EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 200,000 Max Cl/Cd: 62.62 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ec863914-il-200000.txt Download as CSV file: xf-ec863914-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3652 0.15159 0.14858 -0.0294 1.0000 0.0493
-12.500 -0.3702 0.14871 0.14572 -0.0304 1.0000 0.0495
-7.000 -0.6578 0.03972 0.03421 -0.0651 0.9996 0.0255
-6.750 -0.6237 0.03493 0.02880 -0.0687 0.9985 0.0224
-6.500 -0.5855 0.03271 0.02600 -0.0711 0.9964 0.0203
-6.250 -0.5475 0.03204 0.02510 -0.0734 0.9942 0.0197
-6.000 -0.5186 0.03080 0.02374 -0.0742 0.9916 0.0196
-5.750 -0.4828 0.02877 0.02166 -0.0766 0.9880 0.0204
-5.500 -0.4391 0.02804 0.02093 -0.0806 0.9846 0.0216
-5.250 -0.3827 0.02723 0.02002 -0.0867 0.9736 0.0224
-5.000 -0.3214 0.02646 0.01909 -0.0938 0.9617 0.0228
-4.750 -0.2704 0.02625 0.01868 -0.0988 0.9581 0.0237
-4.500 -0.2338 0.02577 0.01804 -0.1008 0.9502 0.0252
-4.250 -0.1915 0.02557 0.01769 -0.1039 0.9465 0.0296
-4.000 -0.1372 0.02449 0.01748 -0.1108 0.9450 0.1935
-3.750 -0.1043 0.02446 0.01748 -0.1122 0.9385 0.2256
-3.500 -0.0672 0.02448 0.01753 -0.1144 0.9340 0.2485
-3.250 -0.0246 0.02464 0.01767 -0.1176 0.9313 0.2675
-3.000 0.0054 0.02456 0.01762 -0.1185 0.9246 0.2853
-2.750 0.0451 0.02446 0.01771 -0.1214 0.9206 0.3264
-2.500 0.0900 0.02440 0.01781 -0.1252 0.9182 0.3648
-2.250 0.1311 0.02411 0.01793 -0.1286 0.9143 0.4459
-2.000 0.1574 0.02407 0.01864 -0.1280 0.9078 0.5824
-1.750 0.1940 0.02455 0.01912 -0.1289 0.9045 0.6419
-1.500 0.2175 0.02487 0.01936 -0.1278 0.8964 0.6665
-1.250 0.2503 0.02518 0.01964 -0.1280 0.8922 0.6823
-1.000 0.2775 0.02543 0.01985 -0.1274 0.8859 0.6955
-0.750 0.3027 0.02558 0.02001 -0.1260 0.8798 0.7042
-0.500 0.3401 0.02560 0.02001 -0.1267 0.8770 0.7147
-0.250 0.3630 0.02557 0.01996 -0.1255 0.8673 0.7252
0.000 0.3970 0.02532 0.01971 -0.1253 0.8640 0.7321
0.250 0.4211 0.02523 0.01961 -0.1243 0.8549 0.7406
0.500 0.4537 0.02488 0.01927 -0.1240 0.8513 0.7475
0.750 0.4955 0.02434 0.01872 -0.1257 0.8493 0.7557
1.000 0.5127 0.02410 0.01851 -0.1230 0.8385 0.7620
1.250 0.5566 0.02331 0.01771 -0.1251 0.8361 0.7694
1.500 0.5739 0.02301 0.01746 -0.1224 0.8254 0.7747
1.750 0.6157 0.02222 0.01668 -0.1242 0.8228 0.7831
2.000 0.6296 0.02196 0.01647 -0.1207 0.8121 0.7902
2.250 0.6649 0.02114 0.01568 -0.1209 0.8092 0.7990
2.500 0.6838 0.02081 0.01541 -0.1186 0.7985 0.8069
2.750 0.7155 0.01987 0.01451 -0.1180 0.7949 0.8147
3.000 0.7389 0.01953 0.01422 -0.1168 0.7832 0.8225
3.250 0.7620 0.01899 0.01374 -0.1151 0.7719 0.8284
3.500 0.7937 0.01833 0.01310 -0.1152 0.7600 0.8341
3.750 0.8380 0.01761 0.01240 -0.1179 0.7456 0.8387
4.000 0.8777 0.01676 0.01154 -0.1193 0.7279 0.8411
4.250 0.9221 0.01612 0.01084 -0.1219 0.7023 0.8429
4.500 0.9650 0.01579 0.01036 -0.1244 0.6667 0.8448
4.750 0.9963 0.01591 0.01027 -0.1250 0.6219 0.8465
5.000 1.0190 0.01634 0.01045 -0.1243 0.5726 0.8482
5.250 1.0373 0.01697 0.01082 -0.1229 0.5241 0.8503
5.500 1.0545 0.01771 0.01132 -0.1215 0.4791 0.8518
5.750 1.0704 0.01846 0.01186 -0.1199 0.4387 0.8530
6.000 1.0838 0.01915 0.01236 -0.1177 0.4053 0.8545
6.250 1.0994 0.01984 0.01290 -0.1160 0.3764 0.8563
6.500 1.1181 0.02052 0.01348 -0.1149 0.3519 0.8577
6.750 1.1383 0.02123 0.01407 -0.1142 0.3323 0.8590
7.000 1.1606 0.02192 0.01469 -0.1138 0.3164 0.8602
7.250 1.1844 0.02255 0.01530 -0.1137 0.3028 0.8616
7.500 1.2093 0.02315 0.01592 -0.1137 0.2912 0.8634
7.750 1.2354 0.02380 0.01657 -0.1140 0.2810 0.8650
8.000 1.2630 0.02450 0.01721 -0.1146 0.2720 0.8662
8.250 1.2834 0.02501 0.01783 -0.1138 0.2620 0.8675
8.500 1.3016 0.02559 0.01849 -0.1127 0.2508 0.8688
8.750 1.3186 0.02621 0.01915 -0.1116 0.2397 0.8703
9.000 1.3356 0.02690 0.01983 -0.1104 0.2289 0.8719
9.250 1.3482 0.02760 0.02059 -0.1087 0.2149 0.8740
9.500 1.3613 0.02827 0.02138 -0.1072 0.1960 0.8760
9.750 1.3745 0.02919 0.02227 -0.1059 0.1731 0.8778
10.000 1.3785 0.03118 0.02372 -0.1036 0.0842 0.8792
10.250 1.3671 0.03501 0.02698 -0.0996 0.0255 0.8801
10.500 1.3713 0.03717 0.02925 -0.0972 0.0195 0.8815
10.750 1.3796 0.03889 0.03114 -0.0953 0.0172 0.8830
11.000 1.3860 0.04081 0.03327 -0.0935 0.0156 0.8846
11.250 1.3889 0.04309 0.03574 -0.0915 0.0146 0.8863
11.500 1.3877 0.04582 0.03864 -0.0895 0.0139 0.8881
11.750 1.3823 0.04908 0.04208 -0.0875 0.0134 0.8900
12.000 1.3743 0.05286 0.04603 -0.0857 0.0131 0.8916
12.250 1.3696 0.05653 0.04984 -0.0845 0.0128 0.8931
12.500 1.3696 0.05974 0.05320 -0.0836 0.0127 0.8947
12.750 1.3691 0.06305 0.05666 -0.0829 0.0125 0.8962
13.000 1.3691 0.06647 0.06023 -0.0823 0.0123 0.8978
13.250 1.3698 0.06993 0.06383 -0.0819 0.0122 0.8995
13.500 1.3718 0.07339 0.06743 -0.0816 0.0121 0.9012
13.750 1.3749 0.07683 0.07101 -0.0814 0.0120 0.9029
14.000 1.3789 0.08028 0.07461 -0.0813 0.0119 0.9046
14.250 1.3828 0.08387 0.07837 -0.0813 0.0119 0.9063
14.500 1.3854 0.08760 0.08228 -0.0814 0.0119 0.9079
14.750 1.3861 0.09154 0.08645 -0.0816 0.0120 0.9097
15.000 1.3844 0.09596 0.09109 -0.0822 0.0120 0.9117
15.250 1.3807 0.10075 0.09610 -0.0832 0.0121 0.9138
15.500 1.3750 0.10597 0.10155 -0.0848 0.0122 0.9160
15.750 1.3674 0.11171 0.10753 -0.0869 0.0124 0.9181
16.000 1.3583 0.11776 0.11381 -0.0899 0.0124 0.9204
16.250 1.3472 0.12403 0.12030 -0.0932 0.0124 0.9229
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Polar data table (+)
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