EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 200,000 Max Cl/Cd: 65.98 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e550-il-200000.txt Download as CSV file: xf-e550-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5452 0.05961 0.05552 -0.0702 1.0000 0.0266
-12.000 -0.5530 0.05549 0.05136 -0.0701 1.0000 0.0262
-11.750 -0.6544 0.06075 0.05616 -0.0685 1.0000 0.0265
-11.500 -0.6632 0.05711 0.05246 -0.0677 1.0000 0.0262
-11.250 -0.6692 0.05415 0.04944 -0.0666 1.0000 0.0257
-11.000 -0.6807 0.05125 0.04642 -0.0650 1.0000 0.0250
-10.750 -0.7536 0.04678 0.04120 -0.0564 1.0000 0.0226
-10.500 -0.7652 0.04533 0.03955 -0.0521 1.0000 0.0224
-10.250 -0.7601 0.04257 0.03674 -0.0500 1.0000 0.0222
-10.000 -0.7584 0.04034 0.03433 -0.0480 0.9979 0.0221
-9.750 -0.7282 0.03710 0.03058 -0.0516 0.9842 0.0224
-9.500 -0.6901 0.03463 0.02829 -0.0548 0.9711 0.0240
-9.250 -0.6544 0.03212 0.02552 -0.0575 0.9538 0.0248
-9.000 -0.6082 0.02946 0.02254 -0.0612 0.9415 0.0252
-8.750 -0.5541 0.02714 0.01996 -0.0655 0.9282 0.0261
-8.500 -0.4926 0.02518 0.01796 -0.0705 0.9139 0.0280
-8.250 -0.4357 0.02377 0.01645 -0.0760 0.8879 0.0312
-8.000 -0.3979 0.02258 0.01519 -0.0791 0.8554 0.0360
-7.750 -0.3809 0.02152 0.01401 -0.0784 0.8270 0.0404
-7.500 -0.3709 0.02071 0.01304 -0.0763 0.8032 0.0452
-7.250 -0.3707 0.01979 0.01208 -0.0731 0.7840 0.0511
-7.000 -0.3674 0.01895 0.01118 -0.0700 0.7680 0.0623
-6.750 -0.3642 0.01791 0.01020 -0.0670 0.7543 0.0816
-6.500 -0.3600 0.01675 0.00924 -0.0643 0.7427 0.1255
-6.250 -0.3589 0.01518 0.00821 -0.0616 0.7311 0.2238
-6.000 -0.3612 0.01339 0.00764 -0.0582 0.7213 0.4464
-5.750 -0.3365 0.01397 0.00824 -0.0570 0.7117 0.5350
-5.500 -0.3096 0.01479 0.00897 -0.0560 0.7017 0.5629
-5.250 -0.2817 0.01559 0.00961 -0.0550 0.6937 0.5807
-5.000 -0.2538 0.01635 0.01032 -0.0540 0.6847 0.5930
-4.750 -0.2261 0.01697 0.01080 -0.0532 0.6778 0.6048
-4.500 -0.1982 0.01770 0.01147 -0.0522 0.6703 0.6151
-4.250 -0.1701 0.01833 0.01203 -0.0512 0.6637 0.6229
-4.000 -0.1427 0.01892 0.01250 -0.0504 0.6577 0.6330
-3.750 -0.1132 0.02022 0.01385 -0.0482 0.6509 0.6416
-3.500 -0.0877 0.02054 0.01403 -0.0475 0.6454 0.6532
-3.250 -0.0600 0.02085 0.01429 -0.0466 0.6400 0.6559
-3.000 -0.0337 0.02085 0.01423 -0.0463 0.6345 0.6591
-2.750 -0.0079 0.02059 0.01382 -0.0465 0.6299 0.6637
-2.500 0.0173 0.02003 0.01307 -0.0476 0.6258 0.6691
-2.250 0.0432 0.01995 0.01299 -0.0472 0.6207 0.6708
-2.000 0.0699 0.01988 0.01286 -0.0470 0.6160 0.6727
-1.750 0.0972 0.01979 0.01266 -0.0472 0.6120 0.6751
-1.500 0.1241 0.01964 0.01243 -0.0475 0.6082 0.6776
-1.250 0.1504 0.01941 0.01215 -0.0480 0.6039 0.6809
-1.000 0.1783 0.01909 0.01172 -0.0491 0.6001 0.6839
-0.750 0.2062 0.01891 0.01145 -0.0496 0.5966 0.6862
-0.500 0.2343 0.01892 0.01137 -0.0498 0.5936 0.6878
-0.250 0.2600 0.01885 0.01134 -0.0498 0.5894 0.6893
0.000 0.2870 0.01879 0.01128 -0.0500 0.5856 0.6910
0.250 0.3147 0.01875 0.01120 -0.0503 0.5824 0.6932
0.500 0.3434 0.01872 0.01109 -0.0509 0.5796 0.6957
0.750 0.3727 0.01871 0.01099 -0.0518 0.5768 0.6980
1.000 0.3996 0.01864 0.01095 -0.0524 0.5729 0.7003
1.250 0.4273 0.01861 0.01091 -0.0529 0.5693 0.7022
1.500 0.4544 0.01863 0.01094 -0.0530 0.5663 0.7038
1.750 0.4823 0.01868 0.01098 -0.0532 0.5636 0.7058
2.000 0.5113 0.01880 0.01104 -0.0537 0.5610 0.7079
2.250 0.5369 0.01890 0.01123 -0.0538 0.5575 0.7099
2.500 0.5635 0.01900 0.01138 -0.0540 0.5541 0.7121
2.750 0.5914 0.01906 0.01145 -0.0545 0.5508 0.7145
3.000 0.6208 0.01911 0.01146 -0.0553 0.5478 0.7169
3.250 0.6502 0.01921 0.01152 -0.0559 0.5453 0.7191
3.500 0.6753 0.01941 0.01182 -0.0557 0.5421 0.7212
3.750 0.6998 0.01959 0.01211 -0.0555 0.5382 0.7236
4.000 0.7265 0.01972 0.01229 -0.0556 0.5347 0.7260
4.250 0.7552 0.01979 0.01237 -0.0561 0.5315 0.7286
4.500 0.7855 0.01992 0.01245 -0.0569 0.5287 0.7313
4.750 0.8102 0.02017 0.01280 -0.0569 0.5246 0.7342
5.000 0.8345 0.02032 0.01307 -0.0566 0.5202 0.7364
5.250 0.8616 0.02039 0.01319 -0.0567 0.5165 0.7390
5.500 0.8911 0.02044 0.01325 -0.0571 0.5133 0.7421
5.750 0.9160 0.02069 0.01359 -0.0570 0.5091 0.7456
6.000 0.9401 0.02089 0.01390 -0.0568 0.5041 0.7492
6.250 0.9683 0.02088 0.01394 -0.0571 0.4998 0.7522
6.500 0.9988 0.02085 0.01389 -0.0576 0.4962 0.7551
6.750 1.0190 0.02110 0.01434 -0.0566 0.4906 0.7586
7.000 1.0448 0.02112 0.01444 -0.0565 0.4852 0.7626
7.250 1.0769 0.02099 0.01426 -0.0574 0.4808 0.7669
7.500 1.0974 0.02114 0.01459 -0.0563 0.4748 0.7705
7.750 1.1215 0.02110 0.01467 -0.0558 0.4688 0.7750
8.000 1.1539 0.02090 0.01442 -0.0566 0.4640 0.7803
8.250 1.1714 0.02106 0.01480 -0.0551 0.4567 0.7852
8.500 1.1976 0.02083 0.01464 -0.0548 0.4504 0.7900
8.750 1.2202 0.02081 0.01473 -0.0541 0.4434 0.7959
9.000 1.2426 0.02066 0.01469 -0.0532 0.4357 0.8018
9.250 1.2635 0.02054 0.01468 -0.0521 0.4279 0.8081
9.500 1.2842 0.02038 0.01462 -0.0510 0.4189 0.8160
9.750 1.2991 0.02033 0.01476 -0.0488 0.4094 0.8238
10.000 1.3184 0.02016 0.01464 -0.0474 0.3996 0.8335
10.250 1.3284 0.02019 0.01485 -0.0445 0.3878 0.8447
10.500 1.3368 0.02026 0.01508 -0.0414 0.3751 0.8577
10.750 1.3407 0.02036 0.01530 -0.0375 0.3618 0.8752
11.000 1.3403 0.02057 0.01563 -0.0329 0.3478 0.9057
11.250 1.3456 0.02102 0.01615 -0.0304 0.3297 1.0000
11.500 1.3477 0.02206 0.01706 -0.0281 0.3103 1.0000
11.750 1.3451 0.02346 0.01840 -0.0256 0.2906 1.0000
12.000 1.3392 0.02523 0.02009 -0.0231 0.2721 1.0000
12.250 1.3308 0.02741 0.02219 -0.0210 0.2546 1.0000
12.500 1.3217 0.02988 0.02460 -0.0192 0.2382 1.0000
12.750 1.3123 0.03260 0.02727 -0.0179 0.2229 1.0000
13.000 1.3029 0.03551 0.03013 -0.0168 0.2083 1.0000
13.250 1.2939 0.03855 0.03313 -0.0161 0.1945 1.0000
13.500 1.2850 0.04169 0.03625 -0.0155 0.1815 1.0000
13.750 1.2766 0.04491 0.03944 -0.0152 0.1694 1.0000
14.000 1.2683 0.04823 0.04273 -0.0150 0.1583 1.0000
14.250 1.2597 0.05173 0.04617 -0.0150 0.1476 1.0000
14.500 1.2543 0.05506 0.04952 -0.0152 0.1366 1.0000
14.750 1.2492 0.05845 0.05291 -0.0155 0.1265 1.0000
15.000 1.2429 0.06205 0.05647 -0.0159 0.1175 1.0000
15.250 1.2380 0.06562 0.06002 -0.0165 0.1088 1.0000
15.500 1.2348 0.06908 0.06352 -0.0171 0.1002 1.0000
15.750 1.2295 0.07280 0.06718 -0.0178 0.0931 1.0000
16.000 1.2273 0.07634 0.07078 -0.0186 0.0858 1.0000
16.250 1.2243 0.07993 0.07436 -0.0195 0.0796 1.0000
16.500 1.2216 0.08363 0.07809 -0.0205 0.0738 1.0000
16.750 1.2200 0.08717 0.08164 -0.0214 0.0685 1.0000
17.000 1.2181 0.09088 0.08540 -0.0226 0.0637 1.0000
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Polar data table (+)
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