AH 93-W-215 (ah93w215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-215 (ah93w215-il) Reynolds number: 100,000 Max Cl/Cd: 6.2 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w215-il-100000.txt Download as CSV file: xf-ah93w215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5765 0.07821 0.07279 -0.0795 1.0000 0.1237
-12.750 -0.6388 0.06948 0.06402 -0.0818 1.0000 0.1226
-12.500 -0.6917 0.06294 0.05740 -0.0846 0.9891 0.1219
-12.250 -0.7288 0.05567 0.04965 -0.0899 0.9590 0.1222
-12.000 -0.7507 0.05097 0.04442 -0.0916 0.9402 0.1232
-11.750 -0.7439 0.04719 0.04029 -0.0935 0.9277 0.1255
-11.500 -0.6927 0.04567 0.03888 -0.0983 0.9193 0.1301
-11.250 -0.6710 0.04251 0.03530 -0.1017 0.9100 0.1339
-11.000 -0.6667 0.04009 0.03228 -0.1017 0.8962 0.1369
-10.750 -0.6167 0.03807 0.03034 -0.1068 0.8886 0.1421
-10.500 -0.5912 0.03661 0.02866 -0.1082 0.8774 0.1469
-10.250 -0.5817 0.03529 0.02685 -0.1071 0.8673 0.1510
-10.000 -0.5422 0.03388 0.02559 -0.1100 0.8591 0.1567
-9.750 -0.5157 0.03278 0.02425 -0.1110 0.8518 0.1627
-9.500 -0.5073 0.03193 0.02321 -0.1086 0.8424 0.1672
-9.250 -0.4729 0.03101 0.02236 -0.1104 0.8354 0.1741
-9.000 -0.4602 0.03042 0.02153 -0.1085 0.8283 0.1801
-8.750 -0.4385 0.02961 0.02080 -0.1079 0.8214 0.1867
-8.500 -0.4177 0.02907 0.02016 -0.1072 0.8156 0.1945
-8.250 -0.3945 0.02836 0.01941 -0.1069 0.8104 0.2026
-8.000 -0.3834 0.02810 0.01920 -0.1043 0.8036 0.2103
-7.750 -0.3650 0.02753 0.01858 -0.1030 0.7977 0.2194
-7.500 -0.3423 0.02709 0.01810 -0.1024 0.7930 0.2306
-7.250 -0.3265 0.02674 0.01786 -0.1007 0.7881 0.2407
-7.000 -0.3197 0.02665 0.01770 -0.0973 0.7826 0.2517
-6.750 -0.3000 0.02624 0.01746 -0.0962 0.7775 0.2654
-6.500 -0.2784 0.02583 0.01711 -0.0953 0.7731 0.2817
-6.250 -0.2662 0.02568 0.01708 -0.0928 0.7685 0.2977
-6.000 -0.2622 0.02571 0.01724 -0.0890 0.7631 0.3136
-5.750 -0.2516 0.02562 0.01731 -0.0863 0.7585 0.3341
-5.500 -0.2362 0.02544 0.01725 -0.0842 0.7544 0.3612
-5.250 -0.2159 0.02530 0.01729 -0.0828 0.7508 0.3939
-5.000 -0.2256 0.02588 0.01806 -0.0767 0.7447 0.4152
-4.750 -0.2251 0.02632 0.01862 -0.0722 0.7395 0.4440
-4.500 -0.2104 0.02664 0.01908 -0.0696 0.7354 0.4763
-4.250 -0.1839 0.02689 0.01938 -0.0688 0.7322 0.5100
-4.000 -0.1779 0.02764 0.02020 -0.0649 0.7274 0.5328
-3.750 -0.2035 0.02888 0.02152 -0.0568 0.7201 0.5456
-3.500 -0.1920 0.02953 0.02220 -0.0539 0.7157 0.5666
-3.250 -0.1594 0.02987 0.02255 -0.0538 0.7126 0.5898
-3.000 -0.1168 0.03011 0.02276 -0.0551 0.7102 0.6122
-2.750 -0.2303 0.03293 0.02573 -0.0356 0.6982 0.6076
-2.500 -0.2082 0.03340 0.02620 -0.0342 0.6942 0.6271
-2.250 -0.1620 0.03354 0.02631 -0.0360 0.6917 0.6482
-2.000 -0.2129 0.03574 0.02861 -0.0256 0.6838 0.6538
-1.750 -0.2429 0.03746 0.03031 -0.0187 0.6775 0.6652
-1.500 -0.2157 0.03793 0.03082 -0.0178 0.6734 0.6813
-1.250 -0.1711 0.03793 0.03079 -0.0188 0.6706 0.6986
-1.000 -0.1877 0.03948 0.03234 -0.0135 0.6651 0.7107
-0.750 -0.2156 0.04122 0.03415 -0.0072 0.6588 0.7201
-0.500 -0.2005 0.04184 0.03475 -0.0052 0.6542 0.7345
-0.250 -0.1630 0.04194 0.03480 -0.0054 0.6506 0.7515
0.000 -0.1111 0.04188 0.03469 -0.0070 0.6483 0.7681
0.250 -0.1819 0.04458 0.03751 0.0030 0.6405 0.7757
0.500 -0.1782 0.04535 0.03826 0.0060 0.6355 0.7911
0.750 -0.1464 0.04571 0.03863 0.0065 0.6313 0.8064
1.000 -0.0938 0.04564 0.03852 0.0054 0.6283 0.8245
1.250 -0.1447 0.04775 0.04072 0.0129 0.6217 0.8380
1.500 -0.1428 0.04858 0.04158 0.0159 0.6162 0.8557
1.750 -0.1143 0.04899 0.04198 0.0163 0.6118 0.8744
2.000 -0.2043 0.05474 0.04801 0.0215 0.6589 0.8903
2.250 -0.0812 0.05106 0.04406 0.0163 0.6000 0.9082
2.500 -0.1191 0.05677 0.05001 0.0147 0.6353 0.9251
2.750 0.0447 0.05180 0.04468 0.0060 0.5893 0.9321
3.000 0.0478 0.05483 0.04779 0.0031 0.5805 0.9453
3.250 0.1025 0.05580 0.04872 -0.0025 0.5740 0.9549
3.500 0.1886 0.05569 0.04852 -0.0099 0.5702 0.9595
3.750 0.1908 0.05938 0.05227 -0.0136 0.5600 0.9701
4.000 0.2517 0.05990 0.05276 -0.0192 0.5541 0.9780
4.250 0.3295 0.05953 0.05231 -0.0256 0.5512 0.9844
4.500 0.3277 0.06391 0.05677 -0.0297 0.5396 0.9996
4.750 0.3144 0.06335 0.05612 -0.0248 0.5358 1.0000
5.000 0.3314 0.06224 0.05490 -0.0222 0.5330 1.0000
5.250 0.2802 0.06530 0.05791 -0.0171 0.5235 1.0000
5.500 0.2965 0.06603 0.05856 -0.0164 0.5184 1.0000
5.750 0.3387 0.06554 0.05799 -0.0168 0.5151 1.0000
6.000 0.3091 0.06891 0.06135 -0.0143 0.5052 1.0000
6.250 0.3314 0.06959 0.06197 -0.0141 0.5001 1.0000
6.500 0.3738 0.06921 0.06151 -0.0145 0.4970 1.0000
6.750 0.3441 0.07299 0.06530 -0.0126 0.4867 1.0000
7.000 0.3717 0.07340 0.06568 -0.0125 0.4818 1.0000
7.250 0.4155 0.07287 0.06509 -0.0128 0.4790 1.0000
7.500 0.3785 0.07760 0.06985 -0.0113 0.4687 1.0000
7.750 0.4100 0.07773 0.06995 -0.0113 0.4638 1.0000
8.000 0.4570 0.07685 0.06902 -0.0115 0.4612 1.0000
8.250 0.4160 0.08216 0.07438 -0.0103 0.4500 1.0000
8.500 0.4517 0.08198 0.07418 -0.0103 0.4458 1.0000
8.750 0.5009 0.08078 0.07295 -0.0103 0.4434 1.0000
9.000 0.4550 0.08682 0.07904 -0.0097 0.4314 1.0000
9.250 0.4952 0.08622 0.07841 -0.0095 0.4278 1.0000
9.500 0.4731 0.09061 0.08283 -0.0092 0.4181 1.0000
9.750 0.4949 0.09154 0.08377 -0.0091 0.4129 1.0000
10.000 0.5387 0.09049 0.08270 -0.0089 0.4099 1.0000
10.250 0.5039 0.09624 0.08851 -0.0089 0.3992 1.0000
10.500 0.5373 0.09607 0.08833 -0.0087 0.3946 1.0000
10.750 0.5810 0.09494 0.08721 -0.0083 0.3922 1.0000
11.000 0.5365 0.10192 0.09424 -0.0088 0.3805 1.0000
11.250 0.5742 0.10130 0.09362 -0.0085 0.3767 1.0000
11.500 0.5534 0.10627 0.09864 -0.0090 0.3676 1.0000
11.750 0.5717 0.10749 0.09988 -0.0089 0.3619 1.0000
12.000 0.6177 0.10571 0.09811 -0.0082 0.3587 1.0000
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Polar data table (+)
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