EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Reynolds number: 500,000 Max Cl/Cd: 47.09 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea61012-il-500000.txt Download as CSV file: xf-ea61012-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0861 0.09449 0.09148 -0.0144 1.0000 0.0300
-17.000 -1.1439 0.07945 0.07612 -0.0245 1.0000 0.0299
-16.750 -1.1711 0.07116 0.06761 -0.0297 1.0000 0.0301
-16.500 -1.1917 0.06473 0.06097 -0.0333 1.0000 0.0304
-16.250 -1.2083 0.05946 0.05550 -0.0359 1.0000 0.0308
-16.000 -1.2213 0.05510 0.05093 -0.0376 1.0000 0.0311
-15.750 -1.2330 0.05111 0.04675 -0.0387 1.0000 0.0314
-15.500 -1.2373 0.04807 0.04365 -0.0390 1.0000 0.0320
-15.250 -1.2325 0.04628 0.04184 -0.0390 1.0000 0.0324
-15.000 -1.2257 0.04486 0.04041 -0.0390 1.0000 0.0328
-14.750 -1.2212 0.04327 0.03877 -0.0388 1.0000 0.0333
-14.500 -1.2181 0.04164 0.03705 -0.0384 1.0000 0.0338
-14.250 -1.2160 0.04000 0.03531 -0.0377 1.0000 0.0344
-14.000 -1.2148 0.03822 0.03341 -0.0367 1.0000 0.0350
-13.750 -1.2134 0.03673 0.03176 -0.0355 1.0000 0.0357
-13.500 -1.2123 0.03535 0.03021 -0.0339 1.0000 0.0362
-13.250 -1.2120 0.03417 0.02887 -0.0319 1.0000 0.0367
-13.000 -1.2039 0.03225 0.02690 -0.0305 1.0000 0.0375
-12.750 -1.1934 0.03168 0.02633 -0.0289 1.0000 0.0381
-12.500 -1.1842 0.03114 0.02577 -0.0267 1.0000 0.0387
-12.250 -1.1741 0.03051 0.02508 -0.0247 1.0000 0.0393
-12.000 -1.1604 0.02982 0.02433 -0.0232 1.0000 0.0401
-11.750 -1.1457 0.02910 0.02351 -0.0218 1.0000 0.0410
-11.500 -1.1306 0.02843 0.02270 -0.0204 1.0000 0.0419
-11.250 -1.1147 0.02800 0.02213 -0.0189 1.0000 0.0426
-11.000 -1.0973 0.02605 0.02008 -0.0182 1.0000 0.0437
-10.750 -1.0770 0.02527 0.01932 -0.0175 1.0000 0.0446
-10.500 -1.0568 0.02469 0.01871 -0.0167 1.0000 0.0454
-10.250 -1.0364 0.02415 0.01813 -0.0159 1.0000 0.0464
-10.000 -1.0152 0.02353 0.01744 -0.0151 1.0000 0.0474
-9.750 -0.9936 0.02285 0.01669 -0.0144 1.0000 0.0483
-9.500 -0.9717 0.02231 0.01605 -0.0136 1.0000 0.0492
-9.250 -0.9494 0.02193 0.01559 -0.0129 1.0000 0.0499
-9.000 -0.9269 0.02024 0.01384 -0.0125 1.0000 0.0510
-8.750 -0.9041 0.01935 0.01297 -0.0120 1.0000 0.0520
-8.500 -0.8810 0.01877 0.01240 -0.0115 1.0000 0.0530
-8.250 -0.8577 0.01825 0.01188 -0.0109 1.0000 0.0541
-8.000 -0.8310 0.01766 0.01127 -0.0111 0.9878 0.0552
-7.750 -0.7879 0.01696 0.01050 -0.0146 0.9477 0.0565
-7.500 -0.7524 0.01645 0.00989 -0.0164 0.9191 0.0575
-7.250 -0.7267 0.01619 0.00950 -0.0161 0.8992 0.0583
-7.000 -0.7057 0.01527 0.00850 -0.0150 0.8861 0.0598
-6.750 -0.6836 0.01469 0.00789 -0.0141 0.8760 0.0610
-6.500 -0.6604 0.01429 0.00745 -0.0134 0.8681 0.0623
-6.250 -0.6365 0.01392 0.00705 -0.0127 0.8608 0.0636
-5.750 -0.5875 0.01332 0.00634 -0.0115 0.8482 0.0666
-5.500 -0.5624 0.01307 0.00604 -0.0110 0.8422 0.0678
-5.250 -0.5390 0.01264 0.00556 -0.0102 0.8370 0.0695
-5.000 -0.5149 0.01220 0.00513 -0.0096 0.8316 0.0718
-4.750 -0.4897 0.01192 0.00483 -0.0091 0.8266 0.0742
-4.500 -0.4641 0.01171 0.00458 -0.0087 0.8220 0.0768
-4.250 -0.4376 0.01151 0.00436 -0.0084 0.8173 0.0793
-4.000 -0.4126 0.01115 0.00403 -0.0079 0.8125 0.0850
-3.750 -0.3866 0.01093 0.00380 -0.0075 0.8082 0.0912
-3.500 -0.3617 0.01056 0.00355 -0.0070 0.8038 0.1118
-3.250 -0.3400 0.00975 0.00322 -0.0062 0.7987 0.2076
-3.000 -0.3195 0.00888 0.00291 -0.0053 0.7936 0.3392
-2.750 -0.2967 0.00835 0.00269 -0.0045 0.7890 0.4247
-2.500 -0.2751 0.00771 0.00259 -0.0034 0.7837 0.5457
-2.250 -0.2488 0.00758 0.00258 -0.0029 0.7789 0.5939
-2.000 -0.2217 0.00754 0.00257 -0.0025 0.7747 0.6205
-1.750 -0.1941 0.00752 0.00258 -0.0023 0.7703 0.6404
-1.500 -0.1664 0.00750 0.00260 -0.0020 0.7655 0.6577
-1.250 -0.1388 0.00750 0.00263 -0.0017 0.7609 0.6747
-1.000 -0.1110 0.00755 0.00267 -0.0014 0.7569 0.6889
-0.750 -0.0830 0.00757 0.00274 -0.0012 0.7526 0.6991
-0.500 -0.0550 0.00760 0.00279 -0.0009 0.7474 0.7109
-0.250 -0.0274 0.00765 0.00280 -0.0005 0.7411 0.7220
0.000 0.0000 0.00764 0.00284 0.0000 0.7316 0.7316
0.250 0.0273 0.00765 0.00280 0.0005 0.7221 0.7410
0.500 0.0550 0.00760 0.00279 0.0009 0.7109 0.7473
0.750 0.0829 0.00757 0.00274 0.0012 0.6991 0.7526
1.000 0.1110 0.00755 0.00266 0.0014 0.6888 0.7569
1.250 0.1387 0.00750 0.00263 0.0017 0.6747 0.7609
1.500 0.1663 0.00750 0.00260 0.0020 0.6578 0.7655
1.750 0.1940 0.00752 0.00258 0.0023 0.6402 0.7703
2.000 0.2217 0.00754 0.00257 0.0025 0.6204 0.7747
2.250 0.2488 0.00758 0.00258 0.0029 0.5937 0.7789
2.500 0.2751 0.00771 0.00259 0.0034 0.5459 0.7837
2.750 0.2967 0.00834 0.00269 0.0045 0.4252 0.7890
3.000 0.3195 0.00888 0.00291 0.0053 0.3392 0.7936
3.250 0.3400 0.00975 0.00322 0.0062 0.2074 0.7987
3.500 0.3616 0.01056 0.00355 0.0070 0.1116 0.8038
3.750 0.3865 0.01093 0.00380 0.0075 0.0912 0.8082
4.000 0.4125 0.01114 0.00403 0.0079 0.0851 0.8125
4.250 0.4376 0.01151 0.00436 0.0084 0.0793 0.8174
4.500 0.4641 0.01171 0.00457 0.0087 0.0768 0.8220
4.750 0.4897 0.01191 0.00483 0.0092 0.0742 0.8266
5.000 0.5148 0.01220 0.00513 0.0096 0.0718 0.8317
5.250 0.5389 0.01264 0.00556 0.0103 0.0695 0.8370
5.500 0.5624 0.01307 0.00604 0.0110 0.0678 0.8422
5.750 0.5874 0.01331 0.00634 0.0115 0.0666 0.8482
6.250 0.6364 0.01392 0.00704 0.0127 0.0636 0.8609
6.500 0.6603 0.01428 0.00744 0.0134 0.0623 0.8682
6.750 0.6836 0.01468 0.00788 0.0141 0.0611 0.8760
7.000 0.7057 0.01526 0.00849 0.0150 0.0598 0.8861
7.250 0.7266 0.01620 0.00951 0.0161 0.0583 0.8992
7.500 0.7524 0.01644 0.00987 0.0165 0.0575 0.9193
7.750 0.7880 0.01696 0.01050 0.0146 0.0565 0.9479
8.000 0.8311 0.01765 0.01126 0.0111 0.0551 0.9884
8.250 0.8577 0.01825 0.01188 0.0109 0.0541 1.0000
8.500 0.8810 0.01877 0.01240 0.0115 0.0530 1.0000
8.750 0.9041 0.01934 0.01296 0.0120 0.0520 1.0000
9.000 0.9270 0.02023 0.01384 0.0125 0.0510 1.0000
9.250 0.9494 0.02192 0.01558 0.0129 0.0499 1.0000
9.500 0.9718 0.02230 0.01605 0.0136 0.0492 1.0000
9.750 0.9937 0.02285 0.01668 0.0144 0.0483 1.0000
10.000 1.0153 0.02352 0.01744 0.0151 0.0473 1.0000
10.250 1.0365 0.02411 0.01808 0.0159 0.0463 1.0000
10.500 1.0569 0.02469 0.01871 0.0167 0.0454 1.0000
10.750 1.0771 0.02524 0.01928 0.0175 0.0445 1.0000
11.000 1.0974 0.02606 0.02009 0.0182 0.0437 1.0000
11.250 1.1148 0.02797 0.02210 0.0189 0.0426 1.0000
11.500 1.1306 0.02843 0.02271 0.0204 0.0419 1.0000
11.750 1.1458 0.02921 0.02362 0.0218 0.0411 1.0000
12.000 1.1603 0.03000 0.02452 0.0232 0.0402 1.0000
12.250 1.1743 0.03059 0.02517 0.0247 0.0393 1.0000
12.500 1.1846 0.03114 0.02577 0.0267 0.0387 1.0000
12.750 1.1939 0.03164 0.02629 0.0288 0.0381 1.0000
13.000 1.2041 0.03233 0.02699 0.0305 0.0375 1.0000
13.250 1.2116 0.03436 0.02906 0.0318 0.0366 1.0000
13.500 1.2126 0.03542 0.03029 0.0339 0.0363 1.0000
13.750 1.2141 0.03663 0.03167 0.0355 0.0356 1.0000
14.000 1.2150 0.03828 0.03346 0.0367 0.0350 1.0000
14.250 1.2175 0.03987 0.03517 0.0376 0.0344 1.0000
14.500 1.2192 0.04161 0.03702 0.0382 0.0338 1.0000
14.750 1.2222 0.04324 0.03874 0.0387 0.0333 1.0000
15.000 1.2271 0.04479 0.04033 0.0389 0.0328 1.0000
15.250 1.2318 0.04648 0.04207 0.0389 0.0324 1.0000
15.500 1.2386 0.04802 0.04360 0.0389 0.0320 1.0000
15.750 1.2351 0.05097 0.04661 0.0386 0.0315 1.0000
16.000 1.2215 0.05521 0.05105 0.0375 0.0311 1.0000
16.250 1.2086 0.05957 0.05561 0.0357 0.0308 1.0000
16.500 1.1944 0.06450 0.06073 0.0332 0.0304 1.0000
16.750 1.1753 0.07069 0.06713 0.0297 0.0300 1.0000
17.000 1.1406 0.08025 0.07694 0.0238 0.0300 1.0000
17.250 1.0703 0.09791 0.09496 0.0119 0.0304 1.0000
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Polar data table (+)
Polar graphs
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