AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 50,000 Max Cl/Cd: 28.23 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5046-il-50000.txt Download as CSV file: xf-as5046-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5143 0.10928 0.10245 -0.0297 1.0000 0.1520
-10.750 -0.5732 0.09302 0.08631 -0.0427 1.0000 0.1291
-10.500 -0.6028 0.08505 0.07831 -0.0473 1.0000 0.1224
-10.250 -0.6323 0.07866 0.07189 -0.0498 1.0000 0.1186
-10.000 -0.6751 0.07356 0.06672 -0.0505 1.0000 0.1162
-9.750 -0.7252 0.06975 0.06259 -0.0487 1.0000 0.1133
-9.500 -0.7260 0.06587 0.05856 -0.0475 1.0000 0.1094
-9.250 -0.7287 0.06199 0.05454 -0.0460 1.0000 0.1065
-9.000 -0.7379 0.05846 0.05074 -0.0436 1.0000 0.1033
-8.750 -0.7533 0.05560 0.04737 -0.0400 1.0000 0.0997
-8.500 -0.7648 0.05442 0.04574 -0.0355 1.0000 0.0977
-8.250 -0.7652 0.05208 0.04331 -0.0323 1.0000 0.0968
-8.000 -0.7640 0.04988 0.04092 -0.0292 1.0000 0.0959
-7.750 -0.7595 0.04773 0.03852 -0.0266 1.0000 0.0955
-7.500 -0.7515 0.04569 0.03618 -0.0242 1.0000 0.0956
-7.250 -0.7403 0.04379 0.03395 -0.0221 1.0000 0.0964
-7.000 -0.7261 0.04205 0.03186 -0.0203 1.0000 0.0974
-6.750 -0.7070 0.04006 0.02971 -0.0188 1.0000 0.0987
-6.500 -0.6833 0.03823 0.02787 -0.0175 1.0000 0.1007
-6.250 -0.6578 0.03695 0.02662 -0.0159 1.0000 0.1038
-6.000 -0.6340 0.03610 0.02570 -0.0140 1.0000 0.1096
-5.750 -0.6132 0.03522 0.02496 -0.0117 1.0000 0.1174
-5.500 -0.5987 0.03446 0.02412 -0.0090 1.0000 0.1259
-5.250 -0.5899 0.03329 0.02313 -0.0064 1.0000 0.1374
-5.000 -0.5820 0.03186 0.02189 -0.0043 1.0000 0.1575
-4.750 -0.5773 0.02884 0.01986 -0.0033 1.0000 0.2291
-4.500 -0.4125 0.04964 0.04216 0.0224 1.0000 0.8051
-4.250 -0.3819 0.04882 0.04103 0.0213 1.0000 0.8273
-4.000 -0.3652 0.04798 0.03999 0.0218 1.0000 0.8467
-3.750 -0.3472 0.04716 0.03897 0.0219 1.0000 0.8645
-3.500 -0.3242 0.04633 0.03793 0.0210 1.0000 0.8809
-3.250 -0.2969 0.04551 0.03692 0.0193 1.0000 0.8960
-3.000 -0.2693 0.04474 0.03596 0.0173 1.0000 0.9095
-2.750 -0.2476 0.04406 0.03512 0.0162 1.0000 0.9212
-2.500 -0.2406 0.04356 0.03451 0.0175 1.0000 0.9311
-2.250 -0.2081 0.04297 0.03376 0.0143 1.0000 0.9412
-2.000 -0.1901 0.04252 0.03320 0.0136 1.0000 0.9496
-1.750 -0.1699 0.04216 0.03272 0.0124 1.0000 0.9575
-1.500 -0.1486 0.04185 0.03231 0.0110 1.0000 0.9646
-1.250 -0.1302 0.04164 0.03202 0.0100 1.0000 0.9713
-1.000 -0.1075 0.04148 0.03177 0.0083 1.0000 0.9774
-0.750 -0.0880 0.04143 0.03164 0.0070 1.0000 0.9834
-0.500 -0.0415 0.04146 0.03159 0.0006 0.9949 0.9888
-0.250 0.0079 0.04158 0.03162 -0.0063 0.9869 0.9941
0.000 0.0585 0.04169 0.03169 -0.0135 0.9782 0.9988
0.250 0.0926 0.04187 0.03183 -0.0174 0.9692 1.0000
0.500 0.1245 0.04211 0.03204 -0.0207 0.9598 1.0000
0.750 0.1498 0.04236 0.03229 -0.0228 0.9496 1.0000
1.000 0.1717 0.04268 0.03261 -0.0241 0.9389 1.0000
1.250 0.1987 0.04307 0.03301 -0.0263 0.9276 1.0000
1.500 0.2335 0.04350 0.03346 -0.0297 0.9158 1.0000
1.750 0.2533 0.04395 0.03394 -0.0303 0.9030 1.0000
2.000 0.2701 0.04449 0.03451 -0.0304 0.8896 1.0000
2.250 0.2916 0.04506 0.03513 -0.0312 0.8757 1.0000
2.500 0.3169 0.04566 0.03578 -0.0324 0.8611 1.0000
2.750 0.3437 0.04625 0.03642 -0.0337 0.8457 1.0000
3.000 0.3689 0.04685 0.03709 -0.0345 0.8295 1.0000
3.250 0.3906 0.04746 0.03777 -0.0347 0.8126 1.0000
3.500 0.4077 0.04808 0.03846 -0.0339 0.7948 1.0000
3.750 0.4225 0.04870 0.03914 -0.0328 0.7763 1.0000
4.000 0.4387 0.04925 0.03976 -0.0316 0.7573 1.0000
4.250 0.4605 0.04966 0.04026 -0.0310 0.7380 1.0000
4.500 0.4918 0.04982 0.04052 -0.0313 0.7187 1.0000
4.750 0.5402 0.04952 0.04035 -0.0335 0.6997 1.0000
5.000 0.5533 0.04972 0.04065 -0.0311 0.6808 1.0000
5.250 0.5418 0.05033 0.04129 -0.0259 0.6621 1.0000
5.500 0.5388 0.05067 0.04168 -0.0217 0.6436 1.0000
5.750 0.5420 0.05079 0.04187 -0.0182 0.6255 1.0000
6.000 0.5524 0.05067 0.04182 -0.0154 0.6077 1.0000
6.250 0.5809 0.04995 0.04123 -0.0143 0.5897 1.0000
6.500 0.6236 0.04848 0.03991 -0.0140 0.5723 1.0000
6.750 0.6820 0.04580 0.03745 -0.0144 0.5552 1.0000
7.000 0.7400 0.04259 0.03442 -0.0143 0.5386 1.0000
7.250 0.7417 0.04304 0.03494 -0.0113 0.5173 1.0000
7.500 0.8053 0.03939 0.03144 -0.0115 0.4972 1.0000
7.750 0.8798 0.03548 0.02754 -0.0129 0.4716 1.0000
8.000 0.9216 0.03430 0.02625 -0.0130 0.4441 1.0000
8.250 0.9435 0.03476 0.02668 -0.0120 0.4189 1.0000
8.500 0.9818 0.03478 0.02648 -0.0127 0.3924 1.0000
8.750 0.9978 0.03614 0.02791 -0.0119 0.3701 1.0000
9.000 1.0260 0.03714 0.02882 -0.0122 0.3474 1.0000
9.250 1.0529 0.03840 0.02999 -0.0125 0.3261 1.0000
9.500 1.0703 0.04015 0.03184 -0.0121 0.3073 1.0000
9.750 1.0885 0.04191 0.03366 -0.0117 0.2891 1.0000
10.000 1.1067 0.04380 0.03562 -0.0114 0.2724 1.0000
10.250 1.1233 0.04583 0.03773 -0.0109 0.2571 1.0000
10.500 1.1399 0.04798 0.03993 -0.0104 0.2432 1.0000
10.750 1.1599 0.05011 0.04205 -0.0102 0.2297 1.0000
11.000 1.1555 0.05314 0.04543 -0.0082 0.2211 1.0000
11.250 1.1613 0.05602 0.04845 -0.0071 0.2121 1.0000
11.500 1.1435 0.05978 0.05253 -0.0046 0.2073 1.0000
11.750 1.1603 0.06238 0.05513 -0.0042 0.1983 1.0000
12.000 1.1240 0.06714 0.06018 -0.0015 0.1975 1.0000
12.250 1.0816 0.07345 0.06672 -0.0008 0.1979 1.0000
12.500 1.0341 0.08169 0.07510 -0.0023 0.1991 1.0000
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Polar data table (+)
Polar graphs
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