EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 100,000 Max Cl/Cd: 43.07 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e552-il-100000-n5.txt Download as CSV file: xf-e552-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 552 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5163 0.10919 0.10366 -0.0493 1.0000 0.0190
-14.500 -0.5374 0.10048 0.09485 -0.0542 1.0000 0.0188
-14.250 -0.5593 0.09241 0.08665 -0.0588 1.0000 0.0187
-14.000 -0.5816 0.08503 0.07910 -0.0629 1.0000 0.0186
-13.750 -0.6019 0.07862 0.07250 -0.0663 1.0000 0.0186
-13.500 -0.6190 0.07322 0.06691 -0.0687 1.0000 0.0186
-13.250 -0.6311 0.06876 0.06228 -0.0704 1.0000 0.0185
-13.000 -0.6435 0.06449 0.05780 -0.0718 1.0000 0.0187
-12.750 -0.6514 0.06080 0.05392 -0.0726 1.0000 0.0188
-12.500 -0.6593 0.05734 0.05027 -0.0731 1.0000 0.0192
-12.250 -0.6592 0.05490 0.04778 -0.0732 1.0000 0.0195
-12.000 -0.6588 0.05270 0.04555 -0.0731 1.0000 0.0201
-11.750 -0.6586 0.05055 0.04333 -0.0729 1.0000 0.0208
-11.500 -0.6567 0.04840 0.04107 -0.0722 1.0000 0.0214
-11.250 -0.6532 0.04640 0.03894 -0.0714 1.0000 0.0220
-11.000 -0.6475 0.04453 0.03692 -0.0702 1.0000 0.0228
-10.750 -0.6395 0.04292 0.03517 -0.0687 1.0000 0.0233
-10.500 -0.6314 0.04149 0.03375 -0.0671 1.0000 0.0240
-10.250 -0.6254 0.04020 0.03249 -0.0655 1.0000 0.0246
-10.000 -0.6221 0.03897 0.03129 -0.0635 1.0000 0.0256
-9.500 -0.5729 0.03576 0.02797 -0.0666 0.9536 0.0298
-9.250 -0.5381 0.03404 0.02619 -0.0705 0.9292 0.0336
-9.000 -0.5030 0.03227 0.02434 -0.0745 0.9041 0.0376
-8.750 -0.4697 0.03052 0.02248 -0.0785 0.8779 0.0446
-8.500 -0.4452 0.02897 0.02078 -0.0808 0.8508 0.0523
-8.250 -0.4339 0.02744 0.01916 -0.0811 0.8261 0.0612
-8.000 -0.4260 0.02607 0.01773 -0.0806 0.8052 0.0719
-7.750 -0.4173 0.02481 0.01643 -0.0797 0.7877 0.0875
-7.500 -0.4096 0.02348 0.01517 -0.0788 0.7724 0.1110
-7.250 -0.4008 0.02205 0.01387 -0.0780 0.7586 0.1489
-7.000 -0.3928 0.02036 0.01250 -0.0772 0.7465 0.2167
-6.750 -0.3805 0.01941 0.01232 -0.0760 0.7354 0.3398
-6.500 -0.3557 0.01958 0.01244 -0.0755 0.7244 0.4028
-6.250 -0.3294 0.01980 0.01241 -0.0753 0.7152 0.4336
-6.000 -0.3025 0.02026 0.01272 -0.0747 0.7058 0.4536
-5.750 -0.2755 0.02066 0.01293 -0.0742 0.6972 0.4693
-5.500 -0.2490 0.02092 0.01298 -0.0737 0.6888 0.4823
-5.250 -0.2227 0.02118 0.01304 -0.0733 0.6810 0.4958
-5.000 -0.1948 0.02191 0.01375 -0.0721 0.6733 0.5059
-4.750 -0.1681 0.02215 0.01384 -0.0716 0.6668 0.5156
-4.500 -0.1415 0.02218 0.01374 -0.0713 0.6599 0.5211
-4.250 -0.1152 0.02178 0.01305 -0.0718 0.6543 0.5277
-4.000 -0.0884 0.02171 0.01289 -0.0716 0.6480 0.5303
-3.750 -0.0615 0.02163 0.01269 -0.0715 0.6420 0.5332
-3.500 -0.0340 0.02148 0.01236 -0.0717 0.6372 0.5366
-3.250 -0.0076 0.02125 0.01200 -0.0719 0.6311 0.5406
-3.000 0.0197 0.02100 0.01155 -0.0724 0.6260 0.5447
-2.750 0.0475 0.02093 0.01136 -0.0725 0.6220 0.5467
-2.500 0.0744 0.02087 0.01125 -0.0725 0.6172 0.5492
-2.250 0.1014 0.02080 0.01110 -0.0726 0.6123 0.5523
-2.000 0.1292 0.02069 0.01085 -0.0729 0.6080 0.5557
-1.750 0.1577 0.02056 0.01053 -0.0734 0.6043 0.5592
-1.500 0.1843 0.02051 0.01045 -0.0736 0.5995 0.5618
-1.250 0.2113 0.02052 0.01044 -0.0735 0.5955 0.5643
-1.000 0.2390 0.02052 0.01038 -0.0737 0.5921 0.5672
-0.750 0.2676 0.02051 0.01026 -0.0740 0.5892 0.5704
-0.500 0.2942 0.02052 0.01025 -0.0742 0.5849 0.5737
-0.250 0.3217 0.02052 0.01018 -0.0746 0.5807 0.5772
0.000 0.3488 0.02057 0.01022 -0.0746 0.5773 0.5796
0.250 0.3768 0.02062 0.01024 -0.0747 0.5745 0.5826
0.500 0.4042 0.02072 0.01031 -0.0749 0.5715 0.5861
0.750 0.4303 0.02083 0.01045 -0.0750 0.5677 0.5899
1.000 0.4576 0.02092 0.01051 -0.0752 0.5641 0.5936
1.250 0.4846 0.02101 0.01062 -0.0752 0.5609 0.5962
1.500 0.5126 0.02110 0.01069 -0.0754 0.5583 0.5995
1.750 0.5394 0.02127 0.01088 -0.0755 0.5555 0.6035
2.000 0.5647 0.02148 0.01115 -0.0755 0.5517 0.6082
2.250 0.5906 0.02165 0.01138 -0.0754 0.5482 0.6118
2.500 0.6172 0.02180 0.01158 -0.0753 0.5452 0.6155
2.750 0.6452 0.02194 0.01172 -0.0756 0.5427 0.6198
3.000 0.6726 0.02214 0.01192 -0.0758 0.5400 0.6246
3.250 0.6951 0.02246 0.01240 -0.0753 0.5360 0.6286
3.500 0.7197 0.02271 0.01275 -0.0750 0.5325 0.6332
3.750 0.7463 0.02292 0.01300 -0.0750 0.5295 0.6388
4.000 0.7742 0.02307 0.01319 -0.0752 0.5269 0.6442
4.250 0.7994 0.02334 0.01354 -0.0750 0.5238 0.6492
4.500 0.8204 0.02378 0.01414 -0.0743 0.5195 0.6551
4.750 0.8446 0.02407 0.01454 -0.0740 0.5158 0.6607
5.000 0.8709 0.02424 0.01480 -0.0739 0.5126 0.6669
5.250 0.9002 0.02437 0.01493 -0.0742 0.5100 0.6745
5.500 0.9175 0.02490 0.01570 -0.0729 0.5051 0.6809
5.750 0.9396 0.02528 0.01621 -0.0724 0.5006 0.6891
6.000 0.9657 0.02542 0.01644 -0.0722 0.4970 0.6966
6.250 0.9960 0.02544 0.01650 -0.0726 0.4940 0.7060
6.500 1.0085 0.02613 0.01745 -0.0706 0.4880 0.7142
6.750 1.0309 0.02640 0.01785 -0.0700 0.4833 0.7246
7.000 1.0591 0.02638 0.01792 -0.0700 0.4796 0.7361
7.250 1.0755 0.02684 0.01859 -0.0685 0.4743 0.7479
7.500 1.0925 0.02720 0.01914 -0.0670 0.4684 0.7613
7.750 1.1201 0.02705 0.01908 -0.0667 0.4640 0.7769
8.000 1.1318 0.02754 0.01981 -0.0645 0.4577 0.7947
8.250 1.1476 0.02773 0.02020 -0.0627 0.4516 0.8173
8.500 1.1749 0.02731 0.01988 -0.0619 0.4472 0.8474
8.750 1.1715 0.02806 0.02098 -0.0576 0.4394 0.9110
9.000 1.1998 0.02786 0.02085 -0.0578 0.4332 1.0000
9.250 1.2048 0.02869 0.02181 -0.0553 0.4252 1.0000
9.500 1.2256 0.02871 0.02187 -0.0543 0.4181 1.0000
9.750 1.2218 0.02980 0.02309 -0.0508 0.4096 1.0000
10.000 1.2431 0.02975 0.02306 -0.0499 0.4018 1.0000
10.250 1.2278 0.03167 0.02513 -0.0460 0.3919 1.0000
10.500 1.2316 0.03273 0.02625 -0.0441 0.3825 1.0000
10.750 1.2368 0.03380 0.02740 -0.0426 0.3724 1.0000
11.000 1.2203 0.03676 0.03046 -0.0405 0.3606 1.0000
11.250 1.2139 0.03924 0.03301 -0.0394 0.3483 1.0000
11.500 1.2147 0.04122 0.03503 -0.0385 0.3357 1.0000
11.750 1.2188 0.04297 0.03678 -0.0378 0.3228 1.0000
12.000 1.2227 0.04477 0.03858 -0.0371 0.3089 1.0000
12.250 1.2256 0.04672 0.04051 -0.0365 0.2945 1.0000
12.500 1.2274 0.04884 0.04260 -0.0359 0.2798 1.0000
12.750 1.2278 0.05115 0.04489 -0.0354 0.2653 1.0000
13.000 1.2273 0.05362 0.04732 -0.0351 0.2510 1.0000
13.250 1.2263 0.05623 0.04989 -0.0348 0.2371 1.0000
13.750 1.2215 0.06211 0.05573 -0.0347 0.2107 1.0000
14.000 1.2190 0.06525 0.05888 -0.0349 0.1984 1.0000
14.250 1.2169 0.06842 0.06205 -0.0352 0.1866 1.0000
14.500 1.2151 0.07163 0.06525 -0.0356 0.1753 1.0000
14.750 1.2134 0.07486 0.06845 -0.0360 0.1647 1.0000
15.000 1.2110 0.07834 0.07196 -0.0367 0.1543 1.0000
15.250 1.2095 0.08180 0.07547 -0.0374 0.1447 1.0000
15.500 1.2078 0.08529 0.07895 -0.0382 0.1358 1.0000
15.750 1.2055 0.08898 0.08267 -0.0391 0.1270 1.0000
16.000 1.2041 0.09262 0.08636 -0.0401 0.1190 1.0000
16.250 1.2017 0.09637 0.09009 -0.0412 0.1117 1.0000
16.500 1.2005 0.10014 0.09397 -0.0424 0.1044 1.0000
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Polar data table (+)
Polar graphs
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