EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 334 AIRFOIL (e334-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.47 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e334-il-1000000-n5.txt Download as CSV file: xf-e334-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 334 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2345 0.08506 0.08217 -0.0520 0.6605 0.0054
-8.750 -0.2309 0.08223 0.07929 -0.0532 0.6478 0.0054
-8.500 -0.2306 0.07873 0.07577 -0.0547 0.6353 0.0054
-8.000 -0.2357 0.07163 0.06866 -0.0587 0.6148 0.0054
-7.750 -0.2442 0.06830 0.06530 -0.0600 0.6065 0.0053
-7.250 -0.2141 0.04921 0.04627 -0.0559 0.5702 0.0053
-6.750 -0.2427 0.05549 0.05224 -0.0616 0.5719 0.0051
-6.500 -0.2358 0.05243 0.04908 -0.0616 0.5634 0.0048
-6.250 -0.2281 0.04876 0.04529 -0.0612 0.5566 0.0046
-6.000 -0.2188 0.04499 0.04137 -0.0605 0.5489 0.0043
-5.750 -0.2110 0.04002 0.03617 -0.0590 0.5429 0.0040
-5.500 -0.2016 0.03500 0.03088 -0.0568 0.5363 0.0039
-5.250 -0.1876 0.03135 0.02697 -0.0549 0.5291 0.0039
-5.000 -0.1722 0.02768 0.02303 -0.0527 0.5230 0.0040
-4.750 -0.1553 0.02413 0.01916 -0.0505 0.5164 0.0044
-4.250 -0.1206 0.01508 0.00899 -0.0449 0.5053 0.0050
-4.000 -0.0959 0.01400 0.00768 -0.0442 0.4975 0.0051
-3.750 -0.0701 0.01333 0.00683 -0.0436 0.4898 0.0052
-3.500 -0.0442 0.01277 0.00612 -0.0431 0.4818 0.0053
-3.250 -0.0187 0.01206 0.00526 -0.0425 0.4756 0.0055
-3.000 0.0067 0.01148 0.00458 -0.0419 0.4689 0.0056
-2.750 0.0323 0.01105 0.00406 -0.0413 0.4626 0.0057
-2.500 0.0581 0.01069 0.00364 -0.0408 0.4560 0.0057
-2.000 0.1097 0.01009 0.00291 -0.0398 0.4437 0.0058
-1.750 0.1358 0.00986 0.00263 -0.0393 0.4380 0.0059
-1.500 0.1620 0.00970 0.00242 -0.0389 0.4322 0.0060
-1.250 0.1887 0.00953 0.00221 -0.0386 0.4271 0.0062
-1.000 0.2153 0.00941 0.00205 -0.0383 0.4210 0.0064
-0.750 0.2420 0.00931 0.00191 -0.0380 0.4162 0.0069
-0.500 0.2691 0.00922 0.00180 -0.0377 0.4117 0.0074
-0.250 0.2959 0.00913 0.00169 -0.0374 0.4065 0.0107
0.000 0.3226 0.00907 0.00163 -0.0372 0.4013 0.0201
0.250 0.3494 0.00896 0.00159 -0.0370 0.3973 0.0443
0.500 0.3756 0.00880 0.00158 -0.0367 0.3928 0.1006
0.750 0.3736 0.00657 0.00165 -0.0311 0.3894 0.8654
1.000 0.3972 0.00669 0.00179 -0.0299 0.3853 0.9031
1.250 0.4229 0.00677 0.00185 -0.0292 0.3814 0.9131
1.500 0.4480 0.00687 0.00192 -0.0284 0.3774 0.9231
1.750 0.4715 0.00699 0.00201 -0.0272 0.3731 0.9332
2.000 0.4977 0.00706 0.00205 -0.0268 0.3692 0.9371
2.250 0.5256 0.00711 0.00207 -0.0268 0.3656 0.9380
2.500 0.5532 0.00718 0.00209 -0.0268 0.3616 0.9389
2.750 0.5806 0.00726 0.00213 -0.0268 0.3572 0.9399
3.000 0.6082 0.00733 0.00217 -0.0268 0.3539 0.9409
3.250 0.6358 0.00739 0.00222 -0.0268 0.3503 0.9422
3.500 0.6632 0.00747 0.00227 -0.0267 0.3464 0.9434
3.750 0.6903 0.00757 0.00234 -0.0267 0.3420 0.9446
4.000 0.7178 0.00765 0.00240 -0.0267 0.3388 0.9457
4.250 0.7453 0.00772 0.00247 -0.0267 0.3347 0.9468
4.500 0.7724 0.00782 0.00255 -0.0267 0.3306 0.9479
4.750 0.7992 0.00794 0.00264 -0.0267 0.3259 0.9491
5.000 0.8266 0.00802 0.00272 -0.0267 0.3221 0.9501
5.250 0.8535 0.00811 0.00282 -0.0266 0.3173 0.9513
5.500 0.8798 0.00823 0.00292 -0.0265 0.3122 0.9527
5.750 0.9063 0.00833 0.00303 -0.0263 0.3079 0.9542
6.000 0.9328 0.00844 0.00314 -0.0262 0.3028 0.9558
6.250 0.9586 0.00859 0.00328 -0.0260 0.2971 0.9574
6.500 0.9850 0.00871 0.00340 -0.0259 0.2924 0.9590
6.750 1.0109 0.00885 0.00354 -0.0257 0.2863 0.9607
7.000 1.0364 0.00901 0.00370 -0.0255 0.2803 0.9624
7.250 1.0621 0.00917 0.00385 -0.0253 0.2725 0.9642
7.500 1.0875 0.00936 0.00403 -0.0251 0.2643 0.9661
7.750 1.1125 0.00957 0.00423 -0.0249 0.2552 0.9683
8.000 1.1379 0.00977 0.00443 -0.0247 0.2472 0.9707
8.250 1.1620 0.01002 0.00467 -0.0243 0.2374 0.9736
8.500 1.1867 0.01030 0.00492 -0.0241 0.2270 0.9764
8.750 1.2136 0.01056 0.00518 -0.0244 0.2177 0.9788
9.000 1.2397 0.01092 0.00550 -0.0246 0.2050 0.9818
9.250 1.2652 0.01131 0.00586 -0.0248 0.1916 0.9852
9.500 1.2921 0.01177 0.00627 -0.0253 0.1771 0.9876
9.750 1.3189 0.01226 0.00671 -0.0259 0.1631 0.9903
10.250 1.3618 0.01343 0.00774 -0.0251 0.1320 1.0000
10.500 1.3784 0.01391 0.00819 -0.0236 0.1215 1.0000
10.750 1.3941 0.01444 0.00869 -0.0220 0.1111 1.0000
11.000 1.4081 0.01501 0.00924 -0.0201 0.1006 1.0000
11.250 1.4193 0.01557 0.00978 -0.0177 0.0921 1.0000
11.500 1.4276 0.01622 0.01040 -0.0149 0.0832 1.0000
11.750 1.4349 0.01696 0.01112 -0.0121 0.0744 1.0000
12.000 1.4401 0.01784 0.01196 -0.0093 0.0648 1.0000
12.250 1.4511 0.01849 0.01266 -0.0074 0.0618 1.0000
12.500 1.4472 0.01995 0.01404 -0.0040 0.0484 1.0000
12.750 1.4568 0.02083 0.01498 -0.0025 0.0475 1.0000
13.000 1.4604 0.02215 0.01632 -0.0007 0.0425 1.0000
13.250 1.4581 0.02405 0.01823 0.0011 0.0354 1.0000
13.500 1.4552 0.02624 0.02043 0.0024 0.0294 1.0000
13.750 1.4656 0.02751 0.02180 0.0028 0.0313 1.0000
14.000 1.4519 0.03105 0.02531 0.0036 0.0220 1.0000
14.250 1.4583 0.03288 0.02723 0.0038 0.0226 1.0000
14.500 1.4559 0.03564 0.03006 0.0039 0.0202 1.0000
14.750 1.4504 0.03883 0.03329 0.0038 0.0178 1.0000
15.000 1.4487 0.04167 0.03621 0.0036 0.0169 1.0000
15.250 1.4442 0.04487 0.03949 0.0034 0.0155 1.0000
15.500 1.4382 0.04829 0.04299 0.0030 0.0146 1.0000
15.750 1.4328 0.05170 0.04648 0.0025 0.0137 1.0000
16.000 1.4248 0.05557 0.05041 0.0018 0.0122 1.0000
16.500 1.4049 0.06403 0.05901 -0.0001 0.0091 1.0000
16.750 1.4038 0.06727 0.06235 -0.0010 0.0097 1.0000
17.000 1.3940 0.07170 0.06684 -0.0022 0.0086 1.0000
17.250 1.3899 0.07547 0.07071 -0.0033 0.0086 1.0000
17.500 1.3813 0.07993 0.07523 -0.0046 0.0075 1.0000
17.750 1.3737 0.08428 0.07966 -0.0061 0.0069 1.0000
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Polar data table (+)
Polar graphs
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