EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 200,000 Max Cl/Cd: 61.16 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87391-il-200000-n5.txt Download as CSV file: xf-ste87391-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4381 0.06765 0.06322 -0.1266 0.9517 0.0170
-12.250 -0.4642 0.06027 0.05559 -0.1324 0.9496 0.0168
-12.000 -0.4783 0.05479 0.04989 -0.1374 0.9478 0.0168
-11.750 -0.5131 0.05327 0.04831 -0.1316 0.9429 0.0168
-11.500 -0.5354 0.05088 0.04578 -0.1292 0.9389 0.0168
-11.250 -0.5515 0.04852 0.04327 -0.1275 0.9361 0.0168
-11.000 -0.5607 0.04624 0.04081 -0.1266 0.9339 0.0169
-10.750 -0.5902 0.04544 0.03994 -0.1192 0.9281 0.0169
-10.500 -0.5927 0.04344 0.03777 -0.1173 0.9247 0.0171
-10.250 -0.5858 0.04140 0.03550 -0.1167 0.9227 0.0173
-10.000 -0.5732 0.03946 0.03334 -0.1167 0.9212 0.0176
-9.750 -0.5549 0.03760 0.03125 -0.1173 0.9201 0.0180
-9.500 -0.5629 0.03669 0.03023 -0.1121 0.9153 0.0182
-9.250 -0.5498 0.03531 0.02866 -0.1109 0.9126 0.0186
-9.000 -0.5302 0.03401 0.02717 -0.1108 0.9108 0.0192
-8.750 -0.5080 0.03286 0.02581 -0.1109 0.9094 0.0200
-8.500 -0.4831 0.03174 0.02449 -0.1114 0.9083 0.0207
-8.250 -0.4561 0.03067 0.02322 -0.1121 0.9074 0.0210
-8.000 -0.4289 0.02934 0.02181 -0.1130 0.9066 0.0215
-7.750 -0.4201 0.02856 0.02099 -0.1103 0.9028 0.0219
-7.500 -0.4007 0.02774 0.02012 -0.1096 0.9000 0.0225
-7.250 -0.3755 0.02698 0.01931 -0.1099 0.8981 0.0231
-7.000 -0.3479 0.02630 0.01855 -0.1106 0.8967 0.0239
-6.750 -0.3181 0.02570 0.01787 -0.1117 0.8954 0.0253
-6.500 -0.2868 0.02515 0.01722 -0.1130 0.8943 0.0266
-6.250 -0.2544 0.02457 0.01655 -0.1145 0.8935 0.0276
-6.000 -0.2212 0.02399 0.01587 -0.1162 0.8927 0.0292
-5.750 -0.2069 0.02378 0.01561 -0.1142 0.8879 0.0306
-5.500 -0.1805 0.02348 0.01522 -0.1144 0.8853 0.0329
-5.250 -0.1500 0.02311 0.01480 -0.1153 0.8834 0.0371
-5.000 -0.1172 0.02256 0.01434 -0.1168 0.8820 0.0575
-4.750 -0.0825 0.02176 0.01404 -0.1193 0.8810 0.1503
-4.500 -0.0490 0.02158 0.01391 -0.1207 0.8799 0.1833
-4.250 -0.0149 0.02143 0.01381 -0.1223 0.8790 0.2109
-4.000 0.0018 0.02151 0.01388 -0.1206 0.8737 0.2248
-3.750 0.0289 0.02144 0.01384 -0.1208 0.8705 0.2420
-3.500 0.0604 0.02130 0.01373 -0.1219 0.8685 0.2597
-3.250 0.0937 0.02113 0.01360 -0.1232 0.8669 0.2778
-3.000 0.1283 0.02094 0.01344 -0.1248 0.8657 0.2943
-2.750 0.1636 0.02074 0.01327 -0.1265 0.8647 0.3110
-2.500 0.1778 0.02086 0.01343 -0.1243 0.8573 0.3253
-2.250 0.2099 0.02068 0.01331 -0.1254 0.8547 0.3490
-2.000 0.2448 0.02041 0.01316 -0.1271 0.8530 0.3830
-1.750 0.2812 0.02008 0.01299 -0.1291 0.8516 0.4299
-1.500 0.3050 0.01998 0.01309 -0.1287 0.8462 0.4815
-1.250 0.3334 0.01974 0.01314 -0.1291 0.8418 0.5529
-1.000 0.3624 0.01947 0.01324 -0.1288 0.8392 0.6393
-0.750 0.3920 0.01930 0.01320 -0.1285 0.8372 0.6983
-0.500 0.4074 0.01954 0.01343 -0.1262 0.8282 0.7239
-0.250 0.4395 0.01932 0.01319 -0.1267 0.8251 0.7424
0.000 0.4709 0.01909 0.01293 -0.1272 0.8217 0.7559
0.250 0.4909 0.01916 0.01299 -0.1257 0.8126 0.7676
0.500 0.5232 0.01873 0.01255 -0.1260 0.8095 0.7770
0.750 0.5407 0.01881 0.01264 -0.1240 0.7985 0.7854
1.000 0.5631 0.01871 0.01255 -0.1228 0.7897 0.7933
1.250 0.5902 0.01841 0.01224 -0.1223 0.7830 0.8005
1.500 0.6111 0.01842 0.01226 -0.1209 0.7725 0.8074
1.750 0.6424 0.01798 0.01182 -0.1211 0.7671 0.8149
2.000 0.6638 0.01794 0.01181 -0.1196 0.7557 0.8253
2.250 0.6860 0.01771 0.01161 -0.1178 0.7455 0.8398
2.500 0.7130 0.01719 0.01111 -0.1167 0.7366 0.8535
2.750 0.7448 0.01668 0.01059 -0.1169 0.7242 0.8602
3.000 0.7820 0.01606 0.00992 -0.1183 0.7092 0.8633
3.250 0.8218 0.01549 0.00928 -0.1202 0.6897 0.8656
3.500 0.8618 0.01505 0.00871 -0.1222 0.6648 0.8677
3.750 0.8959 0.01493 0.00841 -0.1233 0.6342 0.8697
4.000 0.9228 0.01510 0.00841 -0.1233 0.6011 0.8718
4.250 0.9424 0.01541 0.00856 -0.1218 0.5694 0.8738
4.500 0.9599 0.01582 0.00882 -0.1201 0.5392 0.8759
4.750 0.9759 0.01630 0.00916 -0.1182 0.5094 0.8784
5.250 1.0078 0.01740 0.01001 -0.1146 0.4530 0.8827
5.500 1.0245 0.01797 0.01048 -0.1131 0.4284 0.8850
5.750 1.0409 0.01851 0.01094 -0.1114 0.4066 0.8873
6.000 1.0569 0.01905 0.01140 -0.1097 0.3873 0.8893
6.250 1.0739 0.01958 0.01190 -0.1082 0.3688 0.8913
6.500 1.0910 0.02014 0.01241 -0.1068 0.3514 0.8935
6.750 1.1088 0.02070 0.01293 -0.1056 0.3358 0.8957
7.000 1.1268 0.02126 0.01347 -0.1044 0.3221 0.8981
7.250 1.1447 0.02184 0.01404 -0.1032 0.3105 0.9008
7.500 1.1621 0.02235 0.01457 -0.1018 0.2998 0.9033
7.750 1.1802 0.02288 0.01512 -0.1006 0.2901 0.9058
8.000 1.1974 0.02348 0.01572 -0.0993 0.2811 0.9085
8.250 1.2161 0.02402 0.01631 -0.0983 0.2723 0.9113
8.500 1.2338 0.02463 0.01696 -0.0972 0.2651 0.9143
8.750 1.2512 0.02516 0.01756 -0.0959 0.2576 0.9176
9.000 1.2672 0.02579 0.01822 -0.0944 0.2505 0.9215
9.250 1.2841 0.02637 0.01887 -0.0932 0.2421 0.9263
9.500 1.2981 0.02703 0.01957 -0.0915 0.2321 0.9326
9.750 1.3098 0.02777 0.02033 -0.0895 0.2206 0.9418
10.000 1.3191 0.02842 0.02100 -0.0872 0.2081 0.9671
10.250 1.3323 0.02927 0.02186 -0.0858 0.1936 0.9981
10.500 1.3475 0.03018 0.02279 -0.0847 0.1802 0.9981
10.750 1.3613 0.03119 0.02379 -0.0836 0.1654 0.9981
11.000 1.3738 0.03231 0.02488 -0.0823 0.1462 0.9981
11.250 1.3827 0.03370 0.02616 -0.0806 0.1213 0.9981
11.500 1.3864 0.03551 0.02780 -0.0785 0.0910 0.9981
11.750 1.3877 0.03757 0.02969 -0.0762 0.0660 0.9981
12.000 1.3885 0.03974 0.03175 -0.0740 0.0463 0.9981
12.250 1.3891 0.04197 0.03393 -0.0719 0.0323 0.9981
12.500 1.3903 0.04419 0.03616 -0.0699 0.0233 0.9981
12.750 1.3916 0.04647 0.03849 -0.0682 0.0183 0.9981
13.000 1.3932 0.04879 0.04090 -0.0666 0.0156 0.9981
13.250 1.3944 0.05122 0.04344 -0.0651 0.0140 0.9981
13.500 1.3954 0.05374 0.04609 -0.0638 0.0129 0.9981
13.750 1.3946 0.05652 0.04899 -0.0627 0.0121 0.9981
14.000 1.3913 0.05968 0.05229 -0.0616 0.0114 0.9981
14.250 1.3903 0.06269 0.05545 -0.0609 0.0110 0.9981
14.500 1.3876 0.06599 0.05891 -0.0604 0.0105 0.9981
14.750 1.3838 0.06953 0.06259 -0.0600 0.0100 0.9981
15.000 1.3786 0.07334 0.06655 -0.0600 0.0097 0.9981
15.250 1.3722 0.07746 0.07082 -0.0601 0.0094 0.9981
15.500 1.3634 0.08205 0.07555 -0.0606 0.0091 0.9981
15.750 1.3539 0.08687 0.08052 -0.0614 0.0089 0.9981
16.000 1.3432 0.09200 0.08580 -0.0625 0.0088 0.9981
16.250 1.3312 0.09747 0.09143 -0.0640 0.0087 0.9981
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Polar data table (+)
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