E205 (10.48%) (e205-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 500,000 Max Cl/Cd: 105.4 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e205-il-500000.txt Download as CSV file: xf-e205-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4084 0.08542 0.08324 -0.0297 1.0000 0.0226
-8.750 -0.4084 0.08184 0.07969 -0.0313 1.0000 0.0235
-8.500 -0.4113 0.07786 0.07575 -0.0333 1.0000 0.0240
-8.250 -0.4167 0.07389 0.07182 -0.0354 1.0000 0.0242
-8.000 -0.4313 0.06946 0.06744 -0.0380 1.0000 0.0248
-7.000 -0.4376 0.04174 0.03910 -0.0544 0.9885 0.0283
-6.750 -0.4077 0.03910 0.03634 -0.0578 0.9820 0.0293
-6.500 -0.3792 0.03589 0.03293 -0.0607 0.9714 0.0311
-6.000 -0.3456 0.01950 0.01445 -0.0596 0.9296 0.0208
-5.750 -0.3179 0.01822 0.01289 -0.0593 0.9041 0.0204
-5.500 -0.2941 0.01683 0.01120 -0.0584 0.8756 0.0204
-5.250 -0.2721 0.01517 0.00925 -0.0572 0.8488 0.0209
-5.000 -0.2487 0.01414 0.00798 -0.0561 0.8241 0.0210
-4.750 -0.2249 0.01328 0.00692 -0.0551 0.8013 0.0211
-4.250 -0.1769 0.01192 0.00528 -0.0533 0.7628 0.0223
-4.000 -0.1521 0.01147 0.00469 -0.0525 0.7460 0.0231
-3.750 -0.1269 0.01108 0.00419 -0.0519 0.7308 0.0240
-3.500 -0.1013 0.01074 0.00374 -0.0513 0.7170 0.0250
-3.250 -0.0752 0.01051 0.00339 -0.0508 0.7043 0.0265
-2.750 -0.0231 0.00989 0.00261 -0.0498 0.6815 0.0366
-2.500 0.0019 0.00937 0.00233 -0.0493 0.6714 0.0990
-2.250 0.0275 0.00908 0.00218 -0.0489 0.6622 0.1567
-2.000 0.0532 0.00876 0.00206 -0.0486 0.6530 0.2252
-1.750 0.0782 0.00839 0.00198 -0.0482 0.6446 0.3201
-1.500 0.1030 0.00805 0.00191 -0.0477 0.6364 0.4169
-1.250 0.1263 0.00759 0.00187 -0.0469 0.6288 0.5482
-1.000 0.1461 0.00703 0.00186 -0.0452 0.6217 0.7173
-0.750 0.1694 0.00661 0.00194 -0.0436 0.6147 0.8733
-0.500 0.2264 0.00674 0.00205 -0.0493 0.6067 0.9588
-0.250 0.2728 0.00686 0.00208 -0.0530 0.5994 0.9783
0.000 0.3202 0.00695 0.00206 -0.0572 0.5919 0.9886
0.250 0.3696 0.00699 0.00202 -0.0619 0.5846 0.9970
0.500 0.4056 0.00703 0.00197 -0.0637 0.5779 1.0000
0.750 0.4304 0.00708 0.00196 -0.0631 0.5718 1.0000
1.000 0.4552 0.00712 0.00196 -0.0625 0.5655 1.0000
1.250 0.4800 0.00721 0.00197 -0.0619 0.5597 1.0000
1.500 0.5051 0.00725 0.00200 -0.0613 0.5533 1.0000
1.750 0.5301 0.00733 0.00203 -0.0607 0.5476 1.0000
2.000 0.5552 0.00740 0.00208 -0.0602 0.5415 1.0000
2.250 0.5803 0.00747 0.00213 -0.0596 0.5354 1.0000
2.500 0.6053 0.00758 0.00220 -0.0590 0.5295 1.0000
2.750 0.6305 0.00764 0.00226 -0.0585 0.5226 1.0000
3.000 0.6554 0.00776 0.00233 -0.0578 0.5162 1.0000
3.250 0.6806 0.00781 0.00241 -0.0573 0.5087 1.0000
3.500 0.7054 0.00794 0.00249 -0.0567 0.5017 1.0000
3.750 0.7306 0.00799 0.00258 -0.0561 0.4939 1.0000
4.000 0.7554 0.00812 0.00267 -0.0555 0.4866 1.0000
4.250 0.7805 0.00819 0.00279 -0.0549 0.4782 1.0000
4.500 0.8053 0.00831 0.00290 -0.0543 0.4705 1.0000
4.750 0.8300 0.00841 0.00301 -0.0537 0.4615 1.0000
5.000 0.8549 0.00852 0.00314 -0.0531 0.4523 1.0000
5.250 0.8793 0.00866 0.00329 -0.0524 0.4430 1.0000
5.500 0.9038 0.00879 0.00343 -0.0518 0.4323 1.0000
5.750 0.9283 0.00892 0.00359 -0.0511 0.4209 1.0000
6.000 0.9524 0.00908 0.00375 -0.0504 0.4075 1.0000
6.250 0.9760 0.00926 0.00394 -0.0496 0.3915 1.0000
6.500 0.9989 0.00950 0.00414 -0.0487 0.3706 1.0000
6.750 1.0208 0.00982 0.00438 -0.0477 0.3430 1.0000
7.000 1.0413 0.01026 0.00468 -0.0465 0.3054 1.0000
7.250 1.0592 0.01093 0.00513 -0.0450 0.2571 1.0000
7.500 1.0762 0.01169 0.00566 -0.0434 0.2106 1.0000
7.750 1.0927 0.01250 0.00625 -0.0418 0.1690 1.0000
8.000 1.1092 0.01330 0.00686 -0.0402 0.1339 1.0000
8.250 1.1258 0.01407 0.00748 -0.0386 0.1032 1.0000
8.500 1.1419 0.01485 0.00813 -0.0370 0.0777 1.0000
8.750 1.1573 0.01566 0.00882 -0.0352 0.0557 1.0000
9.000 1.1673 0.01681 0.00976 -0.0328 0.0277 1.0000
9.250 1.1769 0.01794 0.01081 -0.0301 0.0159 1.0000
9.500 1.1909 0.01870 0.01164 -0.0281 0.0137 1.0000
9.750 1.2026 0.01951 0.01251 -0.0258 0.0127 1.0000
10.000 1.2060 0.02057 0.01366 -0.0222 0.0116 1.0000
10.250 1.2133 0.02145 0.01465 -0.0194 0.0112 1.0000
10.500 1.2193 0.02248 0.01577 -0.0168 0.0109 1.0000
10.750 1.2241 0.02367 0.01706 -0.0143 0.0106 1.0000
11.000 1.2272 0.02508 0.01856 -0.0120 0.0102 1.0000
11.250 1.2335 0.02639 0.01993 -0.0104 0.0096 1.0000
11.500 1.2343 0.02825 0.02189 -0.0087 0.0093 1.0000
11.750 1.2361 0.03020 0.02393 -0.0075 0.0093 1.0000
12.000 1.2341 0.03262 0.02644 -0.0064 0.0089 1.0000
12.250 1.2259 0.03580 0.02973 -0.0053 0.0087 1.0000
12.500 1.2240 0.03850 0.03253 -0.0046 0.0086 1.0000
12.750 1.2225 0.04121 0.03534 -0.0039 0.0085 1.0000
13.000 1.2269 0.04340 0.03766 -0.0037 0.0084 1.0000
13.250 1.2285 0.04594 0.04031 -0.0033 0.0083 1.0000
13.500 1.2304 0.04846 0.04294 -0.0032 0.0083 1.0000
13.750 1.2294 0.05134 0.04593 -0.0027 0.0083 1.0000
14.000 1.2311 0.05404 0.04875 -0.0028 0.0081 1.0000
14.250 1.2309 0.05698 0.05180 -0.0028 0.0081 1.0000
14.500 1.2304 0.06009 0.05505 -0.0031 0.0080 1.0000
14.750 1.2287 0.06340 0.05849 -0.0033 0.0081 1.0000
15.000 1.2262 0.06698 0.06222 -0.0040 0.0079 1.0000
15.250 1.2225 0.07084 0.06623 -0.0048 0.0078 1.0000
15.500 1.2177 0.07496 0.07050 -0.0060 0.0077 1.0000
15.750 1.2111 0.07948 0.07518 -0.0072 0.0079 1.0000
16.000 1.2029 0.08446 0.08033 -0.0091 0.0078 1.0000
16.250 1.1931 0.08986 0.08590 -0.0112 0.0078 1.0000
16.500 1.1821 0.09566 0.09186 -0.0137 0.0079 1.0000
16.750 1.1691 0.10210 0.09849 -0.0168 0.0079 1.0000
17.000 1.1556 0.10882 0.10537 -0.0202 0.0079 1.0000
17.250 1.1409 0.11611 0.11283 -0.0241 0.0079 1.0000
17.500 1.1243 0.12412 0.12102 -0.0287 0.0079 1.0000
17.750 1.1077 0.13243 0.12948 -0.0335 0.0080 1.0000
18.000 1.0911 0.14102 0.13821 -0.0386 0.0081 1.0000
18.250 1.0738 0.15024 0.14758 -0.0442 0.0082 1.0000
18.500 1.0556 0.16018 0.15765 -0.0503 0.0083 1.0000
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