AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 50,000 Max Cl/Cd: 23.64 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5048-il-50000-n5.txt Download as CSV file: xf-as5048-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6394 0.09275 0.08461 -0.0628 1.0000 0.0397
-13.000 -0.6582 0.08764 0.07938 -0.0642 1.0000 0.0396
-12.750 -0.6770 0.08295 0.07455 -0.0650 1.0000 0.0395
-12.500 -0.6961 0.07864 0.07008 -0.0652 1.0000 0.0394
-12.250 -0.7132 0.07480 0.06606 -0.0648 1.0000 0.0394
-12.000 -0.7302 0.07130 0.06235 -0.0638 1.0000 0.0395
-11.750 -0.7454 0.06817 0.05901 -0.0621 1.0000 0.0396
-11.500 -0.7532 0.06533 0.05606 -0.0604 1.0000 0.0400
-11.250 -0.7513 0.06284 0.05354 -0.0590 1.0000 0.0407
-11.000 -0.7531 0.06052 0.05112 -0.0570 1.0000 0.0413
-10.750 -0.7554 0.05832 0.04878 -0.0546 1.0000 0.0418
-10.500 -0.7560 0.05621 0.04651 -0.0520 1.0000 0.0423
-10.250 -0.7536 0.05415 0.04428 -0.0495 1.0000 0.0429
-10.000 -0.7459 0.05211 0.04205 -0.0474 1.0000 0.0434
-9.750 -0.7330 0.05019 0.03994 -0.0457 1.0000 0.0441
-9.500 -0.7124 0.04838 0.03793 -0.0447 1.0000 0.0450
-9.250 -0.6930 0.04701 0.03633 -0.0433 1.0000 0.0466
-9.000 -0.6575 0.04568 0.03504 -0.0438 1.0000 0.0493
-8.750 -0.6406 0.04511 0.03446 -0.0417 1.0000 0.0516
-8.250 -0.5674 0.04357 0.03276 -0.0424 0.9916 0.0578
-8.000 -0.5413 0.04236 0.03147 -0.0433 0.9799 0.0628
-7.750 -0.5216 0.04103 0.03008 -0.0437 0.9673 0.0675
-7.500 -0.5058 0.03962 0.02861 -0.0438 0.9557 0.0729
-7.250 -0.4923 0.03806 0.02704 -0.0438 0.9456 0.0807
-7.000 -0.4795 0.03625 0.02532 -0.0440 0.9375 0.0950
-6.750 -0.4777 0.03429 0.02366 -0.0426 0.9273 0.1235
-6.500 -0.4864 0.03167 0.02184 -0.0403 0.9178 0.2198
-6.250 -0.4591 0.03376 0.02588 -0.0345 0.9140 0.5038
-6.000 -0.4423 0.03547 0.02741 -0.0316 0.9080 0.5818
-5.750 -0.4025 0.03976 0.03147 -0.0276 0.9040 0.6311
-5.500 -0.3732 0.04011 0.03153 -0.0274 0.8990 0.6444
-5.250 -0.3471 0.03989 0.03102 -0.0276 0.8943 0.6572
-5.000 -0.3250 0.03946 0.03033 -0.0276 0.8900 0.6710
-4.750 -0.2929 0.03974 0.03040 -0.0277 0.8856 0.6781
-4.500 -0.2790 0.03935 0.02982 -0.0264 0.8799 0.6898
-4.250 -0.2437 0.03924 0.02948 -0.0277 0.8766 0.6976
-4.000 -0.2217 0.03882 0.02887 -0.0276 0.8726 0.7073
-3.750 -0.2054 0.03879 0.02872 -0.0260 0.8669 0.7150
-3.500 -0.1909 0.03843 0.02822 -0.0247 0.8618 0.7238
-3.250 -0.1574 0.03824 0.02785 -0.0260 0.8586 0.7299
-3.000 -0.1525 0.03787 0.02737 -0.0234 0.8530 0.7391
-2.750 -0.1298 0.03789 0.02730 -0.0228 0.8481 0.7441
-2.500 -0.1145 0.03759 0.02688 -0.0217 0.8433 0.7517
-2.250 -0.0870 0.03728 0.02644 -0.0224 0.8399 0.7573
-2.000 -0.0730 0.03734 0.02644 -0.0206 0.8344 0.7626
-1.750 -0.0718 0.03713 0.02616 -0.0172 0.8280 0.7703
-1.500 -0.0424 0.03697 0.02591 -0.0181 0.8242 0.7745
-1.250 -0.0081 0.03680 0.02564 -0.0197 0.8213 0.7786
-1.000 -0.0203 0.03695 0.02578 -0.0140 0.8126 0.7854
-0.750 -0.0011 0.03677 0.02553 -0.0134 0.8078 0.7902
-0.500 0.0342 0.03665 0.02534 -0.0152 0.8045 0.7934
-0.250 0.0323 0.03690 0.02559 -0.0110 0.7964 0.7985
0.000 0.0485 0.03678 0.02541 -0.0100 0.7908 0.8035
0.250 0.0802 0.03659 0.02516 -0.0114 0.7871 0.8071
0.500 0.0816 0.03696 0.02556 -0.0077 0.7782 0.8111
0.750 0.1077 0.03694 0.02552 -0.0080 0.7728 0.8146
1.250 0.1348 0.03712 0.02566 -0.0052 0.7583 0.8234
1.500 0.1702 0.03707 0.02561 -0.0067 0.7537 0.8260
1.750 0.1771 0.03743 0.02600 -0.0041 0.7444 0.8298
2.000 0.2045 0.03742 0.02600 -0.0046 0.7381 0.8333
2.250 0.2196 0.03761 0.02620 -0.0033 0.7300 0.8376
2.500 0.2402 0.03772 0.02633 -0.0028 0.7219 0.8412
2.750 0.2818 0.03752 0.02616 -0.0050 0.7177 0.8435
3.000 0.2815 0.03809 0.02680 -0.0015 0.7052 0.8478
3.250 0.3228 0.03783 0.02657 -0.0036 0.7008 0.8510
3.500 0.3220 0.03838 0.02718 -0.0002 0.6877 0.8561
3.750 0.3590 0.03819 0.02706 -0.0017 0.6819 0.8589
4.000 0.3669 0.03862 0.02757 0.0008 0.6696 0.8629
4.250 0.3787 0.03898 0.02800 0.0026 0.6580 0.8675
4.500 0.4141 0.03864 0.02775 0.0015 0.6510 0.8714
4.750 0.4221 0.03910 0.02830 0.0038 0.6375 0.8763
5.250 0.4746 0.03870 0.02811 0.0044 0.6176 0.8847
5.500 0.4871 0.03898 0.02849 0.0059 0.6033 0.8905
5.750 0.5037 0.03914 0.02878 0.0072 0.5892 0.8959
6.000 0.5233 0.03914 0.02890 0.0081 0.5756 0.9022
6.500 0.5827 0.03785 0.02789 0.0087 0.5535 0.9143
6.750 0.6031 0.03780 0.02799 0.0094 0.5386 0.9221
7.000 0.6277 0.03762 0.02796 0.0096 0.5236 0.9299
7.250 0.6547 0.03733 0.02781 0.0096 0.5085 0.9397
7.500 0.6847 0.03690 0.02752 0.0093 0.4929 0.9521
7.750 0.7168 0.03636 0.02708 0.0088 0.4763 0.9681
8.000 0.7515 0.03574 0.02654 0.0080 0.4585 0.9855
8.250 0.7788 0.03511 0.02592 0.0083 0.4399 1.0000
8.500 0.8030 0.03493 0.02569 0.0087 0.4205 1.0000
8.750 0.8217 0.03534 0.02606 0.0092 0.3999 1.0000
9.000 0.8413 0.03580 0.02647 0.0096 0.3793 1.0000
9.250 0.8604 0.03640 0.02699 0.0101 0.3598 1.0000
9.500 0.8781 0.03716 0.02767 0.0106 0.3412 1.0000
9.750 0.8942 0.03809 0.02854 0.0111 0.3236 1.0000
10.000 0.9086 0.03918 0.02958 0.0117 0.3071 1.0000
10.250 0.9219 0.04039 0.03078 0.0122 0.2916 1.0000
10.500 0.9348 0.04168 0.03207 0.0128 0.2773 1.0000
10.750 0.9474 0.04300 0.03341 0.0134 0.2639 1.0000
11.000 0.9613 0.04425 0.03464 0.0139 0.2518 1.0000
11.250 0.9758 0.04543 0.03577 0.0144 0.2400 1.0000
11.500 0.9837 0.04721 0.03768 0.0150 0.2285 1.0000
11.750 0.9944 0.04877 0.03929 0.0155 0.2180 1.0000
12.000 1.0087 0.04997 0.04043 0.0161 0.2079 1.0000
12.250 1.0124 0.05219 0.04285 0.0166 0.1983 1.0000
12.500 1.0232 0.05376 0.04440 0.0171 0.1893 1.0000
12.750 1.0278 0.05589 0.04667 0.0176 0.1806 1.0000
13.000 1.0356 0.05783 0.04867 0.0181 0.1728 1.0000
13.250 1.0387 0.06016 0.05114 0.0185 0.1651 1.0000
13.500 1.0451 0.06225 0.05329 0.0188 0.1583 1.0000
13.750 1.0427 0.06529 0.05653 0.0190 0.1520 1.0000
14.000 1.0550 0.06672 0.05788 0.0194 0.1456 1.0000
14.250 1.0411 0.07112 0.06261 0.0191 0.1407 1.0000
14.500 1.0387 0.07427 0.06589 0.0190 0.1356 1.0000
14.750 1.0462 0.07633 0.06794 0.0191 0.1306 1.0000
15.000 1.0220 0.08246 0.07441 0.0178 0.1274 1.0000
15.250 1.0003 0.08865 0.08084 0.0160 0.1241 1.0000
15.500 1.0007 0.09177 0.08401 0.0153 0.1200 1.0000
15.750 0.9949 0.09602 0.08835 0.0141 0.1168 1.0000
16.000 0.9314 0.11067 0.10330 0.0071 0.1159 1.0000
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Polar data table (+)
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