E169 (14.4%) (e169-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 100,000 Max Cl/Cd: 41.68 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e169-il-100000-n5.txt Download as CSV file: xf-e169-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8165 0.15062 0.14531 0.0234 1.0000 0.0330
-16.750 -0.8742 0.13087 0.12533 0.0123 1.0000 0.0324
-16.500 -0.8996 0.12057 0.11483 0.0063 1.0000 0.0324
-16.250 -0.9171 0.11251 0.10658 0.0018 1.0000 0.0328
-16.000 -0.9323 0.10523 0.09910 -0.0023 1.0000 0.0335
-15.750 -0.9442 0.09887 0.09253 -0.0057 1.0000 0.0341
-15.500 -0.9505 0.09387 0.08741 -0.0080 1.0000 0.0350
-15.250 -0.9513 0.09016 0.08369 -0.0095 1.0000 0.0360
-15.000 -0.9539 0.08612 0.07959 -0.0112 1.0000 0.0369
-14.750 -0.9574 0.08197 0.07534 -0.0130 1.0000 0.0381
-14.500 -0.9609 0.07791 0.07117 -0.0147 1.0000 0.0393
-14.250 -0.9641 0.07403 0.06716 -0.0161 1.0000 0.0407
-14.000 -0.9672 0.07022 0.06317 -0.0175 1.0000 0.0422
-13.750 -0.9698 0.06679 0.05973 -0.0185 1.0000 0.0438
-13.500 -0.9739 0.06312 0.05603 -0.0199 1.0000 0.0454
-13.250 -0.9768 0.05967 0.05250 -0.0210 1.0000 0.0472
-13.000 -0.9793 0.05631 0.04903 -0.0220 1.0000 0.0495
-12.750 -0.9802 0.05321 0.04580 -0.0227 1.0000 0.0518
-12.500 -0.9860 0.04969 0.04228 -0.0237 1.0000 0.0538
-12.250 -0.9901 0.04639 0.03893 -0.0246 1.0000 0.0564
-12.000 -0.9924 0.04341 0.03584 -0.0252 1.0000 0.0599
-11.750 -0.9956 0.04050 0.03283 -0.0256 1.0000 0.0633
-11.500 -1.0002 0.03768 0.02998 -0.0257 1.0000 0.0667
-11.250 -1.0016 0.03537 0.02756 -0.0252 1.0000 0.0713
-11.000 -1.0045 0.03324 0.02540 -0.0242 1.0000 0.0759
-10.750 -1.0060 0.03148 0.02360 -0.0223 1.0000 0.0820
-10.500 -1.0060 0.02998 0.02208 -0.0199 1.0000 0.0890
-10.250 -1.0003 0.02866 0.02070 -0.0180 1.0000 0.0985
-10.000 -0.9932 0.02733 0.01939 -0.0162 1.0000 0.1100
-9.750 -0.9832 0.02614 0.01822 -0.0146 1.0000 0.1236
-9.500 -0.9710 0.02507 0.01714 -0.0131 1.0000 0.1393
-9.250 -0.9574 0.02409 0.01621 -0.0117 1.0000 0.1562
-9.000 -0.9418 0.02325 0.01538 -0.0104 1.0000 0.1742
-8.750 -0.9245 0.02252 0.01463 -0.0092 1.0000 0.1920
-8.500 -0.9059 0.02188 0.01395 -0.0081 1.0000 0.2093
-8.250 -0.8865 0.02131 0.01333 -0.0070 1.0000 0.2251
-8.000 -0.8665 0.02079 0.01278 -0.0060 1.0000 0.2402
-7.750 -0.8458 0.02033 0.01228 -0.0050 1.0000 0.2549
-7.500 -0.8245 0.01991 0.01180 -0.0040 1.0000 0.2691
-7.250 -0.8030 0.01953 0.01141 -0.0030 1.0000 0.2823
-7.000 -0.7812 0.01918 0.01103 -0.0021 1.0000 0.2950
-6.750 -0.7591 0.01885 0.01068 -0.0011 1.0000 0.3071
-6.500 -0.7368 0.01854 0.01033 -0.0002 1.0000 0.3190
-6.250 -0.7146 0.01824 0.00997 0.0008 1.0000 0.3310
-6.000 -0.6924 0.01797 0.00965 0.0017 1.0000 0.3423
-5.750 -0.6703 0.01770 0.00940 0.0027 1.0000 0.3524
-5.500 -0.6484 0.01743 0.00910 0.0037 1.0000 0.3627
-5.250 -0.6268 0.01719 0.00882 0.0048 1.0000 0.3729
-5.000 -0.6020 0.01696 0.00861 0.0051 0.9962 0.3820
-4.750 -0.5611 0.01673 0.00833 0.0023 0.9726 0.3938
-4.500 -0.5211 0.01652 0.00802 -0.0002 0.9445 0.4056
-4.250 -0.4800 0.01634 0.00783 -0.0028 0.9164 0.4159
-4.000 -0.4402 0.01616 0.00758 -0.0050 0.8876 0.4265
-3.750 -0.4050 0.01603 0.00730 -0.0062 0.8581 0.4375
-3.250 -0.3464 0.01585 0.00694 -0.0061 0.8033 0.4560
-3.000 -0.3195 0.01578 0.00675 -0.0056 0.7796 0.4657
-2.750 -0.2931 0.01571 0.00662 -0.0050 0.7575 0.4745
-2.500 -0.2666 0.01566 0.00644 -0.0045 0.7374 0.4844
-2.250 -0.2402 0.01560 0.00634 -0.0039 0.7187 0.4934
-2.000 -0.2137 0.01554 0.00622 -0.0034 0.7009 0.5030
-1.750 -0.1869 0.01550 0.00610 -0.0030 0.6841 0.5133
-1.500 -0.1602 0.01546 0.00603 -0.0025 0.6685 0.5227
-1.250 -0.1335 0.01542 0.00594 -0.0021 0.6536 0.5331
-1.000 -0.1068 0.01540 0.00587 -0.0017 0.6395 0.5437
-0.750 -0.0802 0.01538 0.00583 -0.0012 0.6261 0.5539
-0.500 -0.0534 0.01536 0.00580 -0.0008 0.6125 0.5651
-0.250 -0.0266 0.01535 0.00577 -0.0005 0.5999 0.5768
0.000 0.0000 0.01534 0.00578 0.0000 0.5880 0.5880
0.250 0.0266 0.01535 0.00577 0.0005 0.5768 0.5999
0.500 0.0534 0.01536 0.00580 0.0008 0.5651 0.6126
0.750 0.0801 0.01538 0.00583 0.0012 0.5538 0.6261
1.000 0.1068 0.01540 0.00587 0.0017 0.5437 0.6395
1.250 0.1334 0.01542 0.00594 0.0021 0.5331 0.6536
1.500 0.1602 0.01546 0.00603 0.0026 0.5227 0.6685
1.750 0.1869 0.01550 0.00610 0.0030 0.5133 0.6841
2.000 0.2137 0.01554 0.00622 0.0034 0.5030 0.7009
2.250 0.2402 0.01560 0.00634 0.0039 0.4935 0.7187
2.500 0.2666 0.01566 0.00644 0.0045 0.4845 0.7374
2.750 0.2930 0.01571 0.00662 0.0050 0.4745 0.7576
3.000 0.3195 0.01578 0.00675 0.0056 0.4656 0.7796
3.250 0.3464 0.01585 0.00694 0.0061 0.4560 0.8034
3.750 0.4049 0.01603 0.00730 0.0062 0.4375 0.8580
4.000 0.4402 0.01616 0.00758 0.0050 0.4265 0.8876
4.250 0.4800 0.01634 0.00783 0.0028 0.4159 0.9165
4.500 0.5212 0.01652 0.00802 0.0002 0.4056 0.9445
4.750 0.5612 0.01673 0.00833 -0.0023 0.3938 0.9725
5.000 0.6020 0.01696 0.00861 -0.0051 0.3820 0.9962
5.250 0.6269 0.01719 0.00882 -0.0048 0.3728 1.0000
5.500 0.6485 0.01743 0.00910 -0.0037 0.3626 1.0000
5.750 0.6704 0.01770 0.00940 -0.0028 0.3524 1.0000
6.000 0.6924 0.01797 0.00965 -0.0017 0.3423 1.0000
6.250 0.7146 0.01824 0.00998 -0.0008 0.3310 1.0000
6.500 0.7369 0.01854 0.01033 0.0002 0.3190 1.0000
6.750 0.7591 0.01885 0.01068 0.0011 0.3072 1.0000
7.000 0.7812 0.01918 0.01103 0.0020 0.2950 1.0000
7.250 0.8030 0.01953 0.01141 0.0030 0.2823 1.0000
7.500 0.8245 0.01990 0.01180 0.0040 0.2691 1.0000
7.750 0.8457 0.02033 0.01228 0.0050 0.2548 1.0000
8.000 0.8665 0.02079 0.01278 0.0060 0.2402 1.0000
8.250 0.8865 0.02131 0.01333 0.0070 0.2251 1.0000
8.500 0.9058 0.02188 0.01394 0.0081 0.2093 1.0000
8.750 0.9244 0.02252 0.01463 0.0092 0.1921 1.0000
9.000 0.9417 0.02325 0.01538 0.0104 0.1741 1.0000
9.250 0.9574 0.02409 0.01620 0.0117 0.1563 1.0000
9.500 0.9709 0.02507 0.01714 0.0131 0.1393 1.0000
9.750 0.9831 0.02614 0.01821 0.0146 0.1236 1.0000
10.000 0.9931 0.02733 0.01939 0.0162 0.1100 1.0000
10.250 1.0003 0.02865 0.02069 0.0180 0.0986 1.0000
10.500 1.0060 0.02997 0.02207 0.0200 0.0890 1.0000
10.750 1.0060 0.03147 0.02359 0.0223 0.0820 1.0000
11.000 1.0046 0.03322 0.02538 0.0242 0.0760 1.0000
11.250 1.0018 0.03535 0.02754 0.0253 0.0713 1.0000
11.500 1.0004 0.03766 0.02996 0.0257 0.0667 1.0000
11.750 0.9958 0.04048 0.03281 0.0256 0.0633 1.0000
12.000 0.9927 0.04338 0.03580 0.0252 0.0599 1.0000
12.250 0.9907 0.04634 0.03887 0.0246 0.0565 1.0000
12.500 0.9864 0.04965 0.04224 0.0237 0.0538 1.0000
12.750 0.9810 0.05314 0.04573 0.0227 0.0518 1.0000
13.000 0.9799 0.05625 0.04897 0.0220 0.0494 1.0000
13.250 0.9778 0.05956 0.05239 0.0211 0.0472 1.0000
13.500 0.9750 0.06300 0.05591 0.0199 0.0454 1.0000
13.750 0.9713 0.06661 0.05956 0.0186 0.0439 1.0000
14.000 0.9686 0.07005 0.06299 0.0176 0.0423 1.0000
14.250 0.9652 0.07391 0.06703 0.0162 0.0406 1.0000
14.500 0.9621 0.07777 0.07103 0.0147 0.0393 1.0000
14.750 0.9581 0.08192 0.07529 0.0130 0.0379 1.0000
15.000 0.9548 0.08604 0.07950 0.0112 0.0369 1.0000
15.250 0.9521 0.09009 0.08361 0.0094 0.0359 1.0000
15.500 0.9517 0.09368 0.08719 0.0080 0.0348 1.0000
15.750 0.9436 0.09911 0.09278 0.0054 0.0340 1.0000
16.000 0.9322 0.10535 0.09922 0.0021 0.0334 1.0000
16.250 0.9180 0.11242 0.10650 -0.0018 0.0328 1.0000
16.500 0.9006 0.12046 0.11472 -0.0063 0.0325 1.0000
16.750 0.8756 0.13066 0.12512 -0.0122 0.0324 1.0000
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Polar data table (+)
Polar graphs
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