EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 100,000 Max Cl/Cd: 41.48 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1233-il-100000-n5.txt Download as CSV file: xf-e1233-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1233 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4378 0.08170 0.07658 -0.0662 1.0000 0.0284
-11.500 -0.4828 0.07254 0.06731 -0.0709 1.0000 0.0281
-11.250 -0.5157 0.06719 0.06187 -0.0720 1.0000 0.0279
-11.000 -0.5511 0.06282 0.05740 -0.0714 1.0000 0.0277
-10.750 -0.5723 0.05747 0.05177 -0.0746 0.9946 0.0277
-10.500 -0.5811 0.05238 0.04628 -0.0787 0.9846 0.0278
-10.250 -0.5869 0.04838 0.04186 -0.0805 0.9726 0.0281
-10.000 -0.5845 0.04485 0.03790 -0.0811 0.9601 0.0285
-9.750 -0.5730 0.04203 0.03476 -0.0814 0.9480 0.0289
-9.500 -0.5550 0.04018 0.03282 -0.0817 0.9362 0.0296
-9.250 -0.5361 0.03830 0.03078 -0.0819 0.9245 0.0302
-9.000 -0.5147 0.03638 0.02865 -0.0822 0.9138 0.0312
-8.750 -0.4886 0.03432 0.02626 -0.0831 0.9053 0.0328
-8.500 -0.4668 0.03311 0.02503 -0.0830 0.8931 0.0344
-8.250 -0.4390 0.03168 0.02346 -0.0838 0.8837 0.0364
-8.000 -0.4107 0.03020 0.02184 -0.0844 0.8734 0.0384
-7.750 -0.3828 0.02899 0.02057 -0.0850 0.8619 0.0403
-7.500 -0.3467 0.02764 0.01908 -0.0869 0.8533 0.0436
-7.250 -0.3174 0.02665 0.01800 -0.0877 0.8402 0.0477
-7.000 -0.2822 0.02556 0.01687 -0.0896 0.8288 0.0527
-6.750 -0.2439 0.02451 0.01575 -0.0920 0.8171 0.0594
-6.500 -0.2126 0.02368 0.01486 -0.0931 0.8026 0.0678
-6.250 -0.1800 0.02292 0.01400 -0.0943 0.7883 0.0787
-6.000 -0.1475 0.02222 0.01328 -0.0956 0.7741 0.0913
-5.750 -0.1167 0.02162 0.01264 -0.0966 0.7598 0.1058
-5.500 -0.0910 0.02113 0.01212 -0.0965 0.7446 0.1212
-5.250 -0.0650 0.02065 0.01161 -0.0965 0.7303 0.1382
-5.000 -0.0379 0.02019 0.01111 -0.0966 0.7170 0.1580
-4.750 -0.0138 0.01970 0.01066 -0.0962 0.7037 0.1811
-4.500 0.0079 0.01924 0.01027 -0.0954 0.6905 0.2119
-4.250 0.0302 0.01868 0.00986 -0.0948 0.6787 0.2581
-4.000 0.0499 0.01805 0.00949 -0.0939 0.6668 0.3286
-3.750 0.0677 0.01747 0.00938 -0.0923 0.6555 0.4314
-3.500 0.0896 0.01747 0.00971 -0.0904 0.6451 0.5306
-3.250 0.1117 0.01772 0.00999 -0.0886 0.6338 0.5834
-3.000 0.1377 0.01801 0.01015 -0.0876 0.6242 0.6172
-2.750 0.1609 0.01824 0.01026 -0.0863 0.6134 0.6425
-2.500 0.1864 0.01854 0.01039 -0.0854 0.6042 0.6623
-2.250 0.2096 0.01880 0.01053 -0.0841 0.5942 0.6798
-2.000 0.2343 0.01914 0.01070 -0.0828 0.5859 0.6946
-1.750 0.2554 0.01950 0.01100 -0.0808 0.5765 0.7081
-1.500 0.2788 0.01987 0.01122 -0.0792 0.5688 0.7235
-1.250 0.2990 0.02014 0.01143 -0.0772 0.5599 0.7385
-1.000 0.3208 0.02042 0.01160 -0.0753 0.5524 0.7488
-0.750 0.3440 0.02052 0.01159 -0.0744 0.5449 0.7580
-0.500 0.3659 0.02064 0.01163 -0.0729 0.5371 0.7643
-0.250 0.3922 0.02069 0.01148 -0.0728 0.5307 0.7719
0.000 0.4137 0.02074 0.01150 -0.0717 0.5228 0.7772
0.250 0.4371 0.02081 0.01147 -0.0708 0.5162 0.7819
0.500 0.4626 0.02087 0.01140 -0.0705 0.5102 0.7875
0.750 0.4869 0.02092 0.01138 -0.0703 0.5032 0.7931
1.000 0.5101 0.02099 0.01136 -0.0693 0.4971 0.7968
1.250 0.5343 0.02108 0.01136 -0.0688 0.4915 0.8012
1.500 0.5574 0.02117 0.01141 -0.0682 0.4849 0.8061
1.750 0.5837 0.02126 0.01140 -0.0683 0.4794 0.8112
2.000 0.6084 0.02138 0.01141 -0.0677 0.4748 0.8147
2.250 0.6292 0.02150 0.01157 -0.0666 0.4688 0.8189
2.500 0.6531 0.02163 0.01165 -0.0662 0.4633 0.8236
2.750 0.6807 0.02177 0.01167 -0.0666 0.4586 0.8285
3.000 0.7017 0.02193 0.01182 -0.0654 0.4535 0.8322
3.250 0.7232 0.02209 0.01201 -0.0645 0.4484 0.8362
3.500 0.7472 0.02227 0.01214 -0.0641 0.4439 0.8408
3.750 0.7750 0.02246 0.01222 -0.0645 0.4399 0.8457
4.000 0.7945 0.02267 0.01247 -0.0632 0.4351 0.8498
4.250 0.8148 0.02288 0.01272 -0.0621 0.4302 0.8542
4.500 0.8385 0.02309 0.01290 -0.0617 0.4258 0.8588
4.750 0.8659 0.02332 0.01305 -0.0621 0.4222 0.8637
5.000 0.8853 0.02358 0.01335 -0.0608 0.4183 0.8683
5.250 0.9039 0.02387 0.01372 -0.0596 0.4139 0.8735
5.500 0.9262 0.02415 0.01400 -0.0591 0.4096 0.8787
5.750 0.9495 0.02437 0.01419 -0.0585 0.4060 0.8836
6.000 0.9739 0.02462 0.01441 -0.0582 0.4027 0.8891
6.250 0.9887 0.02502 0.01494 -0.0565 0.3986 0.8960
6.500 1.0048 0.02535 0.01534 -0.0548 0.3948 0.9021
6.750 1.0247 0.02565 0.01567 -0.0539 0.3912 0.9092
7.000 1.0481 0.02590 0.01592 -0.0535 0.3880 0.9165
7.250 1.0712 0.02621 0.01623 -0.0531 0.3848 0.9250
7.500 1.0824 0.02674 0.01693 -0.0510 0.3809 0.9367
7.750 1.1022 0.02726 0.01757 -0.0504 0.3771 0.9503
8.000 1.1300 0.02772 0.01808 -0.0514 0.3736 0.9730
8.250 1.1579 0.02809 0.01843 -0.0522 0.3706 1.0000
8.500 1.1854 0.02858 0.01889 -0.0530 0.3677 1.0000
8.750 1.1927 0.02952 0.02001 -0.0510 0.3637 1.0000
9.000 1.2062 0.03034 0.02092 -0.0499 0.3600 1.0000
9.250 1.2253 0.03103 0.02166 -0.0495 0.3569 1.0000
9.500 1.2492 0.03158 0.02221 -0.0497 0.3541 1.0000
9.750 1.2791 0.03199 0.02257 -0.0507 0.3516 1.0000
10.000 1.2795 0.03327 0.02403 -0.0480 0.3482 1.0000
10.250 1.2788 0.03466 0.02558 -0.0453 0.3444 1.0000
10.500 1.2871 0.03577 0.02678 -0.0439 0.3411 1.0000
10.750 1.3038 0.03659 0.02763 -0.0433 0.3383 1.0000
11.000 1.3294 0.03705 0.02809 -0.0436 0.3359 1.0000
11.250 1.3435 0.03803 0.02912 -0.0428 0.3332 1.0000
11.500 1.3110 0.04129 0.03266 -0.0383 0.3289 1.0000
11.750 1.2955 0.04407 0.03560 -0.0358 0.3250 1.0000
12.000 1.3032 0.04555 0.03715 -0.0351 0.3220 1.0000
12.250 1.3282 0.04592 0.03753 -0.0352 0.3197 1.0000
12.500 1.3670 0.04544 0.03701 -0.0362 0.3177 1.0000
13.000 1.1521 0.07047 0.06267 -0.0319 0.2997 1.0000
13.250 1.2116 0.06638 0.05856 -0.0313 0.3005 1.0000
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