E169 (14.4%) (e169-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 200,000 Max Cl/Cd: 56.08 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e169-il-200000.txt Download as CSV file: xf-e169-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9194 0.13617 0.13218 0.0126 1.0000 0.0279
-17.500 -0.9448 0.12601 0.12185 0.0065 1.0000 0.0275
-17.250 -0.9734 0.11564 0.11126 -0.0002 1.0000 0.0275
-17.000 -0.9944 0.10734 0.10278 -0.0052 1.0000 0.0273
-16.750 -1.0139 0.09970 0.09494 -0.0100 1.0000 0.0274
-16.500 -1.0308 0.09288 0.08792 -0.0141 1.0000 0.0275
-16.250 -1.0464 0.08660 0.08143 -0.0178 1.0000 0.0277
-16.000 -1.0610 0.08079 0.07542 -0.0211 1.0000 0.0279
-15.750 -1.0661 0.07643 0.07097 -0.0221 1.0000 0.0287
-15.500 -1.0653 0.07329 0.06783 -0.0231 1.0000 0.0296
-15.250 -1.0685 0.06958 0.06402 -0.0245 1.0000 0.0302
-15.000 -1.0713 0.06602 0.06036 -0.0259 1.0000 0.0310
-14.750 -1.0746 0.06245 0.05665 -0.0271 1.0000 0.0318
-14.500 -1.0765 0.05909 0.05315 -0.0281 1.0000 0.0327
-14.250 -1.0775 0.05592 0.04982 -0.0289 1.0000 0.0335
-14.000 -1.0773 0.05295 0.04667 -0.0296 1.0000 0.0342
-13.750 -1.0742 0.05031 0.04395 -0.0292 1.0000 0.0355
-13.500 -1.0710 0.04789 0.04155 -0.0292 1.0000 0.0369
-13.250 -1.0683 0.04545 0.03907 -0.0295 1.0000 0.0384
-13.000 -1.0664 0.04296 0.03648 -0.0298 1.0000 0.0403
-12.750 -1.0630 0.04066 0.03402 -0.0299 1.0000 0.0419
-12.500 -1.0600 0.03835 0.03169 -0.0292 1.0000 0.0438
-12.250 -1.0586 0.03604 0.02940 -0.0290 1.0000 0.0459
-12.000 -1.0556 0.03399 0.02729 -0.0287 1.0000 0.0484
-11.750 -1.0512 0.03217 0.02532 -0.0281 1.0000 0.0511
-11.500 -1.0531 0.02996 0.02313 -0.0268 1.0000 0.0539
-11.250 -1.0523 0.02826 0.02141 -0.0252 1.0000 0.0571
-11.000 -1.0477 0.02696 0.01998 -0.0232 1.0000 0.0615
-10.750 -1.0515 0.02534 0.01842 -0.0200 1.0000 0.0662
-10.500 -1.0441 0.02422 0.01722 -0.0177 1.0000 0.0737
-10.250 -1.0391 0.02280 0.01586 -0.0153 1.0000 0.0829
-10.000 -1.0301 0.02153 0.01464 -0.0133 1.0000 0.0951
-9.750 -1.0178 0.02043 0.01357 -0.0115 1.0000 0.1106
-9.500 -1.0047 0.01936 0.01261 -0.0098 1.0000 0.1284
-9.250 -0.9887 0.01850 0.01180 -0.0084 1.0000 0.1488
-9.000 -0.9708 0.01777 0.01112 -0.0072 1.0000 0.1692
-8.750 -0.9519 0.01716 0.01056 -0.0060 1.0000 0.1890
-8.500 -0.9312 0.01668 0.01006 -0.0050 1.0000 0.2085
-8.250 -0.9105 0.01624 0.00964 -0.0040 1.0000 0.2265
-8.000 -0.8894 0.01586 0.00926 -0.0030 1.0000 0.2434
-7.750 -0.8677 0.01554 0.00895 -0.0020 1.0000 0.2595
-7.500 -0.8456 0.01524 0.00864 -0.0010 1.0000 0.2741
-7.250 -0.8231 0.01498 0.00835 -0.0001 1.0000 0.2878
-7.000 -0.8005 0.01474 0.00806 0.0009 1.0000 0.3008
-6.750 -0.7778 0.01453 0.00781 0.0019 1.0000 0.3134
-6.500 -0.7552 0.01430 0.00762 0.0028 1.0000 0.3250
-6.250 -0.7326 0.01408 0.00742 0.0038 1.0000 0.3362
-6.000 -0.7100 0.01388 0.00719 0.0048 1.0000 0.3477
-5.750 -0.6878 0.01374 0.00699 0.0059 1.0000 0.3592
-5.500 -0.6658 0.01353 0.00687 0.0069 1.0000 0.3690
-5.250 -0.6453 0.01336 0.00671 0.0081 1.0000 0.3791
-5.000 -0.6249 0.01327 0.00658 0.0092 0.9991 0.3898
-4.750 -0.5760 0.01312 0.00647 0.0048 0.9854 0.4025
-4.500 -0.5288 0.01293 0.00631 0.0009 0.9689 0.4144
-4.250 -0.4849 0.01273 0.00609 -0.0022 0.9456 0.4258
-4.000 -0.4400 0.01258 0.00586 -0.0055 0.9205 0.4379
-3.750 -0.4007 0.01244 0.00570 -0.0074 0.8897 0.4482
-3.500 -0.3702 0.01237 0.00553 -0.0075 0.8569 0.4575
-3.250 -0.3439 0.01238 0.00538 -0.0067 0.8270 0.4676
-3.000 -0.3183 0.01233 0.00528 -0.0059 0.8005 0.4759
-2.750 -0.2927 0.01232 0.00514 -0.0052 0.7762 0.4855
-2.500 -0.2668 0.01231 0.00506 -0.0044 0.7545 0.4945
-2.250 -0.2408 0.01229 0.00494 -0.0038 0.7348 0.5037
-2.000 -0.2144 0.01229 0.00485 -0.0033 0.7155 0.5139
-1.750 -0.1879 0.01224 0.00479 -0.0028 0.6977 0.5227
-1.500 -0.1613 0.01223 0.00470 -0.0023 0.6810 0.5329
-1.250 -0.1346 0.01222 0.00465 -0.0019 0.6654 0.5430
-1.000 -0.1078 0.01219 0.00460 -0.0015 0.6506 0.5529
-0.750 -0.0809 0.01220 0.00454 -0.0011 0.6367 0.5639
-0.500 -0.0540 0.01220 0.00452 -0.0007 0.6236 0.5750
-0.250 -0.0270 0.01218 0.00450 -0.0003 0.6107 0.5858
0.000 0.0000 0.01217 0.00450 0.0000 0.5978 0.5978
0.250 0.0270 0.01218 0.00450 0.0003 0.5858 0.6107
0.500 0.0540 0.01220 0.00452 0.0007 0.5750 0.6236
0.750 0.0808 0.01220 0.00454 0.0011 0.5639 0.6366
1.000 0.1077 0.01219 0.00460 0.0015 0.5529 0.6506
1.250 0.1345 0.01222 0.00465 0.0019 0.5430 0.6654
1.500 0.1613 0.01223 0.00470 0.0023 0.5329 0.6810
1.750 0.1879 0.01224 0.00479 0.0028 0.5227 0.6977
2.000 0.2144 0.01229 0.00485 0.0033 0.5139 0.7155
2.250 0.2408 0.01229 0.00494 0.0038 0.5037 0.7348
2.500 0.2668 0.01231 0.00506 0.0044 0.4945 0.7545
2.750 0.2926 0.01232 0.00514 0.0052 0.4855 0.7762
3.000 0.3183 0.01234 0.00528 0.0059 0.4759 0.8005
3.250 0.3439 0.01238 0.00538 0.0067 0.4676 0.8270
3.500 0.3702 0.01236 0.00553 0.0075 0.4575 0.8570
3.750 0.4007 0.01244 0.00570 0.0074 0.4482 0.8897
4.000 0.4400 0.01258 0.00586 0.0055 0.4379 0.9204
4.250 0.4849 0.01273 0.00609 0.0022 0.4259 0.9455
4.500 0.5288 0.01293 0.00631 -0.0009 0.4144 0.9688
4.750 0.5759 0.01312 0.00647 -0.0048 0.4026 0.9853
5.000 0.6249 0.01327 0.00658 -0.0092 0.3897 0.9991
5.250 0.6454 0.01336 0.00671 -0.0082 0.3791 1.0000
5.500 0.6660 0.01353 0.00687 -0.0069 0.3690 1.0000
5.750 0.6879 0.01374 0.00699 -0.0059 0.3592 1.0000
6.000 0.7101 0.01388 0.00719 -0.0048 0.3476 1.0000
6.250 0.7327 0.01408 0.00742 -0.0038 0.3362 1.0000
6.500 0.7553 0.01430 0.00762 -0.0029 0.3250 1.0000
6.750 0.7779 0.01453 0.00781 -0.0019 0.3134 1.0000
7.000 0.8006 0.01473 0.00806 -0.0009 0.3008 1.0000
7.250 0.8232 0.01498 0.00836 0.0000 0.2879 1.0000
7.500 0.8456 0.01524 0.00864 0.0010 0.2742 1.0000
7.750 0.8677 0.01554 0.00895 0.0020 0.2595 1.0000
8.000 0.8894 0.01586 0.00926 0.0030 0.2434 1.0000
8.250 0.9105 0.01624 0.00963 0.0040 0.2264 1.0000
8.500 0.9312 0.01668 0.01006 0.0050 0.2086 1.0000
8.750 0.9518 0.01716 0.01055 0.0060 0.1890 1.0000
9.000 0.9707 0.01777 0.01112 0.0072 0.1691 1.0000
9.250 0.9886 0.01850 0.01180 0.0084 0.1488 1.0000
9.500 1.0046 0.01936 0.01261 0.0099 0.1284 1.0000
9.750 1.0177 0.02043 0.01356 0.0115 0.1106 1.0000
10.000 1.0300 0.02153 0.01463 0.0133 0.0950 1.0000
10.250 1.0390 0.02279 0.01586 0.0154 0.0829 1.0000
10.500 1.0440 0.02421 0.01721 0.0178 0.0738 1.0000
10.750 1.0513 0.02534 0.01842 0.0200 0.0663 1.0000
11.000 1.0475 0.02696 0.01997 0.0233 0.0616 1.0000
11.250 1.0524 0.02824 0.02138 0.0252 0.0572 1.0000
11.500 1.0531 0.02995 0.02312 0.0268 0.0539 1.0000
11.750 1.0512 0.03215 0.02530 0.0281 0.0512 1.0000
12.000 1.0559 0.03397 0.02726 0.0287 0.0484 1.0000
12.250 1.0590 0.03600 0.02936 0.0290 0.0458 1.0000
12.500 1.0603 0.03831 0.03166 0.0292 0.0438 1.0000
12.750 1.0631 0.04064 0.03400 0.0298 0.0418 1.0000
13.000 1.0667 0.04293 0.03645 0.0298 0.0403 1.0000
13.250 1.0698 0.04532 0.03894 0.0297 0.0387 1.0000
13.500 1.0721 0.04779 0.04146 0.0293 0.0371 1.0000
13.750 1.0747 0.05025 0.04390 0.0291 0.0355 1.0000
14.000 1.0781 0.05288 0.04660 0.0296 0.0342 1.0000
14.250 1.0777 0.05591 0.04981 0.0288 0.0334 1.0000
14.500 1.0771 0.05903 0.05309 0.0281 0.0326 1.0000
14.750 1.0745 0.06248 0.05668 0.0270 0.0316 1.0000
15.000 1.0721 0.06594 0.06027 0.0258 0.0309 1.0000
15.250 1.0693 0.06946 0.06388 0.0244 0.0300 1.0000
15.500 1.0683 0.07278 0.06724 0.0232 0.0292 1.0000
15.750 1.0677 0.07625 0.07077 0.0222 0.0285 1.0000
16.000 1.0624 0.08061 0.07524 0.0210 0.0280 1.0000
16.250 1.0473 0.08654 0.08137 0.0179 0.0277 1.0000
16.500 1.0313 0.09285 0.08789 0.0140 0.0275 1.0000
16.750 1.0162 0.09935 0.09458 0.0104 0.0275 1.0000
17.000 0.9943 0.10745 0.10289 0.0052 0.0273 1.0000
17.250 0.9735 0.11573 0.11136 0.0000 0.0274 1.0000
17.500 0.9497 0.12499 0.12080 -0.0056 0.0276 1.0000
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Polar data table (+)
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