(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.69 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e171-il-1000000.txt Download as CSV file: xf-e171-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9287 0.10860 0.10648 -0.0025 1.0000 0.0048
-16.250 -0.9445 0.10045 0.09822 -0.0071 1.0000 0.0047
-16.000 -0.9627 0.09208 0.08975 -0.0120 1.0000 0.0048
-15.750 -0.9913 0.08207 0.07952 -0.0178 1.0000 0.0046
-15.500 -1.0087 0.07483 0.07212 -0.0219 1.0000 0.0046
-15.250 -1.0204 0.06901 0.06618 -0.0251 1.0000 0.0046
-15.000 -1.0334 0.06339 0.06043 -0.0280 1.0000 0.0046
-14.750 -1.0481 0.05798 0.05489 -0.0306 1.0000 0.0047
-14.500 -1.0615 0.05301 0.04975 -0.0324 1.0000 0.0046
-14.250 -1.0728 0.04863 0.04522 -0.0339 1.0000 0.0047
-14.000 -1.0781 0.04517 0.04165 -0.0348 1.0000 0.0048
-13.750 -1.0888 0.04124 0.03755 -0.0353 1.0000 0.0048
-13.500 -1.0917 0.03835 0.03452 -0.0355 1.0000 0.0048
-13.250 -1.0937 0.03572 0.03177 -0.0353 1.0000 0.0049
-13.000 -1.0953 0.03324 0.02915 -0.0348 1.0000 0.0049
-12.750 -1.0947 0.03110 0.02690 -0.0339 1.0000 0.0049
-12.500 -1.0923 0.02928 0.02497 -0.0329 1.0000 0.0050
-12.250 -1.0889 0.02764 0.02324 -0.0315 1.0000 0.0051
-12.000 -1.0869 0.02598 0.02144 -0.0297 1.0000 0.0051
-11.750 -1.0806 0.02480 0.02018 -0.0278 1.0000 0.0053
-11.500 -1.0736 0.02374 0.01903 -0.0257 1.0000 0.0053
-11.250 -1.0671 0.02271 0.01792 -0.0232 1.0000 0.0055
-11.000 -1.0611 0.02173 0.01685 -0.0203 1.0000 0.0055
-10.750 -1.0501 0.02102 0.01607 -0.0180 1.0000 0.0058
-10.500 -1.0376 0.02013 0.01509 -0.0160 1.0000 0.0059
-10.250 -1.0224 0.01941 0.01429 -0.0143 1.0000 0.0062
-10.000 -1.0052 0.01880 0.01362 -0.0129 1.0000 0.0064
-9.750 -0.9886 0.01811 0.01286 -0.0113 1.0000 0.0066
-9.500 -0.9739 0.01724 0.01190 -0.0094 1.0000 0.0067
-9.250 -0.9649 0.01589 0.01044 -0.0067 1.0000 0.0074
-9.000 -0.9472 0.01528 0.00978 -0.0051 1.0000 0.0078
-8.750 -0.9277 0.01481 0.00929 -0.0038 1.0000 0.0083
-8.500 -0.9087 0.01431 0.00873 -0.0024 1.0000 0.0088
-8.250 -0.8887 0.01388 0.00826 -0.0011 1.0000 0.0093
-8.000 -0.8680 0.01352 0.00787 0.0001 1.0000 0.0098
-7.750 -0.8530 0.01268 0.00696 0.0023 1.0000 0.0114
-7.500 -0.8329 0.01230 0.00657 0.0036 1.0000 0.0125
-7.250 -0.8120 0.01200 0.00625 0.0048 1.0000 0.0137
-7.000 -0.7785 0.01137 0.00560 0.0032 0.9967 0.0170
-6.750 -0.7426 0.01103 0.00523 0.0011 0.9918 0.0193
-6.500 -0.7079 0.01050 0.00471 -0.0007 0.9843 0.0250
-6.250 -0.6737 0.01003 0.00429 -0.0024 0.9718 0.0360
-6.000 -0.6367 0.00945 0.00384 -0.0048 0.9503 0.0627
-5.750 -0.6050 0.00898 0.00345 -0.0059 0.9143 0.0938
-5.500 -0.5823 0.00867 0.00315 -0.0049 0.8794 0.1245
-5.250 -0.5601 0.00832 0.00287 -0.0040 0.8526 0.1623
-5.000 -0.5372 0.00796 0.00261 -0.0032 0.8307 0.2040
-4.750 -0.5137 0.00762 0.00235 -0.0025 0.8121 0.2482
-4.500 -0.4900 0.00726 0.00212 -0.0019 0.7958 0.2959
-4.250 -0.4671 0.00680 0.00188 -0.0012 0.7809 0.3651
-3.750 -0.4170 0.00629 0.00160 -0.0003 0.7549 0.4610
-3.500 -0.3903 0.00618 0.00152 -0.0001 0.7434 0.4866
-3.250 -0.3630 0.00612 0.00145 0.0000 0.7329 0.5040
-3.000 -0.3357 0.00608 0.00139 0.0001 0.7229 0.5222
-2.750 -0.3080 0.00605 0.00133 0.0002 0.7132 0.5357
-2.500 -0.2804 0.00601 0.00129 0.0002 0.7046 0.5471
-2.250 -0.2527 0.00600 0.00124 0.0003 0.6961 0.5571
-2.000 -0.2245 0.00598 0.00120 0.0002 0.6881 0.5668
-1.500 -0.1686 0.00595 0.00114 0.0002 0.6731 0.5839
-1.000 -0.1124 0.00593 0.00110 0.0001 0.6590 0.6003
-0.500 -0.0562 0.00593 0.00108 0.0001 0.6451 0.6153
0.000 0.0000 0.00592 0.00107 0.0000 0.6300 0.6300
0.500 0.0562 0.00593 0.00108 -0.0001 0.6152 0.6451
1.000 0.1124 0.00593 0.00110 -0.0001 0.6003 0.6590
1.500 0.1686 0.00595 0.00114 -0.0002 0.5840 0.6731
2.000 0.2245 0.00598 0.00120 -0.0002 0.5667 0.6881
2.250 0.2526 0.00600 0.00124 -0.0003 0.5571 0.6961
2.500 0.2804 0.00601 0.00129 -0.0002 0.5471 0.7046
2.750 0.3080 0.00605 0.00133 -0.0002 0.5359 0.7133
3.000 0.3357 0.00608 0.00139 -0.0001 0.5221 0.7230
3.250 0.3630 0.00612 0.00145 0.0000 0.5040 0.7329
3.500 0.3903 0.00618 0.00152 0.0001 0.4860 0.7433
3.750 0.4170 0.00629 0.00160 0.0003 0.4603 0.7549
4.000 0.4427 0.00649 0.00172 0.0006 0.4215 0.7674
4.250 0.4671 0.00680 0.00188 0.0012 0.3657 0.7808
4.500 0.4900 0.00726 0.00212 0.0019 0.2962 0.7957
4.750 0.5137 0.00762 0.00235 0.0025 0.2486 0.8122
5.000 0.5371 0.00796 0.00261 0.0032 0.2037 0.8307
5.250 0.5601 0.00832 0.00287 0.0040 0.1620 0.8525
5.500 0.5823 0.00867 0.00315 0.0049 0.1248 0.8794
5.750 0.6051 0.00897 0.00344 0.0059 0.0948 0.9142
6.000 0.6367 0.00945 0.00384 0.0048 0.0627 0.9503
6.500 0.7080 0.01050 0.00471 0.0007 0.0250 0.9844
6.750 0.7427 0.01102 0.00522 -0.0011 0.0193 0.9918
7.000 0.7786 0.01138 0.00561 -0.0032 0.0169 0.9967
7.250 0.8120 0.01200 0.00625 -0.0048 0.0137 1.0000
7.500 0.8327 0.01231 0.00658 -0.0036 0.0126 1.0000
7.750 0.8530 0.01268 0.00696 -0.0023 0.0113 1.0000
8.000 0.8679 0.01353 0.00788 -0.0001 0.0097 1.0000
8.250 0.8887 0.01389 0.00827 0.0011 0.0094 1.0000
8.500 0.9085 0.01432 0.00874 0.0024 0.0088 1.0000
8.750 0.9277 0.01482 0.00929 0.0038 0.0083 1.0000
9.000 0.9468 0.01531 0.00982 0.0052 0.0079 1.0000
9.250 0.9651 0.01588 0.01042 0.0066 0.0074 1.0000
9.500 0.9722 0.01738 0.01206 0.0097 0.0067 1.0000
9.750 0.9876 0.01820 0.01295 0.0115 0.0066 1.0000
10.000 1.0064 0.01870 0.01352 0.0127 0.0064 1.0000
10.250 1.0226 0.01939 0.01428 0.0143 0.0062 1.0000
10.500 1.0365 0.02025 0.01521 0.0161 0.0059 1.0000
10.750 1.0520 0.02089 0.01593 0.0177 0.0057 1.0000
11.000 1.0605 0.02180 0.01692 0.0203 0.0055 1.0000
11.250 1.0678 0.02269 0.01790 0.0231 0.0054 1.0000
11.500 1.0741 0.02374 0.01904 0.0256 0.0053 1.0000
11.750 1.0812 0.02478 0.02016 0.0277 0.0052 1.0000
12.000 1.0848 0.02621 0.02170 0.0298 0.0051 1.0000
12.250 1.0907 0.02753 0.02311 0.0313 0.0051 1.0000
12.500 1.0938 0.02919 0.02487 0.0327 0.0050 1.0000
12.750 1.0988 0.03076 0.02653 0.0336 0.0049 1.0000
13.000 1.0958 0.03327 0.02918 0.0346 0.0048 1.0000
13.250 1.0978 0.03536 0.03136 0.0350 0.0048 1.0000
13.500 1.0913 0.03851 0.03468 0.0353 0.0048 1.0000
13.750 1.0890 0.04130 0.03759 0.0351 0.0046 1.0000
14.000 1.0821 0.04480 0.04124 0.0346 0.0046 1.0000
14.250 1.0738 0.04866 0.04526 0.0337 0.0047 1.0000
14.500 1.0641 0.05284 0.04957 0.0323 0.0046 1.0000
14.750 1.0450 0.05857 0.05548 0.0300 0.0045 1.0000
15.000 1.0352 0.06335 0.06039 0.0278 0.0046 1.0000
15.250 1.0223 0.06897 0.06615 0.0249 0.0046 1.0000
15.500 1.0023 0.07622 0.07356 0.0209 0.0046 1.0000
15.750 0.9895 0.08274 0.08021 0.0171 0.0047 1.0000
16.000 0.9697 0.09091 0.08851 0.0123 0.0046 1.0000
16.250 0.9174 0.10700 0.10492 0.0032 0.0049 1.0000
16.500 0.9134 0.11260 0.11055 0.0000 0.0048 1.0000
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Polar data table (+)
Polar graphs
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