E169 (14.4%) (e169-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 100,000 Max Cl/Cd: 39.29 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e169-il-100000.txt Download as CSV file: xf-e169-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9141 0.09832 0.09294 -0.0135 1.0000 0.0614
-14.750 -0.9480 0.08904 0.08349 -0.0193 1.0000 0.0607
-14.500 -0.9777 0.08110 0.07535 -0.0241 1.0000 0.0602
-14.250 -1.0036 0.07428 0.06831 -0.0279 1.0000 0.0599
-14.000 -1.0258 0.06847 0.06226 -0.0308 1.0000 0.0599
-13.750 -1.0460 0.06342 0.05695 -0.0329 1.0000 0.0602
-13.500 -1.0637 0.05906 0.05233 -0.0342 1.0000 0.0608
-13.250 -1.0791 0.05540 0.04837 -0.0347 1.0000 0.0615
-13.000 -1.0767 0.05185 0.04476 -0.0344 1.0000 0.0639
-12.750 -1.0694 0.04953 0.04245 -0.0339 1.0000 0.0666
-12.500 -1.0700 0.04690 0.03964 -0.0332 1.0000 0.0688
-12.250 -1.0727 0.04443 0.03693 -0.0320 1.0000 0.0714
-12.000 -1.0696 0.04188 0.03419 -0.0307 1.0000 0.0748
-11.750 -1.0574 0.04003 0.03247 -0.0298 1.0000 0.0798
-11.500 -1.0559 0.03810 0.03030 -0.0277 1.0000 0.0842
-11.250 -1.0432 0.03605 0.02835 -0.0266 1.0000 0.0905
-11.000 -1.0408 0.03443 0.02655 -0.0242 1.0000 0.0974
-10.750 -1.0313 0.03268 0.02496 -0.0226 1.0000 0.1065
-10.500 -1.0240 0.03099 0.02331 -0.0206 1.0000 0.1173
-10.250 -1.0166 0.02947 0.02183 -0.0186 1.0000 0.1303
-10.000 -1.0082 0.02811 0.02052 -0.0166 1.0000 0.1460
-9.750 -0.9987 0.02689 0.01930 -0.0146 1.0000 0.1644
-9.500 -0.9872 0.02586 0.01833 -0.0128 1.0000 0.1839
-9.250 -0.9736 0.02509 0.01762 -0.0110 1.0000 0.2045
-9.000 -0.9592 0.02441 0.01689 -0.0093 1.0000 0.2257
-8.750 -0.9413 0.02400 0.01658 -0.0079 1.0000 0.2450
-8.500 -0.9228 0.02366 0.01622 -0.0064 1.0000 0.2640
-8.250 -0.9036 0.02333 0.01581 -0.0050 1.0000 0.2819
-8.000 -0.8835 0.02303 0.01544 -0.0037 1.0000 0.2984
-7.750 -0.8623 0.02279 0.01516 -0.0025 1.0000 0.3139
-7.500 -0.8399 0.02260 0.01499 -0.0015 1.0000 0.3283
-7.250 -0.8166 0.02243 0.01485 -0.0004 1.0000 0.3419
-7.000 -0.7933 0.02224 0.01469 0.0006 1.0000 0.3548
-6.750 -0.7703 0.02201 0.01445 0.0016 1.0000 0.3673
-6.500 -0.7480 0.02171 0.01412 0.0027 1.0000 0.3798
-6.250 -0.7264 0.02136 0.01370 0.0039 1.0000 0.3925
-6.000 -0.7046 0.02107 0.01336 0.0050 1.0000 0.4048
-5.750 -0.6809 0.02086 0.01325 0.0060 1.0000 0.4151
-5.500 -0.6594 0.02052 0.01289 0.0072 1.0000 0.4263
-5.250 -0.6393 0.02012 0.01240 0.0084 1.0000 0.4381
-5.000 -0.6180 0.01989 0.01225 0.0096 1.0000 0.4480
-4.750 -0.5992 0.01957 0.01196 0.0110 1.0000 0.4578
-4.500 -0.5850 0.01925 0.01158 0.0128 1.0000 0.4688
-4.250 -0.5724 0.01914 0.01158 0.0149 1.0000 0.4768
-4.000 -0.5455 0.01901 0.01142 0.0139 0.9938 0.4879
-3.750 -0.4896 0.01886 0.01125 0.0081 0.9752 0.5025
-3.500 -0.4349 0.01864 0.01099 0.0027 0.9573 0.5170
-3.250 -0.3808 0.01837 0.01070 -0.0023 0.9401 0.5313
-3.000 -0.3339 0.01814 0.01048 -0.0056 0.9189 0.5438
-2.750 -0.2914 0.01793 0.01027 -0.0078 0.8966 0.5554
-2.500 -0.2569 0.01775 0.01004 -0.0086 0.8725 0.5671
-2.250 -0.2277 0.01762 0.00980 -0.0083 0.8485 0.5792
-2.000 -0.2008 0.01757 0.00971 -0.0075 0.8256 0.5899
-1.750 -0.1752 0.01751 0.00962 -0.0066 0.8041 0.6005
-1.500 -0.1502 0.01745 0.00946 -0.0056 0.7848 0.6122
-1.250 -0.1254 0.01742 0.00934 -0.0046 0.7666 0.6247
-1.000 -0.1003 0.01740 0.00933 -0.0036 0.7486 0.6354
-0.750 -0.0753 0.01738 0.00928 -0.0026 0.7319 0.6475
-0.500 -0.0503 0.01736 0.00922 -0.0018 0.7164 0.6604
-0.250 -0.0252 0.01735 0.00917 -0.0009 0.7017 0.6741
0.000 0.0000 0.01735 0.00913 0.0000 0.6881 0.6882
0.250 0.0252 0.01735 0.00917 0.0009 0.6741 0.7017
0.500 0.0503 0.01736 0.00922 0.0018 0.6604 0.7165
0.750 0.0753 0.01738 0.00928 0.0026 0.6475 0.7319
1.000 0.1003 0.01740 0.00933 0.0036 0.6354 0.7486
1.250 0.1254 0.01742 0.00934 0.0046 0.6247 0.7666
1.500 0.1502 0.01745 0.00946 0.0056 0.6123 0.7847
1.750 0.1752 0.01751 0.00961 0.0066 0.6005 0.8041
2.000 0.2008 0.01757 0.00971 0.0075 0.5899 0.8256
2.250 0.2277 0.01762 0.00979 0.0084 0.5792 0.8485
2.500 0.2569 0.01775 0.01004 0.0086 0.5671 0.8725
2.750 0.2914 0.01793 0.01027 0.0078 0.5554 0.8966
3.000 0.3339 0.01814 0.01049 0.0056 0.5438 0.9189
3.250 0.3808 0.01837 0.01070 0.0023 0.5313 0.9401
3.500 0.4348 0.01864 0.01099 -0.0027 0.5170 0.9572
3.750 0.4897 0.01886 0.01125 -0.0081 0.5025 0.9752
4.000 0.5456 0.01901 0.01142 -0.0139 0.4879 0.9938
4.250 0.5725 0.01914 0.01158 -0.0149 0.4768 1.0000
4.500 0.5851 0.01924 0.01157 -0.0128 0.4688 1.0000
4.750 0.5993 0.01957 0.01196 -0.0110 0.4578 1.0000
5.000 0.6181 0.01988 0.01225 -0.0096 0.4480 1.0000
5.250 0.6395 0.02012 0.01240 -0.0084 0.4381 1.0000
5.500 0.6595 0.02051 0.01289 -0.0072 0.4262 1.0000
5.750 0.6810 0.02086 0.01325 -0.0060 0.4151 1.0000
6.000 0.7046 0.02107 0.01336 -0.0050 0.4048 1.0000
6.250 0.7265 0.02136 0.01371 -0.0039 0.3925 1.0000
6.500 0.7481 0.02171 0.01412 -0.0027 0.3798 1.0000
6.750 0.7704 0.02201 0.01446 -0.0016 0.3673 1.0000
7.000 0.7933 0.02224 0.01468 -0.0006 0.3548 1.0000
7.250 0.8167 0.02243 0.01485 0.0004 0.3419 1.0000
7.500 0.8399 0.02260 0.01498 0.0014 0.3284 1.0000
7.750 0.8623 0.02279 0.01516 0.0025 0.3139 1.0000
8.000 0.8836 0.02303 0.01544 0.0037 0.2985 1.0000
8.250 0.9036 0.02333 0.01583 0.0051 0.2819 1.0000
8.500 0.9227 0.02365 0.01622 0.0064 0.2640 1.0000
8.750 0.9413 0.02400 0.01658 0.0079 0.2450 1.0000
9.000 0.9591 0.02441 0.01688 0.0093 0.2257 1.0000
9.250 0.9736 0.02509 0.01762 0.0111 0.2045 1.0000
9.500 0.9871 0.02585 0.01833 0.0128 0.1839 1.0000
9.750 0.9986 0.02689 0.01930 0.0147 0.1644 1.0000
10.000 1.0081 0.02810 0.02052 0.0166 0.1459 1.0000
10.250 1.0166 0.02947 0.02183 0.0186 0.1304 1.0000
10.500 1.0240 0.03098 0.02331 0.0206 0.1173 1.0000
10.750 1.0313 0.03267 0.02495 0.0226 0.1066 1.0000
11.000 1.0411 0.03443 0.02654 0.0242 0.0975 1.0000
11.250 1.0432 0.03604 0.02834 0.0266 0.0906 1.0000
11.500 1.0557 0.03809 0.03029 0.0278 0.0842 1.0000
11.750 1.0575 0.04002 0.03246 0.0298 0.0798 1.0000
12.000 1.0695 0.04186 0.03418 0.0308 0.0749 1.0000
12.250 1.0729 0.04441 0.03690 0.0320 0.0714 1.0000
12.500 1.0703 0.04689 0.03963 0.0332 0.0688 1.0000
12.750 1.0696 0.04950 0.04241 0.0339 0.0665 1.0000
13.000 1.0776 0.05179 0.04469 0.0344 0.0637 1.0000
13.250 1.0808 0.05536 0.04832 0.0347 0.0616 1.0000
13.500 1.0640 0.05900 0.05226 0.0342 0.0608 1.0000
13.750 1.0465 0.06336 0.05689 0.0329 0.0602 1.0000
14.000 1.0264 0.06840 0.06219 0.0308 0.0598 1.0000
14.250 1.0033 0.07434 0.06837 0.0278 0.0598 1.0000
14.500 0.9778 0.08109 0.07534 0.0240 0.0601 1.0000
14.750 0.9455 0.08933 0.08379 0.0188 0.0605 1.0000
15.000 0.9137 0.09842 0.09304 0.0133 0.0613 1.0000
15.250 0.7041 0.15890 0.15362 -0.0230 0.0868 1.0000
15.500 0.7178 0.16192 0.15666 -0.0224 0.0855 1.0000
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Polar data table (+)
Polar graphs
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