EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 200,000 Max Cl/Cd: 58.07 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1233-il-200000-n5.txt Download as CSV file: xf-e1233-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5508 0.07964 0.07528 -0.0696 1.0000 0.0159
-13.500 -0.6061 0.06706 0.06232 -0.0773 1.0000 0.0156
-13.250 -0.6322 0.06109 0.05616 -0.0797 1.0000 0.0156
-13.000 -0.6489 0.05710 0.05206 -0.0804 1.0000 0.0157
-12.750 -0.6685 0.05321 0.04800 -0.0803 1.0000 0.0157
-12.500 -0.6840 0.05025 0.04491 -0.0794 1.0000 0.0157
-12.250 -0.6871 0.04747 0.04202 -0.0801 0.9984 0.0159
-12.000 -0.6764 0.04431 0.03864 -0.0835 0.9942 0.0159
-11.750 -0.6636 0.04176 0.03595 -0.0861 0.9892 0.0163
-11.500 -0.6481 0.03939 0.03339 -0.0887 0.9842 0.0166
-11.250 -0.6345 0.03724 0.03108 -0.0899 0.9774 0.0168
-11.000 -0.6160 0.03523 0.02888 -0.0917 0.9717 0.0172
-10.500 -0.5936 0.03197 0.02531 -0.0907 0.9498 0.0178
-10.250 -0.5827 0.03060 0.02380 -0.0896 0.9374 0.0183
-10.000 -0.5697 0.02950 0.02268 -0.0887 0.9246 0.0189
-9.750 -0.5507 0.02829 0.02141 -0.0884 0.9137 0.0193
-9.500 -0.5249 0.02710 0.02011 -0.0893 0.9048 0.0202
-9.250 -0.5015 0.02595 0.01884 -0.0894 0.8927 0.0208
-9.000 -0.4723 0.02472 0.01750 -0.0906 0.8822 0.0218
-8.750 -0.4368 0.02354 0.01625 -0.0930 0.8716 0.0226
-8.500 -0.4001 0.02244 0.01504 -0.0956 0.8588 0.0239
-8.250 -0.3557 0.02134 0.01381 -0.0997 0.8457 0.0253
-8.000 -0.3069 0.02036 0.01272 -0.1047 0.8307 0.0275
-7.750 -0.2649 0.01956 0.01181 -0.1082 0.8122 0.0303
-7.500 -0.2309 0.01892 0.01102 -0.1100 0.7922 0.0334
-7.250 -0.2031 0.01839 0.01038 -0.1105 0.7732 0.0370
-7.000 -0.1789 0.01793 0.00983 -0.1102 0.7547 0.0417
-6.750 -0.1564 0.01754 0.00936 -0.1096 0.7375 0.0475
-6.250 -0.1140 0.01690 0.00858 -0.1076 0.7052 0.0627
-6.000 -0.0930 0.01662 0.00825 -0.1065 0.6908 0.0715
-5.750 -0.0716 0.01637 0.00793 -0.1055 0.6773 0.0809
-5.500 -0.0501 0.01614 0.00764 -0.1045 0.6640 0.0912
-5.250 -0.0289 0.01590 0.00737 -0.1034 0.6511 0.1027
-5.000 -0.0073 0.01565 0.00710 -0.1025 0.6393 0.1165
-4.750 0.0142 0.01539 0.00684 -0.1015 0.6280 0.1328
-4.500 0.0361 0.01512 0.00659 -0.1006 0.6171 0.1519
-4.000 0.0800 0.01454 0.00609 -0.0989 0.5959 0.2074
-3.750 0.1017 0.01419 0.00584 -0.0982 0.5863 0.2529
-3.500 0.1234 0.01373 0.00560 -0.0975 0.5767 0.3185
-3.250 0.1446 0.01324 0.00540 -0.0967 0.5678 0.4072
-3.000 0.1664 0.01289 0.00543 -0.0957 0.5586 0.5054
-2.500 0.2148 0.01299 0.00565 -0.0938 0.5412 0.5978
-2.250 0.2401 0.01313 0.00570 -0.0931 0.5332 0.6219
-2.000 0.2656 0.01327 0.00578 -0.0924 0.5253 0.6400
-1.750 0.2907 0.01343 0.00587 -0.0916 0.5173 0.6547
-1.500 0.3159 0.01360 0.00596 -0.0909 0.5100 0.6672
-1.250 0.3417 0.01375 0.00602 -0.0904 0.5024 0.6806
-1.000 0.3661 0.01400 0.00620 -0.0895 0.4958 0.6944
-0.750 0.3899 0.01426 0.00644 -0.0882 0.4894 0.7072
-0.500 0.4151 0.01445 0.00654 -0.0876 0.4825 0.7186
-0.250 0.4386 0.01464 0.00666 -0.0865 0.4764 0.7244
0.000 0.4640 0.01474 0.00671 -0.0860 0.4700 0.7302
0.250 0.4907 0.01483 0.00669 -0.0859 0.4638 0.7358
0.500 0.5152 0.01495 0.00674 -0.0853 0.4585 0.7390
0.750 0.5403 0.01505 0.00681 -0.0847 0.4533 0.7421
1.000 0.5654 0.01515 0.00686 -0.0843 0.4475 0.7457
1.250 0.5906 0.01527 0.00690 -0.0839 0.4421 0.7498
1.500 0.6167 0.01539 0.00693 -0.0837 0.4371 0.7539
1.750 0.6420 0.01548 0.00701 -0.0833 0.4319 0.7570
2.000 0.6661 0.01561 0.00710 -0.0827 0.4272 0.7599
2.250 0.6903 0.01576 0.00720 -0.0820 0.4230 0.7632
2.500 0.7153 0.01590 0.00730 -0.0817 0.4186 0.7665
2.750 0.7405 0.01602 0.00741 -0.0814 0.4138 0.7703
3.000 0.7658 0.01617 0.00750 -0.0811 0.4091 0.7742
3.250 0.7884 0.01633 0.00762 -0.0802 0.4051 0.7769
3.500 0.8119 0.01649 0.00777 -0.0795 0.4013 0.7797
3.750 0.8355 0.01662 0.00793 -0.0789 0.3973 0.7828
4.000 0.8588 0.01678 0.00809 -0.0782 0.3933 0.7865
4.250 0.8822 0.01697 0.00823 -0.0776 0.3894 0.7904
4.500 0.9056 0.01719 0.00838 -0.0770 0.3859 0.7936
4.750 0.9274 0.01733 0.00858 -0.0761 0.3820 0.7963
5.000 0.9493 0.01751 0.00881 -0.0752 0.3783 0.7995
5.250 0.9716 0.01772 0.00902 -0.0744 0.3748 0.8031
5.500 0.9943 0.01796 0.00924 -0.0737 0.3716 0.8071
6.000 1.0386 0.01845 0.00974 -0.0722 0.3650 0.8137
6.250 1.0592 0.01867 0.01003 -0.0711 0.3613 0.8171
6.500 1.0799 0.01892 0.01032 -0.0701 0.3580 0.8211
6.750 1.1014 0.01920 0.01060 -0.0693 0.3550 0.8254
7.000 1.1236 0.01951 0.01087 -0.0687 0.3523 0.8293
7.250 1.1437 0.01979 0.01121 -0.0677 0.3495 0.8327
7.500 1.1625 0.02007 0.01158 -0.0664 0.3461 0.8368
7.750 1.1818 0.02037 0.01194 -0.0653 0.3429 0.8416
8.000 1.2015 0.02070 0.01230 -0.0643 0.3398 0.8466
8.250 1.2199 0.02101 0.01264 -0.0630 0.3371 0.8510
8.500 1.2404 0.02136 0.01298 -0.0622 0.3347 0.8558
8.750 1.2590 0.02174 0.01345 -0.0611 0.3321 0.8612
9.000 1.2755 0.02211 0.01394 -0.0597 0.3290 0.8670
9.250 1.2916 0.02250 0.01441 -0.0582 0.3259 0.8738
9.500 1.3082 0.02290 0.01487 -0.0569 0.3229 0.8813
9.750 1.3249 0.02329 0.01531 -0.0556 0.3205 0.8895
10.000 1.3436 0.02370 0.01573 -0.0546 0.3182 0.8990
10.500 1.3728 0.02463 0.01696 -0.0517 0.3127 0.9422
11.000 1.4044 0.02579 0.01825 -0.0500 0.3068 1.0000
11.250 1.4217 0.02642 0.01891 -0.0493 0.3044 1.0000
11.500 1.4406 0.02702 0.01950 -0.0489 0.3020 1.0000
11.750 1.4536 0.02784 0.02041 -0.0478 0.2993 1.0000
12.000 1.4640 0.02876 0.02146 -0.0465 0.2963 1.0000
12.250 1.4750 0.02969 0.02248 -0.0453 0.2933 1.0000
12.500 1.4864 0.03061 0.02346 -0.0442 0.2905 1.0000
12.750 1.4995 0.03147 0.02434 -0.0433 0.2878 1.0000
13.000 1.5148 0.03227 0.02513 -0.0427 0.2851 1.0000
13.250 1.5180 0.03371 0.02675 -0.0412 0.2821 1.0000
13.500 1.5218 0.03518 0.02835 -0.0399 0.2785 1.0000
13.750 1.5275 0.03659 0.02984 -0.0388 0.2752 1.0000
14.000 1.5364 0.03781 0.03109 -0.0380 0.2720 1.0000
14.250 1.5459 0.03907 0.03237 -0.0373 0.2689 1.0000
14.500 1.5425 0.04134 0.03483 -0.0362 0.2653 1.0000
14.750 1.5421 0.04349 0.03711 -0.0354 0.2616 1.0000
15.000 1.5455 0.04538 0.03905 -0.0348 0.2581 1.0000
15.250 1.5546 0.04678 0.04045 -0.0345 0.2549 1.0000
15.500 1.5478 0.04978 0.04363 -0.0340 0.2512 1.0000
15.750 1.5405 0.05298 0.04699 -0.0337 0.2471 1.0000
16.000 1.5391 0.05565 0.04973 -0.0336 0.2431 1.0000
16.250 1.5468 0.05734 0.05141 -0.0335 0.2397 1.0000
16.500 1.5303 0.06193 0.05621 -0.0339 0.2353 1.0000
16.750 1.5174 0.06627 0.06069 -0.0344 0.2305 1.0000
17.000 1.5186 0.06891 0.06335 -0.0348 0.2263 1.0000
17.250 1.5056 0.07349 0.06805 -0.0356 0.2217 1.0000
17.500 1.4840 0.07939 0.07411 -0.0370 0.2163 1.0000
17.750 1.4862 0.08210 0.07683 -0.0376 0.2116 1.0000
18.000 1.4611 0.08877 0.08367 -0.0395 0.2061 1.0000
18.250 1.4442 0.09442 0.08942 -0.0412 0.2004 1.0000
18.500 1.4491 0.09686 0.09186 -0.0420 0.1957 1.0000
18.750 1.4101 0.10607 0.10127 -0.0452 0.1887 1.0000
19.000 1.4179 0.10812 0.10328 -0.0459 0.1835 1.0000
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