EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.79 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e521-il-1000000-n5.txt Download as CSV file: xf-e521-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -1.0449 0.12926 0.12656 0.0077 1.0000 0.0017
-19.000 -1.0767 0.11819 0.11534 0.0013 1.0000 0.0016
-18.750 -1.1075 0.10769 0.10468 -0.0047 1.0000 0.0016
-18.500 -1.1307 0.09896 0.09580 -0.0096 1.0000 0.0016
-18.250 -1.1579 0.08974 0.08643 -0.0148 1.0000 0.0016
-18.000 -1.1786 0.08200 0.07854 -0.0191 1.0000 0.0015
-17.750 -1.1952 0.07525 0.07165 -0.0227 1.0000 0.0015
-17.500 -1.2102 0.06903 0.06529 -0.0259 1.0000 0.0015
-17.250 -1.2251 0.06310 0.05921 -0.0288 1.0000 0.0016
-17.000 -1.2337 0.05840 0.05440 -0.0309 1.0000 0.0016
-16.750 -1.2380 0.05452 0.05041 -0.0324 1.0000 0.0015
-16.500 -1.2468 0.05026 0.04603 -0.0337 1.0000 0.0016
-16.250 -1.2498 0.04698 0.04264 -0.0345 1.0000 0.0016
-16.000 -1.2518 0.04401 0.03957 -0.0350 1.0000 0.0016
-15.750 -1.2537 0.04121 0.03668 -0.0351 1.0000 0.0017
-15.500 -1.2544 0.03870 0.03406 -0.0350 1.0000 0.0017
-15.250 -1.2525 0.03654 0.03181 -0.0346 1.0000 0.0018
-15.000 -1.2504 0.03447 0.02966 -0.0341 1.0000 0.0018
-14.750 -1.2450 0.03279 0.02790 -0.0334 1.0000 0.0017
-14.500 -1.2400 0.03111 0.02614 -0.0326 1.0000 0.0018
-14.250 -1.2339 0.02958 0.02454 -0.0317 1.0000 0.0020
-14.000 -1.2273 0.02814 0.02302 -0.0307 1.0000 0.0020
-13.750 -1.2180 0.02693 0.02175 -0.0297 1.0000 0.0019
-13.250 -1.1995 0.02464 0.01931 -0.0275 0.9733 0.0023
-13.000 -1.1754 0.02357 0.01801 -0.0291 0.9005 0.0023
-12.750 -1.1672 0.02271 0.01700 -0.0272 0.8757 0.0024
-12.500 -1.1583 0.02181 0.01599 -0.0254 0.8619 0.0027
-12.250 -1.1477 0.02101 0.01509 -0.0237 0.8517 0.0028
-12.000 -1.1362 0.02025 0.01425 -0.0221 0.8435 0.0030
-11.750 -1.1243 0.01954 0.01347 -0.0204 0.8371 0.0035
-11.500 -1.1110 0.01891 0.01278 -0.0188 0.8317 0.0036
-11.250 -1.0977 0.01832 0.01211 -0.0170 0.8268 0.0040
-11.000 -1.0854 0.01771 0.01144 -0.0151 0.8224 0.0047
-10.750 -1.0716 0.01719 0.01088 -0.0131 0.8182 0.0052
-10.500 -1.0571 0.01674 0.01038 -0.0112 0.8142 0.0057
-10.250 -1.0410 0.01628 0.00988 -0.0096 0.8110 0.0067
-10.000 -1.0222 0.01583 0.00940 -0.0085 0.8083 0.0079
-9.750 -1.0020 0.01541 0.00895 -0.0075 0.8054 0.0088
-9.500 -0.9818 0.01497 0.00850 -0.0066 0.8025 0.0103
-9.250 -0.9602 0.01460 0.00809 -0.0058 0.7997 0.0117
-9.000 -0.9383 0.01424 0.00769 -0.0051 0.7973 0.0130
-8.750 -0.9163 0.01386 0.00729 -0.0044 0.7950 0.0148
-8.500 -0.8931 0.01352 0.00694 -0.0038 0.7928 0.0166
-8.250 -0.8706 0.01311 0.00655 -0.0032 0.7904 0.0206
-8.000 -0.8468 0.01279 0.00622 -0.0028 0.7880 0.0235
-7.750 -0.8239 0.01239 0.00584 -0.0022 0.7858 0.0303
-7.500 -0.8003 0.01203 0.00551 -0.0017 0.7836 0.0372
-7.250 -0.7769 0.01164 0.00517 -0.0012 0.7814 0.0480
-7.000 -0.7526 0.01130 0.00487 -0.0008 0.7795 0.0579
-6.750 -0.7274 0.01101 0.00461 -0.0006 0.7775 0.0661
-6.500 -0.7021 0.01072 0.00434 -0.0003 0.7753 0.0761
-6.250 -0.6770 0.01041 0.00409 0.0000 0.7730 0.0888
-6.000 -0.6515 0.01013 0.00385 0.0002 0.7709 0.1013
-5.750 -0.6259 0.00987 0.00362 0.0004 0.7688 0.1154
-5.500 -0.6008 0.00955 0.00338 0.0006 0.7667 0.1360
-5.250 -0.5748 0.00927 0.00317 0.0008 0.7647 0.1544
-5.000 -0.5487 0.00900 0.00298 0.0009 0.7625 0.1741
-4.750 -0.5225 0.00872 0.00280 0.0010 0.7600 0.1960
-4.500 -0.4959 0.00849 0.00263 0.0010 0.7575 0.2153
-4.250 -0.4695 0.00824 0.00245 0.0011 0.7548 0.2389
-4.000 -0.4429 0.00802 0.00229 0.0012 0.7521 0.2614
-3.750 -0.4160 0.00779 0.00215 0.0012 0.7493 0.2860
-3.500 -0.3888 0.00756 0.00202 0.0012 0.7460 0.3091
-3.250 -0.3619 0.00733 0.00188 0.0012 0.7425 0.3373
-3.000 -0.3349 0.00711 0.00175 0.0012 0.7391 0.3663
-2.750 -0.3078 0.00690 0.00163 0.0011 0.7358 0.3950
-2.500 -0.2803 0.00669 0.00152 0.0011 0.7318 0.4242
-2.250 -0.2528 0.00649 0.00142 0.0010 0.7275 0.4536
-2.000 -0.2254 0.00630 0.00132 0.0010 0.7233 0.4832
-1.750 -0.1977 0.00611 0.00123 0.0009 0.7189 0.5142
-1.500 -0.1701 0.00593 0.00116 0.0008 0.7137 0.5458
-1.250 -0.1424 0.00578 0.00109 0.0008 0.7086 0.5764
-1.000 -0.1142 0.00565 0.00106 0.0006 0.7029 0.6027
-0.750 -0.0859 0.00557 0.00103 0.0005 0.6961 0.6241
-0.500 -0.0573 0.00551 0.00101 0.0003 0.6885 0.6419
-0.250 -0.0288 0.00549 0.00100 0.0002 0.6794 0.6563
0.000 0.0000 0.00547 0.00100 0.0000 0.6687 0.6687
0.250 0.0288 0.00549 0.00100 -0.0002 0.6564 0.6794
0.500 0.0574 0.00551 0.00101 -0.0003 0.6417 0.6885
0.750 0.0859 0.00557 0.00103 -0.0005 0.6244 0.6961
1.000 0.1142 0.00565 0.00106 -0.0006 0.6026 0.7029
1.250 0.1424 0.00578 0.00109 -0.0008 0.5763 0.7086
1.500 0.1701 0.00593 0.00116 -0.0008 0.5460 0.7137
1.750 0.1978 0.00611 0.00123 -0.0009 0.5141 0.7189
2.000 0.2254 0.00630 0.00132 -0.0010 0.4831 0.7233
2.250 0.2529 0.00648 0.00142 -0.0010 0.4538 0.7275
2.500 0.2803 0.00669 0.00152 -0.0011 0.4241 0.7318
2.750 0.3077 0.00690 0.00163 -0.0011 0.3946 0.7358
3.000 0.3349 0.00711 0.00175 -0.0012 0.3665 0.7391
3.250 0.3619 0.00733 0.00188 -0.0012 0.3375 0.7425
3.500 0.3888 0.00756 0.00202 -0.0012 0.3090 0.7460
3.750 0.4160 0.00779 0.00215 -0.0012 0.2861 0.7493
4.000 0.4429 0.00802 0.00229 -0.0012 0.2615 0.7521
4.250 0.4695 0.00824 0.00245 -0.0011 0.2390 0.7548
4.500 0.4959 0.00849 0.00263 -0.0010 0.2157 0.7575
4.750 0.5225 0.00872 0.00280 -0.0010 0.1962 0.7600
5.000 0.5486 0.00900 0.00298 -0.0009 0.1740 0.7625
5.250 0.5747 0.00927 0.00317 -0.0008 0.1542 0.7647
5.500 0.6006 0.00955 0.00339 -0.0006 0.1354 0.7667
5.750 0.6258 0.00986 0.00362 -0.0004 0.1155 0.7688
6.000 0.6514 0.01013 0.00385 -0.0002 0.1014 0.7709
6.250 0.6769 0.01041 0.00408 0.0001 0.0888 0.7730
6.750 0.7272 0.01101 0.00461 0.0006 0.0662 0.7775
7.000 0.7525 0.01130 0.00487 0.0008 0.0579 0.7795
7.250 0.7768 0.01163 0.00517 0.0012 0.0484 0.7814
7.500 0.8004 0.01200 0.00550 0.0017 0.0385 0.7836
7.750 0.8235 0.01240 0.00585 0.0022 0.0297 0.7858
8.000 0.8466 0.01279 0.00622 0.0028 0.0235 0.7880
8.250 0.8703 0.01311 0.00655 0.0033 0.0203 0.7905
8.500 0.8928 0.01352 0.00694 0.0039 0.0165 0.7929
8.750 0.9160 0.01386 0.00729 0.0044 0.0147 0.7951
9.000 0.9380 0.01424 0.00769 0.0051 0.0129 0.7973
9.250 0.9599 0.01460 0.00808 0.0059 0.0115 0.7997
9.500 0.9815 0.01497 0.00850 0.0067 0.0104 0.8025
9.750 1.0017 0.01540 0.00895 0.0076 0.0089 0.8055
10.000 1.0218 0.01582 0.00939 0.0086 0.0079 0.8083
10.250 1.0408 0.01627 0.00987 0.0097 0.0068 0.8110
10.500 1.0568 0.01673 0.01037 0.0113 0.0059 0.8143
10.750 1.0712 0.01718 0.01087 0.0132 0.0052 0.8183
11.000 1.0848 0.01771 0.01144 0.0152 0.0046 0.8225
11.250 1.0970 0.01833 0.01211 0.0172 0.0038 0.8269
11.500 1.1107 0.01890 0.01277 0.0188 0.0039 0.8318
11.750 1.1238 0.01954 0.01347 0.0205 0.0035 0.8372
12.000 1.1362 0.02022 0.01423 0.0221 0.0032 0.8436
12.250 1.1480 0.02096 0.01505 0.0237 0.0029 0.8518
12.500 1.1590 0.02173 0.01591 0.0254 0.0028 0.8620
12.750 1.1663 0.02274 0.01704 0.0273 0.0023 0.8765
13.000 1.1752 0.02354 0.01799 0.0292 0.0023 0.9023
13.250 1.2005 0.02459 0.01926 0.0273 0.0021 0.9805
13.500 1.2095 0.02568 0.02041 0.0286 0.0021 1.0000
13.750 1.2181 0.02690 0.02171 0.0298 0.0020 1.0000
14.000 1.2265 0.02817 0.02306 0.0308 0.0021 1.0000
14.250 1.2342 0.02953 0.02448 0.0318 0.0019 1.0000
14.500 1.2401 0.03106 0.02609 0.0327 0.0018 1.0000
14.750 1.2452 0.03273 0.02784 0.0335 0.0018 1.0000
15.000 1.2496 0.03450 0.02969 0.0342 0.0018 1.0000
15.250 1.2515 0.03658 0.03186 0.0347 0.0017 1.0000
15.500 1.2547 0.03862 0.03399 0.0350 0.0018 1.0000
15.750 1.2559 0.04093 0.03638 0.0352 0.0017 1.0000
16.000 1.2538 0.04373 0.03927 0.0350 0.0016 1.0000
16.250 1.2515 0.04673 0.04240 0.0346 0.0017 1.0000
16.500 1.2492 0.04992 0.04568 0.0339 0.0017 1.0000
16.750 1.2410 0.05406 0.04993 0.0326 0.0016 1.0000
17.000 1.2367 0.05791 0.05390 0.0311 0.0016 1.0000
17.250 1.2261 0.06290 0.05902 0.0289 0.0016 1.0000
17.500 1.2132 0.06850 0.06476 0.0262 0.0016 1.0000
17.750 1.1969 0.07492 0.07132 0.0229 0.0016 1.0000
18.000 1.1808 0.08159 0.07813 0.0193 0.0016 1.0000
18.250 1.1606 0.08921 0.08589 0.0150 0.0016 1.0000
18.500 1.1340 0.09830 0.09513 0.0099 0.0016 1.0000
18.750 1.1044 0.10830 0.10529 0.0043 0.0016 1.0000
19.000 1.0740 0.11875 0.11590 -0.0017 0.0016 1.0000
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Polar data table (+)
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