EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 50,000 Max Cl/Cd: 27.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e520-il-50000-n5.txt Download as CSV file: xf-e520-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7438 0.10878 0.10191 -0.0153 1.0000 0.0606
-14.000 -0.7892 0.09498 0.08796 -0.0237 1.0000 0.0585
-13.750 -0.8210 0.08567 0.07842 -0.0290 1.0000 0.0578
-13.500 -0.8419 0.07900 0.07154 -0.0323 1.0000 0.0581
-13.250 -0.8577 0.07359 0.06591 -0.0344 1.0000 0.0593
-13.000 -0.8705 0.06877 0.06084 -0.0359 1.0000 0.0607
-12.750 -0.8818 0.06430 0.05606 -0.0368 1.0000 0.0627
-12.500 -0.8900 0.06024 0.05159 -0.0372 1.0000 0.0648
-12.250 -0.8786 0.05804 0.04950 -0.0369 1.0000 0.0682
-12.000 -0.8760 0.05534 0.04667 -0.0367 1.0000 0.0723
-11.750 -0.8743 0.05239 0.04329 -0.0364 1.0000 0.0771
-11.500 -0.8642 0.05042 0.04144 -0.0360 1.0000 0.0824
-11.250 -0.8552 0.04813 0.03888 -0.0354 1.0000 0.0891
-11.000 -0.8463 0.04623 0.03704 -0.0349 1.0000 0.0962
-10.750 -0.8355 0.04427 0.03492 -0.0342 1.0000 0.1052
-10.500 -0.8267 0.04248 0.03310 -0.0335 1.0000 0.1152
-10.250 -0.8173 0.04077 0.03142 -0.0327 1.0000 0.1262
-10.000 -0.8072 0.03913 0.02978 -0.0319 1.0000 0.1385
-9.750 -0.7983 0.03755 0.02822 -0.0310 1.0000 0.1527
-9.500 -0.7890 0.03606 0.02671 -0.0299 1.0000 0.1682
-9.250 -0.7806 0.03464 0.02531 -0.0288 1.0000 0.1859
-9.000 -0.7723 0.03333 0.02408 -0.0274 1.0000 0.2042
-8.750 -0.7654 0.03214 0.02300 -0.0257 1.0000 0.2234
-8.500 -0.7593 0.03107 0.02199 -0.0237 1.0000 0.2447
-8.250 -0.7540 0.03012 0.02118 -0.0214 1.0000 0.2663
-8.000 -0.7507 0.02930 0.02044 -0.0187 1.0000 0.2890
-7.750 -0.7522 0.02868 0.01995 -0.0149 1.0000 0.3092
-7.500 -0.7584 0.02821 0.01957 -0.0103 1.0000 0.3285
-7.250 -0.7644 0.02774 0.01911 -0.0056 1.0000 0.3494
-7.000 -0.7566 0.02722 0.01869 -0.0031 0.9955 0.3782
-6.750 -0.7319 0.02681 0.01839 -0.0032 0.9862 0.4151
-6.500 -0.7050 0.02661 0.01822 -0.0034 0.9783 0.4525
-6.250 -0.6746 0.02680 0.01845 -0.0035 0.9715 0.4860
-6.000 -0.6419 0.02720 0.01877 -0.0039 0.9656 0.5164
-5.750 -0.6123 0.02757 0.01902 -0.0038 0.9590 0.5432
-5.500 -0.5754 0.02820 0.01950 -0.0047 0.9543 0.5660
-5.250 -0.5491 0.02851 0.01964 -0.0043 0.9474 0.5869
-5.000 -0.5142 0.02911 0.02005 -0.0049 0.9425 0.6041
-4.750 -0.4792 0.02959 0.02035 -0.0057 0.9380 0.6206
-4.500 -0.4535 0.02993 0.02054 -0.0051 0.9314 0.6357
-4.250 -0.4216 0.03023 0.02066 -0.0057 0.9264 0.6504
-4.000 -0.3947 0.03045 0.02074 -0.0055 0.9208 0.6642
-3.750 -0.3694 0.03060 0.02076 -0.0051 0.9146 0.6775
-3.250 -0.3227 0.03071 0.02061 -0.0040 0.9027 0.7037
-3.000 -0.2894 0.03092 0.02072 -0.0047 0.8979 0.7135
-2.750 -0.2600 0.03100 0.02071 -0.0050 0.8929 0.7237
-2.500 -0.2429 0.03097 0.02059 -0.0035 0.8857 0.7351
-2.250 -0.2144 0.03094 0.02046 -0.0039 0.8808 0.7459
-2.000 -0.1898 0.03107 0.02054 -0.0033 0.8741 0.7539
-1.750 -0.1677 0.03098 0.02038 -0.0027 0.8680 0.7642
-1.500 -0.1418 0.03103 0.02037 -0.0025 0.8618 0.7727
-1.250 -0.1184 0.03102 0.02033 -0.0020 0.8551 0.7812
-1.000 -0.0982 0.03092 0.02016 -0.0012 0.8488 0.7912
-0.750 -0.0704 0.03102 0.02026 -0.0013 0.8417 0.7975
-0.500 -0.0465 0.03089 0.02009 -0.0010 0.8360 0.8068
-0.250 -0.0234 0.03101 0.02022 -0.0004 0.8278 0.8130
0.000 0.0000 0.03089 0.02007 0.0000 0.8217 0.8217
0.250 0.0234 0.03101 0.02022 0.0004 0.8131 0.8278
0.500 0.0466 0.03089 0.02009 0.0010 0.8068 0.8360
0.750 0.0705 0.03101 0.02025 0.0013 0.7975 0.8417
1.000 0.0986 0.03091 0.02015 0.0011 0.7913 0.8488
1.250 0.1186 0.03102 0.02033 0.0020 0.7811 0.8551
1.500 0.1418 0.03103 0.02037 0.0025 0.7727 0.8619
1.750 0.1677 0.03098 0.02038 0.0027 0.7643 0.8680
2.000 0.1899 0.03107 0.02054 0.0033 0.7539 0.8742
2.250 0.2151 0.03093 0.02045 0.0038 0.7462 0.8808
2.500 0.2426 0.03098 0.02060 0.0035 0.7353 0.8858
2.750 0.2598 0.03101 0.02070 0.0050 0.7238 0.8930
3.000 0.2896 0.03091 0.02072 0.0047 0.7138 0.8980
3.250 0.3226 0.03070 0.02061 0.0040 0.7037 0.9028
3.500 0.3391 0.03067 0.02068 0.0057 0.6907 0.9101
3.750 0.3696 0.03057 0.02074 0.0051 0.6775 0.9146
4.000 0.3947 0.03043 0.02072 0.0055 0.6641 0.9209
4.250 0.4217 0.03021 0.02065 0.0057 0.6504 0.9265
4.500 0.4536 0.02992 0.02053 0.0051 0.6358 0.9315
4.750 0.4791 0.02959 0.02035 0.0057 0.6207 0.9381
5.000 0.5142 0.02911 0.02005 0.0049 0.6042 0.9426
5.250 0.5490 0.02851 0.01964 0.0043 0.5869 0.9476
5.500 0.5757 0.02819 0.01949 0.0046 0.5660 0.9544
5.750 0.6125 0.02755 0.01900 0.0038 0.5431 0.9591
6.000 0.6419 0.02719 0.01876 0.0038 0.5164 0.9657
6.250 0.6748 0.02679 0.01843 0.0035 0.4860 0.9716
6.500 0.7051 0.02660 0.01821 0.0034 0.4522 0.9785
6.750 0.7321 0.02680 0.01838 0.0032 0.4148 0.9864
7.000 0.7567 0.02721 0.01868 0.0031 0.3777 0.9957
7.250 0.7642 0.02773 0.01909 0.0056 0.3495 1.0000
7.500 0.7583 0.02820 0.01956 0.0103 0.3285 1.0000
7.750 0.7521 0.02867 0.01994 0.0150 0.3091 1.0000
8.000 0.7508 0.02929 0.02043 0.0187 0.2888 1.0000
8.250 0.7543 0.03012 0.02117 0.0214 0.2660 1.0000
8.500 0.7600 0.03107 0.02198 0.0236 0.2445 1.0000
8.750 0.7663 0.03215 0.02300 0.0256 0.2232 1.0000
9.000 0.7733 0.03334 0.02408 0.0272 0.2040 1.0000
9.250 0.7817 0.03465 0.02533 0.0286 0.1855 1.0000
9.500 0.7899 0.03606 0.02672 0.0298 0.1679 1.0000
9.750 0.7994 0.03755 0.02822 0.0308 0.1525 1.0000
10.000 0.8084 0.03913 0.02979 0.0317 0.1383 1.0000
10.250 0.8184 0.04078 0.03143 0.0326 0.1259 1.0000
10.500 0.8275 0.04250 0.03313 0.0333 0.1149 1.0000
10.750 0.8370 0.04427 0.03491 0.0340 0.1051 1.0000
11.000 0.8474 0.04624 0.03705 0.0347 0.0960 1.0000
11.250 0.8568 0.04814 0.03890 0.0352 0.0890 1.0000
11.500 0.8653 0.05044 0.04145 0.0357 0.0821 1.0000
11.750 0.8753 0.05244 0.04335 0.0362 0.0769 1.0000
12.000 0.8766 0.05539 0.04671 0.0365 0.0719 1.0000
12.250 0.8802 0.05805 0.04952 0.0366 0.0681 1.0000
12.500 0.8903 0.06037 0.05175 0.0369 0.0646 1.0000
12.750 0.8825 0.06442 0.05619 0.0365 0.0625 1.0000
13.000 0.8716 0.06887 0.06095 0.0356 0.0606 1.0000
13.250 0.8588 0.07366 0.06598 0.0341 0.0591 1.0000
13.500 0.8432 0.07914 0.07169 0.0320 0.0581 1.0000
13.750 0.8228 0.08563 0.07838 0.0288 0.0575 1.0000
14.000 0.7901 0.09517 0.08817 0.0234 0.0585 1.0000
14.250 0.7448 0.10901 0.10214 0.0149 0.0606 1.0000
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