EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 50,000 Max Cl/Cd: 33.71 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e68-il-50000.txt Download as CSV file: xf-e68-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3829 0.10855 0.10213 -0.0258 1.0000 0.2895
-8.250 -0.3743 0.10486 0.09847 -0.0239 1.0000 0.2964
-8.000 -0.3996 0.10437 0.09814 -0.0215 1.0000 0.3048
-7.750 -0.3996 0.10105 0.09488 -0.0197 1.0000 0.3086
-7.500 -0.5333 0.08697 0.08115 -0.0359 1.0000 0.1558
-7.250 -0.5503 0.08007 0.07425 -0.0377 1.0000 0.1397
-7.000 -0.5742 0.07285 0.06694 -0.0404 1.0000 0.1302
-6.750 -0.5844 0.06693 0.06080 -0.0418 1.0000 0.1242
-6.500 -0.5871 0.06158 0.05522 -0.0427 1.0000 0.1208
-6.250 -0.5894 0.05370 0.04654 -0.0457 1.0000 0.1154
-6.000 -0.5774 0.05000 0.04254 -0.0457 1.0000 0.1170
-5.750 -0.5628 0.04689 0.03909 -0.0457 1.0000 0.1215
-5.500 -0.5443 0.04298 0.03441 -0.0464 1.0000 0.1260
-5.250 -0.5244 0.04001 0.03112 -0.0463 1.0000 0.1311
-5.000 -0.5028 0.03766 0.02825 -0.0462 1.0000 0.1426
-4.750 -0.4823 0.03582 0.02632 -0.0456 1.0000 0.1588
-4.500 -0.4620 0.03442 0.02491 -0.0449 1.0000 0.1803
-4.250 -0.4411 0.03306 0.02351 -0.0443 1.0000 0.2077
-4.000 -0.4201 0.03188 0.02234 -0.0435 1.0000 0.2387
-3.750 -0.3985 0.03086 0.02125 -0.0429 1.0000 0.2759
-3.500 -0.3787 0.03006 0.02067 -0.0418 1.0000 0.3153
-3.250 -0.3588 0.02943 0.02021 -0.0407 1.0000 0.3636
-3.000 -0.3402 0.02899 0.02002 -0.0392 1.0000 0.4167
-2.750 -0.3227 0.02871 0.01999 -0.0373 1.0000 0.4768
-2.500 -0.3070 0.02858 0.02011 -0.0348 1.0000 0.5393
-2.250 -0.2931 0.02857 0.02030 -0.0317 1.0000 0.6024
-2.000 -0.2817 0.02863 0.02054 -0.0280 1.0000 0.6631
-1.750 -0.2734 0.02871 0.02077 -0.0235 1.0000 0.7226
-1.500 -0.2684 0.02873 0.02091 -0.0183 1.0000 0.7827
-1.250 -0.2662 0.02860 0.02090 -0.0124 1.0000 0.8489
-1.000 -0.2303 0.02857 0.02087 -0.0136 1.0000 0.9576
-0.750 -0.1952 0.02817 0.02012 -0.0196 1.0000 1.0000
-0.500 -0.1697 0.02844 0.02001 -0.0225 1.0000 1.0000
-0.250 -0.1453 0.02895 0.02020 -0.0244 1.0000 1.0000
0.000 -0.1224 0.02957 0.02051 -0.0257 1.0000 1.0000
0.250 -0.1007 0.03026 0.02095 -0.0266 1.0000 1.0000
0.500 -0.0798 0.03099 0.02147 -0.0273 1.0000 1.0000
0.750 -0.0594 0.03178 0.02207 -0.0279 1.0000 1.0000
1.000 -0.0142 0.03362 0.02366 -0.0331 0.9880 1.0000
1.250 0.0399 0.03577 0.02558 -0.0396 0.9705 1.0000
1.500 0.0784 0.03715 0.02679 -0.0433 0.9566 1.0000
1.750 0.1166 0.03857 0.02808 -0.0467 0.9439 1.0000
2.000 0.1514 0.03981 0.02921 -0.0495 0.9309 1.0000
2.250 0.1785 0.04082 0.03014 -0.0509 0.9188 1.0000
2.500 0.2078 0.04195 0.03120 -0.0527 0.9060 1.0000
2.750 0.2375 0.04312 0.03231 -0.0544 0.8931 1.0000
3.000 0.2677 0.04430 0.03345 -0.0562 0.8801 1.0000
3.250 0.2983 0.04550 0.03462 -0.0579 0.8670 1.0000
3.500 0.3295 0.04670 0.03581 -0.0596 0.8537 1.0000
3.750 0.3612 0.04789 0.03699 -0.0614 0.8403 1.0000
4.000 0.3946 0.04908 0.03819 -0.0632 0.8271 1.0000
4.250 0.4253 0.05018 0.03933 -0.0646 0.8133 1.0000
4.500 0.4499 0.05125 0.04043 -0.0652 0.7993 1.0000
4.750 0.4761 0.05231 0.04154 -0.0659 0.7850 1.0000
5.000 0.5031 0.05337 0.04265 -0.0666 0.7705 1.0000
5.250 0.5295 0.05443 0.04380 -0.0672 0.7559 1.0000
5.500 0.5581 0.05541 0.04486 -0.0679 0.7409 1.0000
5.750 0.5861 0.05638 0.04591 -0.0685 0.7260 1.0000
6.000 0.6167 0.05720 0.04686 -0.0691 0.7107 1.0000
6.250 0.6430 0.05807 0.04784 -0.0692 0.6947 1.0000
6.500 0.6609 0.05921 0.04907 -0.0686 0.6781 1.0000
6.750 0.6817 0.06024 0.05023 -0.0682 0.6612 1.0000
7.000 0.7058 0.06110 0.05124 -0.0679 0.6441 1.0000
7.250 0.7346 0.06164 0.05194 -0.0677 0.6270 1.0000
7.500 0.7695 0.06165 0.05214 -0.0676 0.6099 1.0000
7.750 0.8122 0.06087 0.05160 -0.0675 0.5931 1.0000
8.000 0.8313 0.06157 0.05246 -0.0662 0.5741 1.0000
8.250 0.8544 0.06184 0.05291 -0.0649 0.5543 1.0000
8.500 0.9073 0.05911 0.05049 -0.0638 0.5364 1.0000
8.750 1.0802 0.04397 0.03616 -0.0658 0.5164 1.0000
9.000 1.1800 0.03760 0.03003 -0.0685 0.4714 1.0000
9.250 1.2161 0.03614 0.02846 -0.0668 0.4279 1.0000
9.500 1.2276 0.03642 0.02864 -0.0631 0.3890 1.0000
9.750 1.2364 0.03705 0.02905 -0.0593 0.3503 1.0000
10.000 1.2474 0.03802 0.02964 -0.0560 0.3110 1.0000
10.250 1.2485 0.03965 0.03112 -0.0521 0.2789 1.0000
10.500 1.2515 0.04146 0.03275 -0.0486 0.2485 1.0000
10.750 1.2565 0.04351 0.03461 -0.0456 0.2198 1.0000
11.000 1.2633 0.04568 0.03655 -0.0431 0.1934 1.0000
11.250 1.2627 0.04798 0.03888 -0.0400 0.1734 1.0000
11.500 1.2733 0.05048 0.04118 -0.0382 0.1518 1.0000
11.750 1.2773 0.05327 0.04406 -0.0359 0.1368 1.0000
12.000 1.2859 0.05627 0.04712 -0.0342 0.1238 1.0000
12.250 1.3023 0.05962 0.05045 -0.0334 0.1122 1.0000
12.500 1.2878 0.06290 0.05422 -0.0300 0.1090 1.0000
12.750 1.2849 0.06632 0.05791 -0.0279 0.1040 1.0000
13.000 1.3005 0.07079 0.06243 -0.0275 0.0991 1.0000
13.250 1.2804 0.07484 0.06686 -0.0250 0.0985 1.0000
13.500 1.2584 0.07930 0.07167 -0.0232 0.0982 1.0000
13.750 1.2349 0.08421 0.07688 -0.0222 0.0982 1.0000
14.000 1.2087 0.08969 0.08263 -0.0221 0.0983 1.0000
14.250 1.1830 0.09571 0.08888 -0.0228 0.0988 1.0000
14.500 1.1569 0.10237 0.09571 -0.0245 0.0993 1.0000
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Polar data table (+)
Polar graphs
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