EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.76 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e520-il-1000000.txt Download as CSV file: xf-e520-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 520 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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.0801 0.11189 0.10879 -0.0002 1.0000 0.0034
-18.500 -1.0983 0.10420 0.10097 -0.0045 1.0000 0.0034
-18.250 -1.1149 0.09693 0.09358 -0.0085 1.0000 0.0034
-18.000 -1.1329 0.08961 0.08613 -0.0124 1.0000 0.0034
-17.750 -1.1469 0.08324 0.07963 -0.0157 1.0000 0.0034
-17.500 -1.1538 0.07819 0.07448 -0.0183 1.0000 0.0034
-17.250 -1.1721 0.07153 0.06767 -0.0215 1.0000 0.0034
-17.000 -1.1792 0.06684 0.06287 -0.0236 1.0000 0.0034
-16.750 -1.1899 0.06180 0.05771 -0.0257 1.0000 0.0034
-16.500 -1.2180 0.05478 0.05049 -0.0282 1.0000 0.0037
-16.250 -1.2188 0.05157 0.04719 -0.0291 1.0000 0.0036
-16.000 -1.2301 0.04733 0.04284 -0.0299 1.0000 0.0040
-15.750 -1.2319 0.04437 0.03978 -0.0303 1.0000 0.0040
-15.500 -1.2312 0.04182 0.03714 -0.0304 1.0000 0.0040
-15.250 -1.2299 0.03946 0.03469 -0.0303 1.0000 0.0039
-15.000 -1.2263 0.03744 0.03263 -0.0301 1.0000 0.0045
-14.750 -1.2257 0.03519 0.03028 -0.0296 1.0000 0.0044
-14.500 -1.2204 0.03344 0.02846 -0.0291 1.0000 0.0046
-14.250 -1.2157 0.03168 0.02661 -0.0284 1.0000 0.0047
-14.000 -1.2046 0.03049 0.02537 -0.0279 1.0000 0.0051
-13.750 -1.2026 0.02859 0.02339 -0.0268 1.0000 0.0054
-13.500 -1.1976 0.02699 0.02172 -0.0258 1.0000 0.0058
-13.250 -1.1902 0.02560 0.02030 -0.0247 1.0000 0.0063
-13.000 -1.1791 0.02452 0.01918 -0.0239 1.0000 0.0068
-12.750 -1.1678 0.02347 0.01808 -0.0230 1.0000 0.0072
-12.500 -1.1591 0.02226 0.01682 -0.0218 1.0000 0.0081
-12.250 -1.1360 0.02137 0.01569 -0.0230 0.8768 0.0094
-12.000 -1.1251 0.02070 0.01486 -0.0214 0.8510 0.0101
-11.750 -1.1157 0.01985 0.01390 -0.0197 0.8366 0.0112
-11.500 -1.1045 0.01908 0.01309 -0.0181 0.8265 0.0124
-11.250 -1.0916 0.01846 0.01239 -0.0166 0.8186 0.0134
-11.000 -1.0778 0.01789 0.01175 -0.0151 0.8117 0.0141
-10.750 -1.0680 0.01718 0.01099 -0.0129 0.8059 0.0159
-10.500 -1.0556 0.01662 0.01041 -0.0109 0.8011 0.0174
-10.250 -1.0414 0.01621 0.00994 -0.0090 0.7965 0.0185
-10.000 -1.0276 0.01575 0.00942 -0.0071 0.7923 0.0205
-9.750 -1.0101 0.01526 0.00893 -0.0058 0.7886 0.0232
-9.500 -0.9898 0.01488 0.00852 -0.0048 0.7852 0.0252
-9.250 -0.9712 0.01437 0.00802 -0.0037 0.7819 0.0302
-9.000 -0.9504 0.01398 0.00761 -0.0028 0.7788 0.0348
-8.750 -0.9297 0.01354 0.00720 -0.0020 0.7758 0.0413
-8.500 -0.9083 0.01309 0.00679 -0.0012 0.7730 0.0494
-8.250 -0.8866 0.01264 0.00639 -0.0006 0.7703 0.0604
-8.000 -0.8641 0.01223 0.00603 0.0001 0.7677 0.0718
-7.750 -0.8415 0.01183 0.00568 0.0006 0.7650 0.0855
-7.500 -0.8181 0.01149 0.00536 0.0011 0.7622 0.0988
-7.250 -0.7941 0.01111 0.00505 0.0015 0.7600 0.1140
-7.000 -0.7698 0.01075 0.00476 0.0018 0.7577 0.1310
-6.750 -0.7454 0.01039 0.00447 0.0021 0.7553 0.1494
-6.500 -0.7207 0.01005 0.00420 0.0024 0.7528 0.1693
-6.250 -0.6958 0.00971 0.00394 0.0027 0.7505 0.1919
-6.000 -0.6711 0.00937 0.00370 0.0030 0.7481 0.2195
-5.750 -0.6460 0.00901 0.00345 0.0032 0.7459 0.2491
-5.500 -0.6201 0.00869 0.00324 0.0033 0.7437 0.2761
-5.250 -0.5945 0.00835 0.00303 0.0034 0.7413 0.3074
-5.000 -0.5686 0.00802 0.00282 0.0035 0.7390 0.3399
-4.750 -0.5421 0.00775 0.00263 0.0036 0.7367 0.3690
-4.500 -0.5157 0.00748 0.00246 0.0036 0.7342 0.4021
-4.250 -0.4890 0.00724 0.00232 0.0036 0.7317 0.4350
-4.000 -0.4618 0.00698 0.00218 0.0036 0.7292 0.4652
-3.750 -0.4344 0.00676 0.00205 0.0035 0.7264 0.4948
-3.500 -0.4068 0.00656 0.00194 0.0035 0.7236 0.5240
-3.250 -0.3789 0.00641 0.00185 0.0034 0.7211 0.5489
-3.000 -0.3506 0.00634 0.00180 0.0032 0.7183 0.5703
-2.750 -0.3220 0.00626 0.00177 0.0030 0.7157 0.5883
-2.500 -0.2930 0.00619 0.00173 0.0028 0.7128 0.6030
-2.250 -0.2639 0.00615 0.00170 0.0025 0.7098 0.6154
-2.000 -0.2349 0.00612 0.00167 0.0023 0.7068 0.6261
-1.750 -0.2058 0.00612 0.00166 0.0021 0.7037 0.6347
-1.500 -0.1763 0.00612 0.00165 0.0017 0.7005 0.6431
-1.250 -0.1470 0.00609 0.00165 0.0015 0.6970 0.6497
-1.000 -0.1175 0.00609 0.00163 0.0011 0.6935 0.6564
-0.750 -0.0883 0.00609 0.00162 0.0009 0.6900 0.6620
-0.500 -0.0589 0.00611 0.00163 0.0006 0.6863 0.6676
-0.250 -0.0292 0.00611 0.00162 0.0002 0.6818 0.6728
0.000 0.0000 0.00607 0.00161 0.0000 0.6770 0.6772
0.250 0.0293 0.00610 0.00162 -0.0003 0.6724 0.6815
0.500 0.0589 0.00610 0.00162 -0.0006 0.6673 0.6859
0.750 0.0883 0.00609 0.00161 -0.0009 0.6620 0.6898
1.000 0.1176 0.00609 0.00163 -0.0012 0.6566 0.6934
1.250 0.1471 0.00609 0.00165 -0.0015 0.6499 0.6971
1.500 0.1763 0.00612 0.00165 -0.0017 0.6431 0.7006
1.750 0.2058 0.00612 0.00166 -0.0021 0.6347 0.7037
2.000 0.2349 0.00612 0.00167 -0.0023 0.6261 0.7068
2.250 0.2639 0.00615 0.00170 -0.0025 0.6155 0.7098
2.500 0.2931 0.00619 0.00173 -0.0028 0.6030 0.7129
2.750 0.3220 0.00626 0.00177 -0.0030 0.5882 0.7158
3.000 0.3506 0.00634 0.00180 -0.0032 0.5701 0.7183
3.250 0.3790 0.00641 0.00185 -0.0034 0.5490 0.7211
3.500 0.4069 0.00656 0.00194 -0.0035 0.5240 0.7237
3.750 0.4344 0.00676 0.00205 -0.0035 0.4947 0.7264
4.000 0.4618 0.00698 0.00218 -0.0036 0.4651 0.7292
4.250 0.4891 0.00723 0.00232 -0.0037 0.4353 0.7317
4.500 0.5158 0.00748 0.00246 -0.0036 0.4021 0.7342
4.750 0.5422 0.00775 0.00263 -0.0036 0.3692 0.7367
5.000 0.5687 0.00802 0.00282 -0.0035 0.3397 0.7390
5.250 0.5946 0.00835 0.00302 -0.0034 0.3074 0.7413
5.500 0.6202 0.00869 0.00324 -0.0033 0.2758 0.7437
5.750 0.6461 0.00901 0.00346 -0.0032 0.2488 0.7460
6.000 0.6713 0.00936 0.00370 -0.0030 0.2199 0.7481
6.250 0.6961 0.00970 0.00394 -0.0027 0.1924 0.7505
6.500 0.7209 0.01005 0.00420 -0.0025 0.1693 0.7528
6.750 0.7456 0.01039 0.00447 -0.0022 0.1493 0.7553
7.000 0.7700 0.01076 0.00476 -0.0019 0.1308 0.7577
7.250 0.7944 0.01111 0.00505 -0.0015 0.1138 0.7600
7.500 0.8184 0.01149 0.00536 -0.0012 0.0988 0.7622
7.750 0.8418 0.01183 0.00568 -0.0007 0.0853 0.7650
8.000 0.8646 0.01223 0.00602 -0.0001 0.0721 0.7676
8.250 0.8869 0.01266 0.00639 0.0005 0.0599 0.7703
8.500 0.9088 0.01309 0.00678 0.0011 0.0496 0.7730
8.750 0.9301 0.01355 0.00720 0.0019 0.0410 0.7758
9.000 0.9509 0.01398 0.00761 0.0027 0.0346 0.7788
9.250 0.9718 0.01437 0.00802 0.0036 0.0300 0.7819
9.500 0.9904 0.01489 0.00852 0.0047 0.0251 0.7852
9.750 1.0108 0.01526 0.00893 0.0056 0.0230 0.7886
10.000 1.0285 0.01575 0.00943 0.0069 0.0205 0.7922
10.250 1.0427 0.01621 0.00994 0.0088 0.0185 0.7964
10.500 1.0568 0.01663 0.01041 0.0107 0.0172 0.8011
10.750 1.0692 0.01718 0.01099 0.0127 0.0158 0.8059
11.000 1.0785 0.01791 0.01177 0.0149 0.0141 0.8117
11.250 1.0928 0.01845 0.01238 0.0164 0.0133 0.8185
11.500 1.1056 0.01908 0.01309 0.0179 0.0123 0.8264
11.750 1.1159 0.01990 0.01395 0.0196 0.0109 0.8366
12.000 1.1254 0.02076 0.01492 0.0213 0.0101 0.8510
12.250 1.1365 0.02141 0.01573 0.0229 0.0093 0.8768
12.500 1.1608 0.02224 0.01681 0.0215 0.0082 1.0000
12.750 1.1690 0.02349 0.01810 0.0227 0.0072 1.0000
13.000 1.1815 0.02446 0.01911 0.0236 0.0067 1.0000
13.250 1.1908 0.02567 0.02038 0.0246 0.0064 1.0000
13.500 1.2007 0.02687 0.02159 0.0254 0.0058 1.0000
13.750 1.2043 0.02859 0.02338 0.0266 0.0054 1.0000
14.000 1.2099 0.03019 0.02506 0.0274 0.0050 1.0000
14.250 1.2163 0.03177 0.02671 0.0282 0.0048 1.0000
14.500 1.2218 0.03348 0.02850 0.0288 0.0048 1.0000
14.750 1.2271 0.03524 0.03033 0.0293 0.0045 1.0000
15.000 1.2315 0.03714 0.03228 0.0297 0.0040 1.0000
15.250 1.2332 0.03936 0.03459 0.0300 0.0040 1.0000
15.500 1.2348 0.04167 0.03699 0.0301 0.0041 1.0000
15.750 1.2308 0.04471 0.04012 0.0300 0.0038 1.0000
16.000 1.2260 0.04804 0.04355 0.0295 0.0037 1.0000
16.250 1.2250 0.05108 0.04669 0.0288 0.0037 1.0000
16.500 1.2143 0.05554 0.05127 0.0276 0.0036 1.0000
16.750 1.1912 0.06194 0.05785 0.0253 0.0034 1.0000
17.000 1.1918 0.06532 0.06131 0.0239 0.0035 1.0000
17.250 1.1841 0.07008 0.06618 0.0218 0.0036 1.0000
17.500 1.1654 0.07669 0.07295 0.0187 0.0034 1.0000
17.750 1.1451 0.08391 0.08032 0.0150 0.0034 1.0000
18.000 1.1379 0.08916 0.08567 0.0123 0.0034 1.0000
18.250 1.1128 0.09769 0.09435 0.0077 0.0035 1.0000
18.500 1.0965 0.10493 0.10171 0.0038 0.0034 1.0000
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Polar data table (+)
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