542 0.06785 0.06101 -0.0179 0.0280 1.0000
14.750 1.1535 0.07105 0.06424 -0.0179 0.0255 1.0000
15.000 1.1550 0.07395 0.06718 -0.0175 0.0235 1.0000
15.250 1.1610 0.07650 0.06986 -0.0176 0.0215 1.0000
15.500 1.1679 0.07885 0.07229 -0.0176 0.0204 1.0000
15.750 1.1743 0.08129 0.07477 -0.0176 0.0193 1.0000
16.000 1.1848 0.08309 0.07659 -0.0171 0.0184 1.0000
16.250 1.2011 0.08440 0.07801 -0.0158 0.0175 1.0000
16.500 1.2090 0.08696 0.08077 -0.0159 0.0172 1.0000
16.750 1.2154 0.08979 0.08381 -0.0160 0.0169 1.0000
17.000 1.2191 0.09309 0.08734 -0.0162 0.0167 1.0000
17.250 1.2191 0.09692 0.09143 -0.0168 0.0166 1.0000
17.500 1.2157 0.10128 0.09605 -0.0177 0.0165 1.0000
17.750 1.2084 0.10627 0.10129 -0.0191 0.0164 1.0000
18.000 1.1997 0.11146 0.10672 -0.0209 0.0164 1.0000
18.250 1.1883 0.11726 0.11276 -0.0232 0.0163 1.0000
18.500 1.1758 0.12336 0.11909 -0.0260 0.0163 1.0000
18.750 1.1614 0.13002 0.12598 -0.0293 0.0164 1.0000
19.000 1.1450 0.13730 0.13347 -0.0332 0.0165 1.0000
19.250 1.1282 0.14493 0.14131 -0.0377 0.0165 1.0000
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Polar data table (+)
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