S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 50,000 Max Cl/Cd: 36.2 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7055-il-50000-n5.txt Download as CSV file: xf-s7055-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3441 0.10646 0.09986 -0.0379 1.0000 0.1151
-8.750 -0.3568 0.10448 0.09804 -0.0399 1.0000 0.1159
-8.500 -0.3658 0.10210 0.09579 -0.0407 1.0000 0.1160
-8.250 -0.3055 0.08513 0.07929 -0.0425 1.0000 0.0602
-8.000 -0.3616 0.08940 0.08314 -0.0423 1.0000 0.0591
-7.750 -0.3670 0.08700 0.08085 -0.0404 1.0000 0.0579
-7.500 -0.3784 0.08470 0.07867 -0.0389 1.0000 0.0568
-7.250 -0.3907 0.08226 0.07633 -0.0377 1.0000 0.0558
-7.000 -0.4028 0.07972 0.07386 -0.0366 1.0000 0.0548
-6.750 -0.4144 0.07681 0.07100 -0.0359 1.0000 0.0538
-6.500 -0.4239 0.07364 0.06784 -0.0355 1.0000 0.0526
-6.250 -0.4313 0.06996 0.06413 -0.0355 1.0000 0.0513
-6.000 -0.4154 0.06262 0.05644 -0.0424 0.9919 0.0492
-5.500 -0.3704 0.05194 0.04493 -0.0507 0.9750 0.0489
-5.250 -0.3435 0.04903 0.04182 -0.0534 0.9681 0.0519
-5.000 -0.3186 0.04543 0.03775 -0.0555 0.9598 0.0545
-4.750 -0.2903 0.04163 0.03336 -0.0575 0.9528 0.0559
-4.500 -0.2620 0.03830 0.02938 -0.0587 0.9453 0.0572
-4.250 -0.2302 0.03547 0.02573 -0.0598 0.9387 0.0601
-4.000 -0.2016 0.03372 0.02385 -0.0609 0.9313 0.0659
-3.750 -0.1675 0.03179 0.02140 -0.0621 0.9253 0.0710
-3.500 -0.1376 0.03035 0.01972 -0.0627 0.9176 0.0791
-3.250 -0.0996 0.02895 0.01788 -0.0641 0.9124 0.0877
-3.000 -0.0713 0.02800 0.01686 -0.0644 0.9040 0.0990
-2.750 -0.0303 0.02689 0.01559 -0.0666 0.8993 0.1115
-2.500 -0.0027 0.02618 0.01477 -0.0666 0.8902 0.1255
-2.250 0.0355 0.02530 0.01391 -0.0685 0.8849 0.1569
-2.000 0.0597 0.02447 0.01338 -0.0681 0.8751 0.2090
-1.750 0.0841 0.02288 0.01307 -0.0679 0.8681 0.4686
-1.500 0.1832 0.02148 0.01256 -0.0792 0.8694 1.0000
-1.250 0.2083 0.02162 0.01235 -0.0789 0.8590 1.0000
-1.000 0.2324 0.02180 0.01222 -0.0783 0.8487 1.0000
-0.750 0.2633 0.02188 0.01203 -0.0788 0.8406 1.0000
-0.500 0.2881 0.02206 0.01197 -0.0783 0.8305 1.0000
-0.250 0.3112 0.02227 0.01196 -0.0775 0.8199 1.0000
0.000 0.3396 0.02238 0.01188 -0.0775 0.8114 1.0000
0.250 0.3654 0.02253 0.01187 -0.0770 0.8017 1.0000
0.500 0.3875 0.02278 0.01196 -0.0760 0.7908 1.0000
0.750 0.4132 0.02294 0.01199 -0.0755 0.7813 1.0000
1.000 0.4416 0.02301 0.01194 -0.0753 0.7726 1.0000
1.250 0.4632 0.02328 0.01212 -0.0742 0.7613 1.0000
1.500 0.4870 0.02348 0.01224 -0.0733 0.7510 1.0000
1.750 0.5179 0.02346 0.01213 -0.0734 0.7434 1.0000
2.000 0.5390 0.02375 0.01237 -0.0722 0.7318 1.0000
2.250 0.5616 0.02401 0.01260 -0.0712 0.7209 1.0000
2.500 0.5873 0.02415 0.01270 -0.0705 0.7111 1.0000
2.750 0.6153 0.02420 0.01272 -0.0701 0.7021 1.0000
3.000 0.6370 0.02451 0.01302 -0.0690 0.6904 1.0000
3.250 0.6602 0.02475 0.01330 -0.0681 0.6793 1.0000
3.500 0.6860 0.02489 0.01344 -0.0674 0.6690 1.0000
3.750 0.7140 0.02491 0.01347 -0.0669 0.6594 1.0000
4.000 0.7359 0.02522 0.01381 -0.0658 0.6471 1.0000
4.250 0.7587 0.02549 0.01417 -0.0648 0.6351 1.0000
4.500 0.7823 0.02573 0.01446 -0.0638 0.6234 1.0000
4.750 0.8073 0.02591 0.01469 -0.0630 0.6120 1.0000
5.000 0.8338 0.02601 0.01484 -0.0623 0.6008 1.0000
5.250 0.8584 0.02620 0.01514 -0.0614 0.5887 1.0000
5.500 0.8806 0.02652 0.01555 -0.0603 0.5755 1.0000
5.750 0.9031 0.02682 0.01594 -0.0592 0.5621 1.0000
6.000 0.9256 0.02711 0.01632 -0.0581 0.5485 1.0000
6.250 0.9481 0.02740 0.01676 -0.0570 0.5346 1.0000
6.500 0.9704 0.02771 0.01718 -0.0558 0.5204 1.0000
6.750 0.9924 0.02804 0.01762 -0.0546 0.5059 1.0000
7.000 1.0143 0.02838 0.01807 -0.0534 0.4910 1.0000
7.250 1.0360 0.02872 0.01852 -0.0521 0.4759 1.0000
7.500 1.0556 0.02916 0.01913 -0.0506 0.4597 1.0000
7.750 1.0729 0.02971 0.01982 -0.0490 0.4428 1.0000
8.000 1.0903 0.03024 0.02048 -0.0473 0.4255 1.0000
8.250 1.1080 0.03074 0.02109 -0.0456 0.4079 1.0000
8.500 1.1260 0.03122 0.02164 -0.0439 0.3902 1.0000
8.750 1.1373 0.03203 0.02261 -0.0416 0.3713 1.0000
9.000 1.1496 0.03276 0.02349 -0.0394 0.3523 1.0000
9.250 1.1615 0.03348 0.02426 -0.0371 0.3334 1.0000
9.500 1.1673 0.03451 0.02541 -0.0344 0.3140 1.0000
9.750 1.1723 0.03551 0.02648 -0.0315 0.2952 1.0000
10.000 1.1763 0.03666 0.02765 -0.0288 0.2765 1.0000
10.250 1.1776 0.03810 0.02918 -0.0262 0.2576 1.0000
10.500 1.1783 0.03965 0.03076 -0.0238 0.2390 1.0000
10.750 1.1779 0.04142 0.03253 -0.0217 0.2209 1.0000
11.000 1.1754 0.04352 0.03471 -0.0198 0.2023 1.0000
11.250 1.1721 0.04580 0.03705 -0.0182 0.1849 1.0000
11.500 1.1679 0.04832 0.03955 -0.0168 0.1687 1.0000
11.750 1.1628 0.05116 0.04239 -0.0158 0.1528 1.0000
12.000 1.1575 0.05423 0.04552 -0.0151 0.1380 1.0000
12.250 1.1514 0.05754 0.04884 -0.0147 0.1244 1.0000
12.500 1.1449 0.06106 0.05236 -0.0145 0.1124 1.0000
12.750 1.1379 0.06474 0.05600 -0.0145 0.1018 1.0000
13.000 1.1307 0.06874 0.06011 -0.0148 0.0910 1.0000
13.250 1.1252 0.07272 0.06419 -0.0152 0.0823 1.0000
13.500 1.1187 0.07682 0.06826 -0.0157 0.0750 1.0000
13.750 1.1117 0.08124 0.07282 -0.0167 0.0677 1.0000
14.000 1.1062 0.08558 0.07722 -0.0176 0.0622 1.0000
14.250 1.1006 0.09014 0.08194 -0.0187 0.0570 1.0000
14.500 1.0945 0.09463 0.08638 -0.0201 0.0525 1.0000
14.750 1.0879 0.09990 0.09197 -0.0217 0.0490 1.0000
15.000 1.0817 0.10498 0.09721 -0.0236 0.0459 1.0000
15.250 1.0784 0.10923 0.10142 -0.0251 0.0430 1.0000
15.500 1.0707 0.11504 0.10742 -0.0275 0.0412 1.0000
15.750 1.0587 0.12215 0.11483 -0.0309 0.0400 1.0000
16.000 1.0466 0.12958 0.12249 -0.0347 0.0395 1.0000
16.250 1.0321 0.13797 0.13109 -0.0393 0.0394 1.0000
16.500 1.0138 0.14801 0.14128 -0.0450 0.0398 1.0000
16.750 0.9961 0.15868 0.15201 -0.0510 0.0404 1.0000
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