E169 (14.4%) (e169-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 200,000 Max Cl/Cd: 55.57 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e169-il-200000-n5.txt Download as CSV file: xf-e169-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0095 0.09828 0.09296 -0.0023 1.0000 0.0189
-16.250 -1.0144 0.09360 0.08821 -0.0046 1.0000 0.0193
-16.000 -1.0196 0.08897 0.08349 -0.0068 1.0000 0.0198
-15.750 -1.0241 0.08455 0.07898 -0.0088 1.0000 0.0202
-15.500 -1.0288 0.08017 0.07450 -0.0108 1.0000 0.0208
-15.250 -1.0332 0.07595 0.07016 -0.0127 1.0000 0.0214
-15.000 -1.0369 0.07195 0.06605 -0.0144 1.0000 0.0219
-14.750 -1.0418 0.06792 0.06192 -0.0160 1.0000 0.0225
-14.500 -1.0499 0.06365 0.05758 -0.0177 1.0000 0.0230
-14.250 -1.0566 0.05959 0.05346 -0.0194 1.0000 0.0236
-14.000 -1.0617 0.05584 0.04960 -0.0208 1.0000 0.0242
-13.750 -1.0659 0.05226 0.04594 -0.0220 1.0000 0.0250
-13.500 -1.0694 0.04885 0.04243 -0.0231 1.0000 0.0258
-13.250 -1.0717 0.04565 0.03911 -0.0241 1.0000 0.0267
-13.000 -1.0720 0.04273 0.03607 -0.0248 1.0000 0.0279
-12.750 -1.0775 0.03937 0.03266 -0.0257 1.0000 0.0289
-12.500 -1.0798 0.03648 0.02970 -0.0263 1.0000 0.0300
-12.250 -1.0797 0.03402 0.02715 -0.0265 1.0000 0.0315
-12.000 -1.0781 0.03188 0.02490 -0.0263 1.0000 0.0332
-11.750 -1.0768 0.02995 0.02287 -0.0256 1.0000 0.0350
-11.500 -1.0774 0.02814 0.02101 -0.0242 1.0000 0.0369
-11.250 -1.0747 0.02677 0.01958 -0.0223 1.0000 0.0395
-11.000 -1.0691 0.02571 0.01841 -0.0201 1.0000 0.0425
-10.750 -1.0649 0.02452 0.01722 -0.0176 1.0000 0.0464
-10.500 -1.0533 0.02359 0.01622 -0.0159 1.0000 0.0515
-10.250 -1.0420 0.02255 0.01519 -0.0142 1.0000 0.0576
-10.000 -1.0278 0.02166 0.01427 -0.0127 1.0000 0.0650
-9.750 -1.0120 0.02083 0.01343 -0.0113 1.0000 0.0739
-9.500 -0.9958 0.02000 0.01261 -0.0100 1.0000 0.0846
-9.250 -0.9786 0.01921 0.01183 -0.0088 1.0000 0.0966
-9.000 -0.9605 0.01847 0.01112 -0.0076 1.0000 0.1104
-8.750 -0.9417 0.01777 0.01047 -0.0065 1.0000 0.1260
-8.500 -0.9225 0.01710 0.00987 -0.0054 1.0000 0.1439
-8.250 -0.9024 0.01651 0.00934 -0.0044 1.0000 0.1631
-8.000 -0.8814 0.01599 0.00885 -0.0035 1.0000 0.1816
-7.750 -0.8603 0.01550 0.00842 -0.0025 1.0000 0.1991
-7.500 -0.8384 0.01509 0.00803 -0.0016 1.0000 0.2146
-7.250 -0.8161 0.01472 0.00767 -0.0007 1.0000 0.2286
-7.000 -0.7936 0.01438 0.00733 0.0002 1.0000 0.2418
-6.750 -0.7709 0.01408 0.00702 0.0010 1.0000 0.2547
-6.500 -0.7484 0.01379 0.00674 0.0020 1.0000 0.2675
-6.250 -0.7259 0.01351 0.00649 0.0029 1.0000 0.2796
-6.000 -0.6981 0.01326 0.00624 0.0027 0.9950 0.2921
-5.750 -0.6603 0.01301 0.00600 0.0006 0.9745 0.3058
-5.500 -0.6215 0.01280 0.00576 -0.0017 0.9423 0.3188
-5.250 -0.5786 0.01262 0.00550 -0.0048 0.9079 0.3320
-5.000 -0.5411 0.01250 0.00526 -0.0065 0.8705 0.3436
-4.750 -0.5107 0.01239 0.00507 -0.0068 0.8360 0.3532
-4.500 -0.4832 0.01233 0.00487 -0.0065 0.8054 0.3622
-4.250 -0.4570 0.01227 0.00470 -0.0059 0.7789 0.3711
-4.000 -0.4309 0.01222 0.00454 -0.0054 0.7548 0.3794
-3.750 -0.4046 0.01217 0.00437 -0.0048 0.7330 0.3883
-3.500 -0.3784 0.01211 0.00424 -0.0044 0.7128 0.3963
-3.250 -0.3517 0.01208 0.00409 -0.0039 0.6940 0.4051
-3.000 -0.3253 0.01202 0.00398 -0.0035 0.6764 0.4130
-2.750 -0.2984 0.01199 0.00385 -0.0031 0.6599 0.4218
-2.500 -0.2718 0.01194 0.00376 -0.0028 0.6442 0.4298
-2.250 -0.2447 0.01191 0.00365 -0.0024 0.6291 0.4383
-2.000 -0.2178 0.01187 0.00357 -0.0021 0.6150 0.4466
-1.750 -0.1906 0.01184 0.00350 -0.0018 0.6014 0.4552
-1.500 -0.1635 0.01181 0.00343 -0.0015 0.5885 0.4640
-1.250 -0.1364 0.01179 0.00337 -0.0013 0.5762 0.4726
-1.000 -0.1091 0.01178 0.00332 -0.0010 0.5641 0.4820
-0.750 -0.0819 0.01175 0.00330 -0.0007 0.5524 0.4908
-0.500 -0.0545 0.01176 0.00326 -0.0005 0.5416 0.5006
0.000 0.0000 0.01174 0.00325 0.0000 0.5202 0.5202
0.500 0.0545 0.01176 0.00326 0.0005 0.5006 0.5415
0.750 0.0819 0.01175 0.00329 0.0008 0.4908 0.5524
1.000 0.1091 0.01178 0.00332 0.0010 0.4820 0.5641
1.250 0.1364 0.01179 0.00337 0.0013 0.4726 0.5763
1.500 0.1635 0.01181 0.00343 0.0016 0.4640 0.5885
1.750 0.1906 0.01184 0.00350 0.0018 0.4552 0.6014
2.000 0.2177 0.01187 0.00357 0.0021 0.4466 0.6149
2.250 0.2447 0.01191 0.00365 0.0025 0.4383 0.6291
2.500 0.2717 0.01194 0.00376 0.0028 0.4297 0.6441
2.750 0.2984 0.01199 0.00385 0.0031 0.4218 0.6599
3.000 0.3253 0.01202 0.00398 0.0035 0.4131 0.6764
3.250 0.3517 0.01208 0.00409 0.0039 0.4051 0.6939
3.500 0.3783 0.01211 0.00424 0.0044 0.3962 0.7129
3.750 0.4046 0.01217 0.00437 0.0049 0.3883 0.7330
4.000 0.4308 0.01222 0.00454 0.0054 0.3795 0.7547
4.250 0.4569 0.01227 0.00470 0.0059 0.3712 0.7789
4.500 0.4832 0.01233 0.00487 0.0065 0.3623 0.8054
4.750 0.5107 0.01239 0.00507 0.0068 0.3532 0.8357
5.000 0.5411 0.01250 0.00526 0.0065 0.3437 0.8706
5.250 0.5786 0.01262 0.00551 0.0048 0.3320 0.9079
5.500 0.6215 0.01280 0.00576 0.0017 0.3190 0.9422
5.750 0.6603 0.01301 0.00600 -0.0006 0.3057 0.9745
6.000 0.6980 0.01326 0.00624 -0.0027 0.2921 0.9949
6.250 0.7260 0.01351 0.00649 -0.0029 0.2795 1.0000
6.500 0.7485 0.01379 0.00674 -0.0020 0.2676 1.0000
6.750 0.7709 0.01408 0.00702 -0.0011 0.2547 1.0000
7.000 0.7936 0.01438 0.00733 -0.0002 0.2418 1.0000
7.250 0.8162 0.01472 0.00767 0.0007 0.2288 1.0000
7.500 0.8385 0.01509 0.00803 0.0016 0.2147 1.0000
7.750 0.8603 0.01551 0.00842 0.0025 0.1990 1.0000
8.000 0.8814 0.01599 0.00885 0.0035 0.1815 1.0000
8.250 0.9023 0.01651 0.00934 0.0044 0.1629 1.0000
8.500 0.9225 0.01710 0.00987 0.0054 0.1439 1.0000
8.750 0.9416 0.01777 0.01047 0.0065 0.1260 1.0000
9.000 0.9604 0.01847 0.01112 0.0076 0.1103 1.0000
9.250 0.9785 0.01921 0.01183 0.0088 0.0965 1.0000
9.500 0.9957 0.02000 0.01261 0.0100 0.0845 1.0000
10.000 1.0276 0.02166 0.01427 0.0127 0.0648 1.0000
10.250 1.0419 0.02255 0.01518 0.0142 0.0576 1.0000
10.500 1.0531 0.02359 0.01621 0.0159 0.0516 1.0000
10.750 1.0647 0.02452 0.01722 0.0176 0.0465 1.0000
11.000 1.0692 0.02569 0.01841 0.0201 0.0427 1.0000
11.250 1.0747 0.02676 0.01957 0.0223 0.0396 1.0000
11.500 1.0774 0.02812 0.02100 0.0242 0.0369 1.0000
11.750 1.0769 0.02992 0.02285 0.0256 0.0350 1.0000
12.000 1.0782 0.03186 0.02488 0.0263 0.0333 1.0000
12.250 1.0804 0.03395 0.02708 0.0265 0.0314 1.0000
12.500 1.0801 0.03645 0.02967 0.0263 0.0300 1.0000
12.750 1.0781 0.03931 0.03259 0.0257 0.0287 1.0000
13.000 1.0730 0.04263 0.03597 0.0248 0.0278 1.0000
13.250 1.0717 0.04565 0.03911 0.0241 0.0269 1.0000
13.500 1.0699 0.04880 0.04238 0.0231 0.0259 1.0000
13.750 1.0671 0.05214 0.04582 0.0220 0.0250 1.0000
14.000 1.0628 0.05572 0.04951 0.0208 0.0243 1.0000
14.250 1.0572 0.05955 0.05342 0.0193 0.0235 1.0000
14.500 1.0510 0.06351 0.05745 0.0178 0.0231 1.0000
14.750 1.0421 0.06791 0.06191 0.0159 0.0224 1.0000
15.000 1.0376 0.07186 0.06595 0.0144 0.0220 1.0000
15.250 1.0343 0.07587 0.07009 0.0126 0.0212 1.0000
15.500 1.0297 0.08011 0.07443 0.0108 0.0207 1.0000
15.750 1.0248 0.08450 0.07892 0.0088 0.0201 1.0000
16.000 1.0203 0.08893 0.08344 0.0067 0.0197 1.0000
16.250 1.0155 0.09350 0.08810 0.0046 0.0193 1.0000
16.500 1.0107 0.09816 0.09284 0.0023 0.0189 1.0000
16.750 1.0064 0.10277 0.09753 0.0001 0.0186 1.0000
17.000 1.0009 0.10768 0.10249 -0.0024 0.0181 1.0000
17.250 0.9975 0.11214 0.10699 -0.0046 0.0178 1.0000
17.500 0.9933 0.11703 0.11201 -0.0070 0.0176 1.0000
17.750 0.9863 0.12262 0.11774 -0.0100 0.0171 1.0000
18.000 0.9794 0.12825 0.12351 -0.0130 0.0168 1.0000
18.250 0.9725 0.13400 0.12938 -0.0162 0.0165 1.0000
18.500 0.9637 0.14035 0.13585 -0.0198 0.0162 1.0000
18.750 0.9544 0.14692 0.14254 -0.0236 0.0159 1.0000
19.000 0.9437 0.15398 0.14973 -0.0278 0.0156 1.0000
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Polar data table (+)
Polar graphs
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