EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 1,000,000 Max Cl/Cd: 70 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e521-il-1000000.txt Download as CSV file: xf-e521-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0606 0.09934 0.09639 -0.0096 1.0000 0.0030
-17.500 -1.0799 0.09144 0.08837 -0.0140 1.0000 0.0030
-17.250 -1.1024 0.08324 0.08001 -0.0185 1.0000 0.0030
-17.000 -1.1178 0.07653 0.07317 -0.0221 1.0000 0.0030
-16.750 -1.1315 0.07038 0.06688 -0.0253 1.0000 0.0030
-16.500 -1.1472 0.06414 0.06050 -0.0285 1.0000 0.0030
-16.250 -1.1588 0.05887 0.05509 -0.0308 1.0000 0.0030
-16.000 -1.1672 0.05435 0.05045 -0.0327 1.0000 0.0030
-15.750 -1.1727 0.05045 0.04644 -0.0340 1.0000 0.0031
-15.500 -1.1801 0.04660 0.04247 -0.0349 1.0000 0.0031
-15.250 -1.1848 0.04332 0.03907 -0.0354 1.0000 0.0031
-15.000 -1.1895 0.04026 0.03590 -0.0355 1.0000 0.0032
-14.750 -1.1900 0.03779 0.03333 -0.0352 1.0000 0.0031
-14.500 -1.1901 0.03547 0.03090 -0.0348 1.0000 0.0032
-14.250 -1.1889 0.03338 0.02872 -0.0341 1.0000 0.0033
-14.000 -1.1870 0.03141 0.02664 -0.0332 1.0000 0.0033
-13.750 -1.1836 0.02967 0.02481 -0.0321 1.0000 0.0033
-13.500 -1.1776 0.02817 0.02322 -0.0310 1.0000 0.0035
-13.250 -1.1699 0.02683 0.02181 -0.0299 1.0000 0.0037
-13.000 -1.1639 0.02542 0.02032 -0.0286 1.0000 0.0037
-12.750 -1.1545 0.02430 0.01912 -0.0274 1.0000 0.0038
-12.500 -1.1509 0.02280 0.01752 -0.0255 1.0000 0.0040
-12.250 -1.1454 0.02146 0.01609 -0.0237 1.0000 0.0043
-12.000 -1.1353 0.02046 0.01504 -0.0221 1.0000 0.0046
-11.750 -1.1133 0.01962 0.01415 -0.0227 0.9567 0.0054
-11.500 -1.0967 0.01896 0.01328 -0.0218 0.9052 0.0056
-11.250 -1.0899 0.01818 0.01235 -0.0191 0.8865 0.0066
-11.000 -1.0788 0.01758 0.01169 -0.0168 0.8757 0.0077
-10.500 -1.0548 0.01649 0.01048 -0.0123 0.8612 0.0103
-10.250 -1.0379 0.01610 0.01003 -0.0108 0.8560 0.0116
-10.000 -1.0203 0.01560 0.00948 -0.0094 0.8515 0.0135
-9.750 -1.0010 0.01514 0.00902 -0.0084 0.8473 0.0153
-9.500 -0.9796 0.01480 0.00863 -0.0076 0.8435 0.0166
-9.250 -0.9602 0.01431 0.00810 -0.0065 0.8400 0.0196
-9.000 -0.9384 0.01393 0.00771 -0.0057 0.8369 0.0219
-8.750 -0.9162 0.01354 0.00730 -0.0050 0.8337 0.0251
-8.500 -0.8942 0.01313 0.00690 -0.0043 0.8306 0.0294
-8.250 -0.8719 0.01273 0.00651 -0.0037 0.8277 0.0358
-8.000 -0.8488 0.01239 0.00617 -0.0031 0.8250 0.0424
-7.750 -0.8259 0.01198 0.00581 -0.0025 0.8224 0.0535
-7.500 -0.8024 0.01159 0.00547 -0.0020 0.8198 0.0646
-7.250 -0.7793 0.01117 0.00514 -0.0015 0.8172 0.0807
-7.000 -0.7554 0.01080 0.00484 -0.0011 0.8147 0.0963
-6.750 -0.7310 0.01047 0.00456 -0.0007 0.8122 0.1115
-6.500 -0.7063 0.01019 0.00431 -0.0004 0.8097 0.1281
-6.250 -0.6814 0.00985 0.00405 -0.0001 0.8076 0.1477
-6.000 -0.6561 0.00953 0.00382 0.0001 0.8052 0.1679
-5.750 -0.6307 0.00923 0.00360 0.0003 0.8027 0.1891
-5.500 -0.6056 0.00890 0.00338 0.0006 0.8002 0.2169
-5.250 -0.5800 0.00861 0.00317 0.0008 0.7980 0.2440
-5.000 -0.5545 0.00833 0.00299 0.0010 0.7954 0.2732
-4.750 -0.5287 0.00802 0.00280 0.0011 0.7932 0.3047
-4.500 -0.5025 0.00773 0.00263 0.0012 0.7905 0.3355
-4.250 -0.4764 0.00744 0.00246 0.0014 0.7877 0.3694
-4.000 -0.4499 0.00719 0.00231 0.0015 0.7849 0.4023
-3.750 -0.4236 0.00694 0.00216 0.0016 0.7822 0.4366
-3.500 -0.3968 0.00671 0.00204 0.0016 0.7793 0.4695
-3.250 -0.3699 0.00646 0.00191 0.0017 0.7763 0.5062
-3.000 -0.3432 0.00620 0.00180 0.0017 0.7730 0.5439
-2.750 -0.3160 0.00601 0.00170 0.0018 0.7698 0.5783
-2.500 -0.2885 0.00589 0.00164 0.0018 0.7667 0.6079
-2.250 -0.2604 0.00577 0.00161 0.0017 0.7634 0.6321
-2.000 -0.2318 0.00570 0.00157 0.0016 0.7597 0.6510
-1.750 -0.2032 0.00565 0.00154 0.0014 0.7560 0.6663
-1.500 -0.1744 0.00564 0.00152 0.0013 0.7525 0.6792
-1.250 -0.1455 0.00562 0.00153 0.0011 0.7488 0.6897
-1.000 -0.1164 0.00559 0.00152 0.0009 0.7445 0.6983
-0.750 -0.0873 0.00559 0.00150 0.0006 0.7403 0.7065
-0.500 -0.0584 0.00559 0.00150 0.0005 0.7358 0.7130
-0.250 -0.0291 0.00558 0.00150 0.0002 0.7305 0.7195
0.000 0.0000 0.00558 0.00148 0.0000 0.7251 0.7251
0.250 0.0291 0.00558 0.00150 -0.0002 0.7196 0.7305
0.500 0.0584 0.00559 0.00150 -0.0005 0.7129 0.7358
0.750 0.0873 0.00559 0.00150 -0.0007 0.7066 0.7403
1.000 0.1164 0.00559 0.00152 -0.0009 0.6983 0.7445
1.250 0.1455 0.00562 0.00153 -0.0011 0.6897 0.7488
1.500 0.1744 0.00564 0.00152 -0.0013 0.6792 0.7525
1.750 0.2032 0.00565 0.00154 -0.0014 0.6663 0.7560
2.250 0.2604 0.00577 0.00161 -0.0017 0.6322 0.7634
2.500 0.2885 0.00589 0.00164 -0.0018 0.6080 0.7667
2.750 0.3160 0.00601 0.00170 -0.0018 0.5782 0.7698
3.000 0.3432 0.00620 0.00180 -0.0017 0.5439 0.7730
3.250 0.3700 0.00645 0.00191 -0.0017 0.5064 0.7762
3.500 0.3968 0.00671 0.00204 -0.0016 0.4695 0.7793
3.750 0.4236 0.00693 0.00216 -0.0016 0.4367 0.7822
4.000 0.4499 0.00719 0.00231 -0.0015 0.4023 0.7849
4.250 0.4764 0.00744 0.00246 -0.0014 0.3696 0.7877
4.500 0.5025 0.00772 0.00263 -0.0013 0.3359 0.7905
4.750 0.5287 0.00802 0.00280 -0.0011 0.3048 0.7932
5.000 0.5545 0.00833 0.00299 -0.0010 0.2731 0.7954
5.250 0.5799 0.00861 0.00317 -0.0008 0.2438 0.7980
5.500 0.6054 0.00890 0.00338 -0.0006 0.2165 0.8003
5.750 0.6306 0.00923 0.00360 -0.0003 0.1892 0.8027
6.000 0.6561 0.00953 0.00382 -0.0001 0.1680 0.8052
6.250 0.6813 0.00984 0.00405 0.0001 0.1477 0.8076
6.500 0.7062 0.01019 0.00431 0.0004 0.1283 0.8097
6.750 0.7309 0.01047 0.00456 0.0007 0.1115 0.8122
7.000 0.7553 0.01079 0.00484 0.0011 0.0964 0.8147
7.250 0.7792 0.01116 0.00514 0.0015 0.0810 0.8172
7.500 0.8025 0.01157 0.00546 0.0020 0.0662 0.8198
7.750 0.8256 0.01199 0.00581 0.0026 0.0527 0.8224
8.000 0.8485 0.01239 0.00617 0.0031 0.0424 0.8250
8.250 0.8716 0.01273 0.00651 0.0037 0.0355 0.8278
8.500 0.8939 0.01313 0.00690 0.0044 0.0293 0.8306
8.750 0.9159 0.01354 0.00730 0.0051 0.0249 0.8338
9.000 0.9382 0.01393 0.00771 0.0058 0.0219 0.8369
9.250 0.9599 0.01431 0.00810 0.0065 0.0195 0.8400
9.500 0.9793 0.01480 0.00863 0.0076 0.0166 0.8435
9.750 1.0007 0.01513 0.00901 0.0084 0.0153 0.8474
10.000 1.0200 0.01559 0.00948 0.0095 0.0136 0.8516
10.250 1.0374 0.01610 0.01004 0.0109 0.0117 0.8561
10.500 1.0542 0.01648 0.01048 0.0125 0.0104 0.8613
11.000 1.0785 0.01757 0.01168 0.0169 0.0077 0.8760
11.250 1.0894 0.01818 0.01235 0.0191 0.0064 0.8869
11.500 1.0982 0.01886 0.01317 0.0216 0.0062 0.9053
11.750 1.1138 0.01960 0.01414 0.0226 0.0053 0.9579
12.000 1.1349 0.02045 0.01505 0.0222 0.0048 1.0000
12.250 1.1459 0.02138 0.01602 0.0236 0.0045 1.0000
12.500 1.1558 0.02241 0.01711 0.0251 0.0043 1.0000
12.750 1.1563 0.02414 0.01895 0.0273 0.0037 1.0000
13.000 1.1642 0.02536 0.02025 0.0286 0.0037 1.0000
13.250 1.1721 0.02664 0.02161 0.0298 0.0035 1.0000
13.500 1.1783 0.02808 0.02313 0.0311 0.0034 1.0000
13.750 1.1829 0.02968 0.02483 0.0322 0.0034 1.0000
14.000 1.1865 0.03142 0.02666 0.0332 0.0034 1.0000
14.250 1.1903 0.03322 0.02855 0.0340 0.0033 1.0000
14.500 1.1907 0.03539 0.03083 0.0348 0.0032 1.0000
14.750 1.1909 0.03768 0.03321 0.0352 0.0031 1.0000
15.000 1.1897 0.04022 0.03586 0.0355 0.0031 1.0000
15.250 1.1840 0.04339 0.03915 0.0354 0.0031 1.0000
15.500 1.1824 0.04631 0.04217 0.0350 0.0031 1.0000
15.750 1.1773 0.04985 0.04582 0.0341 0.0030 1.0000
16.000 1.1695 0.05401 0.05010 0.0328 0.0030 1.0000
16.250 1.1581 0.05894 0.05518 0.0308 0.0031 1.0000
16.500 1.1492 0.06382 0.06018 0.0286 0.0030 1.0000
16.750 1.1349 0.06984 0.06633 0.0256 0.0030 1.0000
17.000 1.1203 0.07612 0.07275 0.0223 0.0030 1.0000
17.250 1.1036 0.08306 0.07983 0.0185 0.0030 1.0000
17.500 1.0843 0.09068 0.08758 0.0144 0.0030 1.0000
17.750 1.0618 0.09912 0.09617 0.0097 0.0031 1.0000
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Polar data table (+)
Polar graphs
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