EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 100,000 Max Cl/Cd: 35.32 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e657-il-100000-n5.txt Download as CSV file: xf-e657-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 657 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0871 0.10027 0.09463 -0.1167 0.8812 0.0229
-11.250 -0.0823 0.09642 0.09075 -0.1189 0.8777 0.0227
-11.000 -0.0774 0.09308 0.08740 -0.1206 0.8740 0.0222
-10.750 -0.0775 0.08903 0.08338 -0.1224 0.8697 0.0220
-10.500 -0.0783 0.08474 0.07910 -0.1245 0.8656 0.0218
-10.250 -0.0801 0.08007 0.07444 -0.1272 0.8620 0.0217
-9.750 -0.1455 0.05805 0.05234 -0.1415 0.8520 0.0193
-9.500 -0.1652 0.05367 0.04782 -0.1438 0.8473 0.0192
-9.250 -0.1835 0.05031 0.04427 -0.1438 0.8433 0.0191
-9.000 -0.2056 0.04816 0.04197 -0.1411 0.8381 0.0190
-8.750 -0.2175 0.04588 0.03947 -0.1388 0.8334 0.0190
-8.500 -0.2275 0.04305 0.03626 -0.1365 0.8296 0.0191
-8.250 -0.2303 0.04020 0.03291 -0.1344 0.8268 0.0194
-8.000 -0.2195 0.03963 0.03239 -0.1331 0.8239 0.0203
-7.750 -0.2151 0.03817 0.03069 -0.1309 0.8202 0.0207
-7.500 -0.2070 0.03659 0.02880 -0.1290 0.8168 0.0217
-7.250 -0.1951 0.03461 0.02637 -0.1274 0.8139 0.0225
-7.000 -0.1781 0.03275 0.02411 -0.1263 0.8117 0.0234
-6.750 -0.1575 0.03144 0.02263 -0.1257 0.8100 0.0242
-6.500 -0.1430 0.03053 0.02157 -0.1240 0.8072 0.0250
-6.250 -0.1309 0.02974 0.02062 -0.1217 0.8035 0.0262
-6.000 -0.1139 0.02885 0.01954 -0.1201 0.8003 0.0275
-5.750 -0.0943 0.02823 0.01889 -0.1192 0.7978 0.0300
-5.500 -0.0729 0.02750 0.01806 -0.1185 0.7958 0.0336
-5.250 -0.0502 0.02675 0.01718 -0.1178 0.7942 0.0376
-5.000 -0.0261 0.02607 0.01644 -0.1175 0.7927 0.0439
-4.750 -0.0241 0.02623 0.01667 -0.1137 0.7871 0.0489
-4.500 -0.0085 0.02594 0.01636 -0.1121 0.7837 0.0592
-4.250 0.0114 0.02550 0.01600 -0.1112 0.7813 0.0759
-4.000 0.0348 0.02497 0.01556 -0.1108 0.7792 0.1041
-3.750 0.0603 0.02439 0.01516 -0.1108 0.7775 0.1483
-3.500 0.0870 0.02381 0.01483 -0.1111 0.7761 0.2132
-3.250 0.0816 0.02448 0.01569 -0.1064 0.7691 0.2515
-3.000 0.0997 0.02418 0.01573 -0.1053 0.7659 0.3399
-2.750 0.1215 0.02368 0.01571 -0.1046 0.7636 0.4619
-2.500 0.1410 0.02340 0.01595 -0.1025 0.7617 0.5923
-2.250 0.1609 0.02350 0.01625 -0.0998 0.7601 0.6826
-2.000 0.1509 0.02461 0.01743 -0.0938 0.7521 0.7197
-1.750 0.1630 0.02506 0.01789 -0.0903 0.7484 0.7572
-1.500 0.1841 0.02534 0.01806 -0.0884 0.7461 0.7913
-1.250 0.2099 0.02550 0.01806 -0.0875 0.7444 0.8213
-1.000 0.1959 0.02658 0.01915 -0.0810 0.7358 0.8395
-0.750 0.2077 0.02690 0.01941 -0.0777 0.7317 0.8583
-0.500 0.2278 0.02694 0.01935 -0.0756 0.7294 0.8773
-0.250 0.2520 0.02687 0.01917 -0.0742 0.7278 0.8953
0.000 0.2735 0.02688 0.01909 -0.0725 0.7256 0.9136
0.500 0.2986 0.02804 0.02018 -0.0685 0.7131 0.9517
0.750 0.3460 0.02801 0.02004 -0.0721 0.7120 0.9652
1.000 0.3942 0.02794 0.01986 -0.0759 0.7110 0.9738
1.250 0.4397 0.02784 0.01965 -0.0794 0.7098 0.9801
1.750 0.4738 0.02911 0.02087 -0.0788 0.6961 1.0000
2.000 0.5025 0.02886 0.02054 -0.0789 0.6944 1.0000
2.500 0.5167 0.02999 0.02161 -0.0741 0.6800 1.0000
2.750 0.5442 0.03003 0.02159 -0.0744 0.6769 1.0000
3.250 0.5808 0.03091 0.02243 -0.0730 0.6644 1.0000
3.500 0.6117 0.03082 0.02232 -0.0737 0.6616 1.0000
3.750 0.6171 0.03193 0.02344 -0.0718 0.6508 1.0000
4.000 0.6513 0.03164 0.02313 -0.0727 0.6486 1.0000
4.500 0.6897 0.03255 0.02405 -0.0716 0.6347 1.0000
4.750 0.7247 0.03211 0.02363 -0.0725 0.6327 1.0000
5.250 0.7646 0.03284 0.02440 -0.0714 0.6183 1.0000
5.750 0.8060 0.03344 0.02508 -0.0704 0.6039 1.0000
6.000 0.8394 0.03285 0.02453 -0.0709 0.6013 1.0000
6.500 0.8664 0.03434 0.02612 -0.0686 0.5805 1.0000
6.750 0.8932 0.03411 0.02594 -0.0684 0.5746 1.0000
7.000 0.9285 0.03325 0.02513 -0.0689 0.5715 1.0000
7.500 0.9762 0.03319 0.02521 -0.0681 0.5556 1.0000
7.750 0.9887 0.03404 0.02612 -0.0669 0.5429 1.0000
8.000 1.0078 0.03440 0.02656 -0.0662 0.5320 1.0000
8.250 1.0427 0.03349 0.02571 -0.0665 0.5253 1.0000
8.500 1.0610 0.03391 0.02619 -0.0657 0.5123 1.0000
8.750 1.0847 0.03392 0.02627 -0.0652 0.5003 1.0000
9.000 1.1131 0.03356 0.02594 -0.0650 0.4881 1.0000
9.250 1.1409 0.03325 0.02566 -0.0648 0.4745 1.0000
9.500 1.1648 0.03327 0.02569 -0.0643 0.4590 1.0000
9.750 1.1852 0.03358 0.02600 -0.0636 0.4422 1.0000
10.000 1.2033 0.03407 0.02650 -0.0627 0.4245 1.0000
10.250 1.2196 0.03471 0.02714 -0.0617 0.4064 1.0000
10.500 1.2341 0.03551 0.02792 -0.0606 0.3880 1.0000
10.750 1.2470 0.03644 0.02883 -0.0594 0.3697 1.0000
11.000 1.2582 0.03752 0.02988 -0.0582 0.3516 1.0000
11.250 1.2680 0.03874 0.03107 -0.0569 0.3338 1.0000
11.500 1.2764 0.04010 0.03241 -0.0556 0.3165 1.0000
11.750 1.2836 0.04161 0.03391 -0.0544 0.2996 1.0000
12.000 1.2905 0.04319 0.03550 -0.0532 0.2833 1.0000
12.250 1.2965 0.04490 0.03721 -0.0520 0.2675 1.0000
12.500 1.3019 0.04670 0.03903 -0.0509 0.2521 1.0000
12.750 1.3066 0.04862 0.04094 -0.0498 0.2373 1.0000
13.000 1.3109 0.05063 0.04296 -0.0489 0.2232 1.0000
13.250 1.3147 0.05277 0.04514 -0.0480 0.2094 1.0000
13.500 1.3186 0.05496 0.04737 -0.0472 0.1963 1.0000
13.750 1.3217 0.05728 0.04975 -0.0465 0.1839 1.0000
14.000 1.3244 0.05971 0.05222 -0.0459 0.1722 1.0000
14.250 1.3258 0.06233 0.05485 -0.0454 0.1612 1.0000
14.500 1.3271 0.06504 0.05761 -0.0449 0.1505 1.0000
14.750 1.3290 0.06777 0.06043 -0.0447 0.1403 1.0000
15.000 1.3294 0.07073 0.06343 -0.0445 0.1312 1.0000
15.250 1.3287 0.07389 0.06663 -0.0444 0.1226 1.0000
15.500 1.3296 0.07694 0.06981 -0.0444 0.1142 1.0000
15.750 1.3275 0.08040 0.07329 -0.0446 0.1072 1.0000
16.000 1.3273 0.08375 0.07677 -0.0450 0.0997 1.0000
16.250 1.3251 0.08740 0.08047 -0.0454 0.0935 1.0000
16.500 1.3235 0.09107 0.08427 -0.0460 0.0872 1.0000
16.750 1.3207 0.09492 0.08817 -0.0468 0.0821 1.0000
17.000 1.3186 0.09877 0.09217 -0.0477 0.0766 1.0000
17.250 1.3144 0.10293 0.09635 -0.0488 0.0725 1.0000
17.500 1.3130 0.10682 0.10043 -0.0499 0.0677 1.0000
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Polar data table (+)
Polar graphs
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