EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Reynolds number: 100,000 Max Cl/Cd: 29.11 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea61012-il-100000-n5.txt Download as CSV file: xf-ea61012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-012 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7863 0.09461 0.08884 -0.0143 1.0000 0.0587
-12.750 -0.8539 0.07852 0.07257 -0.0259 1.0000 0.0580
-12.500 -0.8967 0.07006 0.06389 -0.0307 1.0000 0.0578
-12.250 -0.9289 0.06421 0.05781 -0.0326 1.0000 0.0578
-12.000 -0.9557 0.05967 0.05301 -0.0328 1.0000 0.0580
-11.750 -0.9797 0.05602 0.04908 -0.0313 1.0000 0.0584
-11.500 -0.9993 0.05302 0.04577 -0.0285 1.0000 0.0590
-11.250 -1.0124 0.05004 0.04237 -0.0260 1.0000 0.0597
-11.000 -1.0063 0.04764 0.03983 -0.0249 1.0000 0.0606
-10.750 -0.9943 0.04577 0.03786 -0.0240 1.0000 0.0615
-10.500 -0.9831 0.04383 0.03576 -0.0229 1.0000 0.0623
-10.250 -0.9707 0.04188 0.03360 -0.0218 1.0000 0.0632
-10.000 -0.9573 0.03998 0.03148 -0.0208 1.0000 0.0641
-9.750 -0.9425 0.03816 0.02943 -0.0197 1.0000 0.0652
-9.500 -0.9269 0.03651 0.02751 -0.0187 1.0000 0.0668
-9.250 -0.9105 0.03494 0.02562 -0.0176 1.0000 0.0684
-9.000 -0.8913 0.03340 0.02384 -0.0168 1.0000 0.0695
-8.750 -0.8686 0.03191 0.02232 -0.0165 1.0000 0.0705
-8.500 -0.8461 0.03064 0.02100 -0.0161 1.0000 0.0716
-8.250 -0.8234 0.02946 0.01976 -0.0156 1.0000 0.0728
-8.000 -0.8005 0.02835 0.01857 -0.0151 1.0000 0.0741
-7.750 -0.7774 0.02730 0.01743 -0.0146 1.0000 0.0755
-7.500 -0.7545 0.02638 0.01640 -0.0140 1.0000 0.0775
-7.250 -0.7318 0.02553 0.01545 -0.0134 1.0000 0.0795
-7.000 -0.7097 0.02456 0.01459 -0.0128 1.0000 0.0814
-6.750 -0.6885 0.02376 0.01382 -0.0120 1.0000 0.0833
-6.500 -0.6685 0.02302 0.01311 -0.0110 1.0000 0.0850
-6.250 -0.6513 0.02237 0.01246 -0.0095 1.0000 0.0869
-6.000 -0.6248 0.02168 0.01173 -0.0098 0.9880 0.0892
-5.750 -0.5925 0.02089 0.01094 -0.0113 0.9723 0.0920
-5.500 -0.5603 0.02016 0.01025 -0.0128 0.9592 0.0956
-5.250 -0.5281 0.01958 0.00963 -0.0141 0.9476 0.1011
-5.000 -0.4971 0.01893 0.00902 -0.0152 0.9371 0.1083
-4.750 -0.4662 0.01838 0.00846 -0.0162 0.9281 0.1180
-4.500 -0.4389 0.01777 0.00797 -0.0165 0.9188 0.1329
-4.250 -0.4118 0.01709 0.00748 -0.0168 0.9112 0.1657
-4.000 -0.3896 0.01631 0.00706 -0.0163 0.9022 0.2307
-3.750 -0.3685 0.01542 0.00671 -0.0156 0.8947 0.3369
-3.500 -0.3493 0.01476 0.00651 -0.0142 0.8864 0.4316
-3.250 -0.3282 0.01448 0.00681 -0.0124 0.8800 0.5408
-3.000 -0.3035 0.01453 0.00695 -0.0114 0.8739 0.5965
-2.750 -0.2783 0.01466 0.00711 -0.0104 0.8678 0.6323
-2.500 -0.2527 0.01492 0.00741 -0.0092 0.8626 0.6683
-2.250 -0.2288 0.01529 0.00782 -0.0077 0.8562 0.6994
-2.000 -0.2044 0.01563 0.00815 -0.0062 0.8506 0.7243
-1.750 -0.1786 0.01595 0.00847 -0.0049 0.8465 0.7433
-1.500 -0.1541 0.01611 0.00861 -0.0039 0.8406 0.7570
-1.250 -0.1283 0.01616 0.00862 -0.0033 0.8352 0.7662
-1.000 -0.1012 0.01617 0.00858 -0.0028 0.8305 0.7727
-0.750 -0.0761 0.01619 0.00858 -0.0023 0.8233 0.7796
-0.500 -0.0503 0.01617 0.00851 -0.0017 0.8167 0.7864
-0.250 -0.0251 0.01618 0.00854 -0.0009 0.8086 0.7932
0.000 0.0000 0.01617 0.00850 0.0000 0.8015 0.8015
0.250 0.0251 0.01618 0.00854 0.0009 0.7932 0.8086
0.500 0.0503 0.01617 0.00851 0.0017 0.7864 0.8167
0.750 0.0761 0.01619 0.00858 0.0023 0.7796 0.8233
1.000 0.1012 0.01617 0.00858 0.0028 0.7728 0.8305
1.250 0.1283 0.01616 0.00862 0.0033 0.7662 0.8352
1.500 0.1541 0.01611 0.00862 0.0039 0.7570 0.8406
1.750 0.1786 0.01595 0.00847 0.0049 0.7433 0.8465
2.000 0.2044 0.01563 0.00816 0.0062 0.7244 0.8506
2.250 0.2288 0.01529 0.00782 0.0077 0.6995 0.8562
2.500 0.2527 0.01492 0.00742 0.0092 0.6685 0.8626
2.750 0.2783 0.01466 0.00711 0.0104 0.6323 0.8678
3.000 0.3035 0.01453 0.00695 0.0114 0.5966 0.8739
3.250 0.3282 0.01448 0.00682 0.0124 0.5410 0.8800
3.500 0.3493 0.01476 0.00651 0.0142 0.4312 0.8864
3.750 0.3686 0.01542 0.00671 0.0156 0.3377 0.8947
4.000 0.3896 0.01630 0.00706 0.0163 0.2312 0.9022
4.500 0.4390 0.01777 0.00796 0.0165 0.1329 0.9188
4.750 0.4662 0.01838 0.00846 0.0162 0.1181 0.9281
5.000 0.4972 0.01893 0.00902 0.0152 0.1084 0.9372
5.250 0.5281 0.01958 0.00963 0.0141 0.1012 0.9476
5.500 0.5603 0.02016 0.01025 0.0128 0.0956 0.9592
5.750 0.5925 0.02088 0.01094 0.0113 0.0920 0.9724
6.000 0.6248 0.02168 0.01173 0.0098 0.0892 0.9881
6.250 0.6512 0.02237 0.01246 0.0095 0.0869 1.0000
6.500 0.6685 0.02302 0.01310 0.0110 0.0851 1.0000
6.750 0.6885 0.02376 0.01382 0.0120 0.0833 1.0000
7.000 0.7098 0.02455 0.01458 0.0128 0.0814 1.0000
7.250 0.7318 0.02553 0.01545 0.0134 0.0795 1.0000
7.500 0.7546 0.02638 0.01640 0.0140 0.0774 1.0000
7.750 0.7775 0.02730 0.01742 0.0146 0.0755 1.0000
8.000 0.8006 0.02836 0.01858 0.0151 0.0741 1.0000
8.250 0.8235 0.02946 0.01976 0.0156 0.0728 1.0000
8.500 0.8462 0.03064 0.02100 0.0161 0.0716 1.0000
8.750 0.8687 0.03191 0.02231 0.0165 0.0705 1.0000
9.000 0.8914 0.03340 0.02383 0.0168 0.0695 1.0000
9.250 0.9104 0.03494 0.02562 0.0176 0.0683 1.0000
9.500 0.9269 0.03651 0.02752 0.0187 0.0667 1.0000
9.750 0.9427 0.03817 0.02943 0.0197 0.0652 1.0000
10.000 0.9574 0.03998 0.03149 0.0207 0.0641 1.0000
10.250 0.9709 0.04189 0.03361 0.0218 0.0632 1.0000
10.500 0.9832 0.04384 0.03577 0.0229 0.0624 1.0000
10.750 0.9946 0.04576 0.03785 0.0239 0.0615 1.0000
11.000 1.0067 0.04765 0.03983 0.0248 0.0605 1.0000
11.250 1.0125 0.05005 0.04238 0.0260 0.0597 1.0000
11.500 0.9991 0.05304 0.04580 0.0285 0.0589 1.0000
11.750 0.9793 0.05607 0.04914 0.0313 0.0584 1.0000
12.000 0.9561 0.05970 0.05305 0.0327 0.0580 1.0000
12.250 0.9295 0.06424 0.05784 0.0325 0.0578 1.0000
12.500 0.8964 0.07017 0.06401 0.0306 0.0578 1.0000
12.750 0.8538 0.07864 0.07270 0.0257 0.0580 1.0000
13.000 0.7839 0.09539 0.08963 0.0136 0.0587 1.0000
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