EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 500,000 Max Cl/Cd: 121.31 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e67-il-500000.txt Download as CSV file: xf-e67-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 67 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2621 0.09117 0.08907 -0.0581 0.9895 0.0262
-10.000 -0.2579 0.08621 0.08412 -0.0610 0.9879 0.0272
-9.750 -0.4504 0.07252 0.07041 -0.0626 0.9934 0.0177
-9.500 -0.4404 0.06912 0.06704 -0.0674 0.9899 0.0183
-9.250 -0.5252 0.03246 0.02893 -0.1081 0.9714 0.0135
-9.000 -0.5181 0.02852 0.02454 -0.1083 0.9635 0.0134
-8.750 -0.4924 0.02587 0.02159 -0.1105 0.9611 0.0137
-8.500 -0.4629 0.02367 0.01910 -0.1127 0.9595 0.0140
-8.250 -0.4393 0.02208 0.01730 -0.1131 0.9557 0.0143
-8.000 -0.4149 0.02052 0.01552 -0.1134 0.9514 0.0145
-7.750 -0.3842 0.01902 0.01382 -0.1148 0.9493 0.0149
-7.500 -0.3510 0.01794 0.01260 -0.1165 0.9479 0.0156
-7.250 -0.3164 0.01692 0.01145 -0.1184 0.9469 0.0164
-7.000 -0.2809 0.01593 0.01030 -0.1204 0.9460 0.0169
-6.750 -0.2551 0.01495 0.00921 -0.1203 0.9419 0.0174
-6.500 -0.2276 0.01366 0.00782 -0.1208 0.9381 0.0188
-6.250 -0.1939 0.01299 0.00709 -0.1223 0.9361 0.0205
-6.000 -0.1593 0.01239 0.00641 -0.1239 0.9343 0.0225
-5.750 -0.1243 0.01159 0.00556 -0.1257 0.9326 0.0281
-5.500 -0.0956 0.01100 0.00501 -0.1260 0.9286 0.0434
-5.250 -0.0675 0.01057 0.00464 -0.1262 0.9238 0.0600
-5.000 -0.0343 0.01020 0.00427 -0.1275 0.9208 0.0764
-4.750 -0.0001 0.00980 0.00393 -0.1290 0.9182 0.0966
-4.500 0.0261 0.00953 0.00372 -0.1288 0.9124 0.1201
-4.250 0.0561 0.00919 0.00349 -0.1294 0.9077 0.1526
-4.000 0.0885 0.00887 0.00324 -0.1305 0.9041 0.1867
-3.750 0.1150 0.00864 0.00309 -0.1303 0.8979 0.2183
-3.500 0.1444 0.00839 0.00292 -0.1307 0.8926 0.2531
-3.250 0.1753 0.00815 0.00275 -0.1315 0.8881 0.2912
-3.000 0.2012 0.00796 0.00266 -0.1311 0.8810 0.3304
-2.750 0.2313 0.00775 0.00253 -0.1317 0.8759 0.3733
-2.500 0.2580 0.00760 0.00247 -0.1315 0.8691 0.4131
-2.250 0.2866 0.00744 0.00239 -0.1316 0.8629 0.4527
-2.000 0.3144 0.00732 0.00234 -0.1316 0.8564 0.4898
-1.750 0.3420 0.00721 0.00229 -0.1315 0.8496 0.5251
-1.500 0.3703 0.00712 0.00226 -0.1316 0.8431 0.5600
-1.250 0.3973 0.00704 0.00224 -0.1313 0.8357 0.5924
-1.000 0.4252 0.00698 0.00223 -0.1313 0.8289 0.6238
-0.750 0.4520 0.00692 0.00222 -0.1309 0.8210 0.6536
-0.500 0.4793 0.00688 0.00223 -0.1307 0.8135 0.6823
-0.250 0.5063 0.00685 0.00223 -0.1304 0.8054 0.7098
0.000 0.5325 0.00682 0.00226 -0.1299 0.7969 0.7358
0.250 0.5597 0.00681 0.00226 -0.1296 0.7890 0.7613
0.500 0.5848 0.00680 0.00231 -0.1289 0.7795 0.7860
0.750 0.6107 0.00681 0.00234 -0.1283 0.7707 0.8101
1.000 0.6359 0.00682 0.00238 -0.1276 0.7614 0.8332
1.250 0.6600 0.00683 0.00243 -0.1266 0.7512 0.8565
1.500 0.6833 0.00685 0.00247 -0.1254 0.7413 0.8792
1.750 0.7059 0.00688 0.00250 -0.1240 0.7310 0.9027
2.000 0.7261 0.00687 0.00253 -0.1221 0.7195 0.9292
2.250 0.7499 0.00686 0.00253 -0.1210 0.7080 0.9601
2.500 0.7862 0.00689 0.00254 -0.1229 0.6954 1.0000
2.750 0.8127 0.00701 0.00261 -0.1227 0.6827 1.0000
3.000 0.8388 0.00713 0.00268 -0.1224 0.6693 1.0000
3.250 0.8644 0.00727 0.00276 -0.1220 0.6552 1.0000
3.500 0.8897 0.00741 0.00286 -0.1215 0.6402 1.0000
3.750 0.9145 0.00757 0.00298 -0.1209 0.6242 1.0000
4.000 0.9389 0.00774 0.00310 -0.1203 0.6072 1.0000
4.250 0.9628 0.00794 0.00324 -0.1195 0.5894 1.0000
4.500 0.9862 0.00815 0.00339 -0.1186 0.5707 1.0000
4.750 1.0093 0.00837 0.00357 -0.1177 0.5500 1.0000
5.000 1.0313 0.00864 0.00376 -0.1166 0.5279 1.0000
5.250 1.0531 0.00892 0.00397 -0.1155 0.5038 1.0000
5.500 1.0740 0.00924 0.00420 -0.1142 0.4779 1.0000
5.750 1.0937 0.00961 0.00448 -0.1127 0.4485 1.0000
6.000 1.1130 0.01001 0.00476 -0.1111 0.4192 1.0000
6.250 1.1317 0.01045 0.00508 -0.1095 0.3887 1.0000
6.500 1.1487 0.01097 0.00545 -0.1076 0.3547 1.0000
6.750 1.1645 0.01152 0.00584 -0.1055 0.3174 1.0000
7.000 1.1779 0.01217 0.00629 -0.1030 0.2773 1.0000
7.250 1.1907 0.01288 0.00679 -0.1005 0.2386 1.0000
7.500 1.2055 0.01352 0.00728 -0.0983 0.2077 1.0000
7.750 1.2201 0.01417 0.00780 -0.0962 0.1801 1.0000
8.000 1.2342 0.01485 0.00835 -0.0940 0.1539 1.0000
8.250 1.2481 0.01557 0.00894 -0.0918 0.1298 1.0000
8.500 1.2624 0.01625 0.00954 -0.0898 0.1095 1.0000
8.750 1.2759 0.01699 0.01021 -0.0876 0.0915 1.0000
9.000 1.2891 0.01775 0.01090 -0.0855 0.0757 1.0000
9.250 1.3019 0.01855 0.01164 -0.0833 0.0610 1.0000
9.500 1.3131 0.01945 0.01247 -0.0810 0.0471 1.0000
9.750 1.3225 0.02050 0.01344 -0.0785 0.0353 1.0000
10.000 1.3325 0.02152 0.01445 -0.0761 0.0280 1.0000
10.250 1.3416 0.02263 0.01559 -0.0737 0.0235 1.0000
10.500 1.3526 0.02362 0.01665 -0.0716 0.0207 1.0000
10.750 1.3559 0.02519 0.01827 -0.0687 0.0182 1.0000
11.000 1.3674 0.02619 0.01937 -0.0669 0.0170 1.0000
11.250 1.3777 0.02731 0.02056 -0.0651 0.0158 1.0000
11.500 1.3861 0.02859 0.02189 -0.0632 0.0145 1.0000
11.750 1.3841 0.03075 0.02414 -0.0604 0.0132 1.0000
12.000 1.3909 0.03227 0.02576 -0.0587 0.0126 1.0000
12.250 1.3984 0.03377 0.02736 -0.0571 0.0119 1.0000
12.500 1.4041 0.03548 0.02916 -0.0555 0.0112 1.0000
12.750 1.4080 0.03740 0.03117 -0.0539 0.0108 1.0000
13.000 1.4107 0.03950 0.03336 -0.0525 0.0103 1.0000
13.250 1.4070 0.04232 0.03628 -0.0509 0.0098 1.0000
13.500 1.3976 0.04592 0.04002 -0.0493 0.0095 1.0000
13.750 1.4003 0.04837 0.04259 -0.0485 0.0092 1.0000
14.000 1.4021 0.05098 0.04533 -0.0478 0.0090 1.0000
14.250 1.4032 0.05377 0.04826 -0.0472 0.0088 1.0000
14.500 1.4031 0.05681 0.05142 -0.0469 0.0085 1.0000
14.750 1.4024 0.06003 0.05477 -0.0467 0.0083 1.0000
15.000 1.4010 0.06343 0.05831 -0.0467 0.0081 1.0000
15.250 1.3986 0.06709 0.06210 -0.0469 0.0080 1.0000
15.500 1.3959 0.07091 0.06605 -0.0474 0.0079 1.0000
15.750 1.3926 0.07494 0.07021 -0.0482 0.0077 1.0000
16.000 1.3881 0.07924 0.07465 -0.0491 0.0075 1.0000
16.250 1.3831 0.08378 0.07931 -0.0504 0.0074 1.0000
16.500 1.3774 0.08854 0.08422 -0.0519 0.0073 1.0000
16.750 1.3707 0.09362 0.08944 -0.0537 0.0072 1.0000
17.000 1.3630 0.09896 0.09492 -0.0558 0.0071 1.0000
17.250 1.3543 0.10466 0.10077 -0.0582 0.0071 1.0000
17.500 1.3449 0.11063 0.10690 -0.0609 0.0071 1.0000
17.750 1.3349 0.11687 0.11329 -0.0640 0.0070 1.0000
18.000 1.3240 0.12344 0.12002 -0.0675 0.0070 1.0000
18.250 1.3125 0.13030 0.12704 -0.0713 0.0070 1.0000
18.500 1.3006 0.13747 0.13438 -0.0756 0.0070 1.0000
18.750 1.2879 0.14501 0.14208 -0.0802 0.0070 1.0000
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Polar data table (+)
Polar graphs
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