EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 200,000 Max Cl/Cd: 56.61 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1233-il-200000.txt Download as CSV file: xf-e1233-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4248 0.08243 0.07908 -0.0631 1.0000 0.0379
-11.000 -0.4266 0.08086 0.07759 -0.0618 1.0000 0.0382
-10.750 -0.6000 0.05959 0.05547 -0.0726 0.9949 0.0330
-10.500 -0.5903 0.05542 0.05119 -0.0765 0.9879 0.0326
-10.250 -0.5958 0.05104 0.04651 -0.0794 0.9772 0.0324
-10.000 -0.5935 0.04634 0.04142 -0.0816 0.9663 0.0322
-9.750 -0.5820 0.04210 0.03679 -0.0833 0.9568 0.0319
-9.500 -0.5654 0.03804 0.03224 -0.0849 0.9483 0.0320
-9.250 -0.5480 0.03509 0.02890 -0.0850 0.9377 0.0322
-9.000 -0.5253 0.03240 0.02574 -0.0856 0.9289 0.0328
-8.750 -0.4932 0.03016 0.02333 -0.0873 0.9227 0.0336
-8.500 -0.4604 0.02898 0.02219 -0.0887 0.9154 0.0354
-8.250 -0.4286 0.02728 0.02021 -0.0898 0.9080 0.0371
-8.000 -0.3890 0.02540 0.01825 -0.0922 0.9044 0.0387
-7.750 -0.3598 0.02419 0.01700 -0.0925 0.8931 0.0404
-7.500 -0.3150 0.02265 0.01529 -0.0956 0.8882 0.0429
-7.250 -0.2801 0.02149 0.01422 -0.0972 0.8761 0.0460
-7.000 -0.2290 0.02028 0.01300 -0.1020 0.8680 0.0519
-6.750 -0.1824 0.01917 0.01188 -0.1059 0.8551 0.0590
-6.500 -0.1407 0.01826 0.01090 -0.1090 0.8390 0.0702
-6.250 -0.1052 0.01745 0.01013 -0.1110 0.8211 0.0847
-6.000 -0.0739 0.01693 0.00951 -0.1119 0.8027 0.1010
-5.750 -0.0482 0.01641 0.00899 -0.1119 0.7847 0.1160
-5.500 -0.0244 0.01602 0.00858 -0.1114 0.7672 0.1316
-5.250 -0.0018 0.01566 0.00819 -0.1107 0.7507 0.1489
-5.000 0.0208 0.01531 0.00782 -0.1099 0.7356 0.1705
-4.750 0.0421 0.01487 0.00743 -0.1090 0.7214 0.1995
-4.500 0.0596 0.01432 0.00706 -0.1075 0.7067 0.2457
-4.250 0.0758 0.01349 0.00666 -0.1061 0.6934 0.3444
-4.000 0.0931 0.01277 0.00660 -0.1045 0.6816 0.5063
-3.750 0.1142 0.01287 0.00689 -0.1027 0.6686 0.5871
-3.500 0.1389 0.01318 0.00714 -0.1014 0.6568 0.6257
-3.250 0.1645 0.01356 0.00741 -0.1003 0.6455 0.6502
-3.000 0.1880 0.01392 0.00769 -0.0988 0.6338 0.6684
-2.750 0.2142 0.01432 0.00792 -0.0979 0.6238 0.6837
-2.500 0.2379 0.01460 0.00810 -0.0967 0.6129 0.6982
-2.250 0.2623 0.01506 0.00847 -0.0951 0.6036 0.7070
-2.000 0.2858 0.01528 0.00859 -0.0939 0.5934 0.7189
-1.750 0.3097 0.01570 0.00891 -0.0923 0.5848 0.7269
-1.500 0.3330 0.01587 0.00901 -0.0911 0.5753 0.7379
-1.250 0.3566 0.01632 0.00934 -0.0894 0.5678 0.7458
-1.000 0.3773 0.01654 0.00955 -0.0875 0.5591 0.7577
-0.750 0.3979 0.01696 0.00989 -0.0850 0.5518 0.7674
-0.500 0.4193 0.01714 0.01002 -0.0834 0.5439 0.7774
-0.250 0.4400 0.01731 0.01014 -0.0814 0.5364 0.7842
0.000 0.4690 0.01742 0.01007 -0.0821 0.5297 0.7928
0.250 0.4879 0.01744 0.01012 -0.0799 0.5226 0.7971
0.500 0.5113 0.01752 0.01012 -0.0789 0.5162 0.8023
0.750 0.5391 0.01762 0.01009 -0.0793 0.5099 0.8085
1.000 0.5615 0.01758 0.01005 -0.0784 0.5030 0.8132
1.250 0.5851 0.01763 0.01001 -0.0775 0.4971 0.8170
1.500 0.6111 0.01776 0.01006 -0.0773 0.4915 0.8216
1.750 0.6364 0.01779 0.01007 -0.0772 0.4854 0.8267
2.000 0.6620 0.01782 0.01004 -0.0770 0.4800 0.8307
2.250 0.6891 0.01800 0.01009 -0.0769 0.4751 0.8344
2.500 0.7094 0.01801 0.01017 -0.0757 0.4695 0.8387
2.750 0.7354 0.01809 0.01020 -0.0757 0.4640 0.8433
3.000 0.7639 0.01822 0.01023 -0.0762 0.4593 0.8475
3.250 0.7872 0.01837 0.01037 -0.0754 0.4548 0.8511
3.500 0.8089 0.01845 0.01050 -0.0745 0.4499 0.8552
3.750 0.8346 0.01857 0.01058 -0.0744 0.4451 0.8597
4.000 0.8646 0.01877 0.01068 -0.0753 0.4408 0.8640
4.250 0.8859 0.01891 0.01085 -0.0742 0.4364 0.8677
4.500 0.9066 0.01903 0.01102 -0.0731 0.4319 0.8719
4.750 0.9318 0.01919 0.01117 -0.0729 0.4277 0.8763
5.000 0.9610 0.01941 0.01132 -0.0736 0.4238 0.8807
5.250 0.9857 0.01966 0.01154 -0.0733 0.4201 0.8846
5.500 1.0030 0.01980 0.01178 -0.0716 0.4159 0.8894
5.750 1.0262 0.01998 0.01200 -0.0711 0.4116 0.8941
6.000 1.0514 0.02016 0.01216 -0.0710 0.4080 0.8985
6.250 1.0778 0.02040 0.01234 -0.0710 0.4047 0.9032
6.500 1.1000 0.02073 0.01273 -0.0704 0.4013 0.9086
6.750 1.1176 0.02095 0.01306 -0.0689 0.3975 0.9141
7.000 1.1363 0.02112 0.01328 -0.0675 0.3938 0.9197
7.250 1.1602 0.02131 0.01347 -0.0672 0.3903 0.9261
7.500 1.1877 0.02159 0.01369 -0.0675 0.3872 0.9321
7.750 1.2093 0.02199 0.01416 -0.0668 0.3841 0.9396
8.000 1.2235 0.02227 0.01459 -0.0648 0.3808 0.9486
8.250 1.2443 0.02256 0.01498 -0.0641 0.3772 0.9590
8.500 1.2752 0.02287 0.01531 -0.0654 0.3736 0.9710
8.750 1.3156 0.02324 0.01563 -0.0685 0.3702 0.9897
9.000 1.3449 0.02388 0.01629 -0.0697 0.3671 1.0000
9.250 1.3610 0.02444 0.01702 -0.0687 0.3638 1.0000
9.500 1.3807 0.02495 0.01762 -0.0683 0.3604 1.0000
9.750 1.4058 0.02538 0.01807 -0.0686 0.3570 1.0000
10.000 1.4383 0.02577 0.01843 -0.0702 0.3540 1.0000
10.250 1.4775 0.02651 0.01910 -0.0731 0.3509 1.0000
10.500 1.4819 0.02716 0.01995 -0.0700 0.3481 1.0000
10.750 1.4904 0.02785 0.02078 -0.0677 0.3449 1.0000
11.000 1.5056 0.02841 0.02141 -0.0664 0.3416 1.0000
11.250 1.5297 0.02884 0.02184 -0.0665 0.3386 1.0000
11.500 1.5656 0.02926 0.02220 -0.0685 0.3358 1.0000
11.750 1.5818 0.03010 0.02311 -0.0675 0.3329 1.0000
12.000 1.5746 0.03104 0.02424 -0.0628 0.3298 1.0000
12.250 1.5766 0.03190 0.02524 -0.0598 0.3265 1.0000
12.500 1.5903 0.03249 0.02587 -0.0584 0.3234 1.0000
12.750 1.6204 0.03268 0.02602 -0.0592 0.3202 1.0000
13.000 1.6499 0.03324 0.02655 -0.0602 0.3169 1.0000
13.250 1.6286 0.03473 0.02828 -0.0544 0.3140 1.0000
13.500 1.6186 0.03615 0.02987 -0.0506 0.3106 1.0000
13.750 1.6256 0.03701 0.03080 -0.0489 0.3072 1.0000
14.000 1.6555 0.03701 0.03075 -0.0495 0.3040 1.0000
14.250 1.6830 0.03744 0.03116 -0.0501 0.3006 1.0000
14.500 1.6487 0.04015 0.03414 -0.0446 0.2976 1.0000
14.750 1.6280 0.04266 0.03683 -0.0413 0.2939 1.0000
15.000 1.6359 0.04369 0.03791 -0.0403 0.2904 1.0000
15.250 1.6774 0.04285 0.03698 -0.0415 0.2870 1.0000
15.500 1.6687 0.04507 0.03933 -0.0395 0.2835 1.0000
15.750 1.6178 0.05037 0.04491 -0.0360 0.2798 1.0000
16.000 1.6023 0.05356 0.04822 -0.0348 0.2758 1.0000
16.250 1.6467 0.05175 0.04632 -0.0354 0.2721 1.0000
16.500 1.6503 0.05350 0.04813 -0.0348 0.2682 1.0000
16.750 1.5281 0.06789 0.06295 -0.0337 0.2627 1.0000
17.000 1.5543 0.06735 0.06241 -0.0337 0.2588 1.0000
17.250 1.6351 0.06112 0.05599 -0.0335 0.2554 1.0000
17.500 1.3219 0.10457 0.10005 -0.0424 0.2385 1.0000
17.750 1.3744 0.09972 0.09523 -0.0409 0.2378 1.0000
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