EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 200,000 Max Cl/Cd: 85.88 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e853-il-200000.txt Download as CSV file: xf-e853-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4180 0.08791 0.08469 -0.0535 1.0000 0.0439
-8.750 -0.4332 0.08339 0.08022 -0.0555 1.0000 0.0439
-8.500 -0.4521 0.08030 0.07719 -0.0553 1.0000 0.0439
-8.250 -0.4780 0.07838 0.07534 -0.0529 1.0000 0.0439
-8.000 -0.5044 0.07650 0.07350 -0.0512 1.0000 0.0439
-7.750 -0.4971 0.07032 0.06704 -0.0616 0.9932 0.0441
-7.500 -0.4912 0.06033 0.05701 -0.0685 0.9865 0.0455
-7.250 -0.4660 0.05589 0.05255 -0.0728 0.9827 0.0471
-7.000 -0.3828 0.03658 0.03321 -0.0825 0.9622 0.0530
-6.750 -0.3667 0.02980 0.02585 -0.0890 0.9566 0.0592
-6.500 -0.3923 0.03324 0.02791 -0.0860 0.9606 0.0209
-6.250 -0.3586 0.02825 0.02234 -0.0893 0.9574 0.0199
-6.000 -0.3307 0.02518 0.01881 -0.0901 0.9499 0.0197
-5.750 -0.2940 0.02264 0.01587 -0.0921 0.9465 0.0203
-5.500 -0.2561 0.02037 0.01334 -0.0946 0.9442 0.0247
-5.250 -0.2273 0.01907 0.01194 -0.0950 0.9363 0.0283
-5.000 -0.1900 0.01709 0.00986 -0.0970 0.9331 0.0347
-4.750 -0.1494 0.01565 0.00844 -0.1001 0.9310 0.0591
-4.500 -0.1190 0.01457 0.00747 -0.1012 0.9234 0.0980
-4.250 -0.0813 0.01224 0.00641 -0.1052 0.9203 0.3585
-4.000 -0.0405 0.01198 0.00625 -0.1077 0.9176 0.4674
-3.750 -0.0100 0.01201 0.00623 -0.1081 0.9098 0.5059
-3.500 0.0281 0.01201 0.00612 -0.1099 0.9056 0.5392
-3.250 0.0608 0.01200 0.00607 -0.1107 0.8992 0.5589
-3.000 0.0950 0.01195 0.00592 -0.1118 0.8932 0.5757
-2.750 0.1292 0.01192 0.00581 -0.1129 0.8877 0.5924
-2.500 0.1591 0.01196 0.00579 -0.1131 0.8802 0.6099
-2.250 0.1914 0.01193 0.00572 -0.1138 0.8743 0.6244
-2.000 0.2200 0.01192 0.00565 -0.1139 0.8666 0.6348
-1.750 0.2514 0.01185 0.00553 -0.1146 0.8607 0.6432
-1.500 0.2797 0.01184 0.00545 -0.1147 0.8530 0.6521
-1.250 0.3103 0.01179 0.00537 -0.1153 0.8473 0.6598
-1.000 0.3372 0.01181 0.00534 -0.1152 0.8399 0.6680
-0.750 0.3686 0.01178 0.00526 -0.1159 0.8348 0.6767
-0.500 0.3937 0.01182 0.00532 -0.1155 0.8271 0.6845
-0.250 0.4243 0.01182 0.00527 -0.1161 0.8221 0.6938
0.000 0.4497 0.01188 0.00538 -0.1157 0.8152 0.7024
0.250 0.4784 0.01190 0.00539 -0.1159 0.8097 0.7116
0.500 0.5056 0.01197 0.00548 -0.1158 0.8038 0.7220
0.750 0.5325 0.01202 0.00558 -0.1157 0.7979 0.7325
1.000 0.5615 0.01205 0.00563 -0.1159 0.7933 0.7433
1.250 0.5858 0.01215 0.00582 -0.1153 0.7866 0.7551
1.500 0.6138 0.01218 0.00590 -0.1154 0.7816 0.7681
1.750 0.6389 0.01228 0.00611 -0.1149 0.7757 0.7824
2.000 0.6647 0.01233 0.00625 -0.1144 0.7699 0.7983
2.250 0.6913 0.01237 0.00637 -0.1141 0.7648 0.8166
2.500 0.7132 0.01242 0.00656 -0.1128 0.7576 0.8368
2.750 0.7386 0.01238 0.00662 -0.1120 0.7521 0.8619
3.000 0.7565 0.01235 0.00677 -0.1097 0.7438 0.8962
3.250 0.7857 0.01219 0.00671 -0.1095 0.7368 0.9556
3.500 0.8208 0.01217 0.00671 -0.1112 0.7269 1.0000
3.750 0.8490 0.01218 0.00675 -0.1113 0.7150 1.0000
4.000 0.8765 0.01213 0.00669 -0.1111 0.7015 1.0000
4.250 0.9032 0.01212 0.00670 -0.1106 0.6886 1.0000
4.500 0.9295 0.01215 0.00678 -0.1102 0.6764 1.0000
4.750 0.9552 0.01217 0.00684 -0.1096 0.6629 1.0000
5.000 0.9801 0.01217 0.00693 -0.1087 0.6474 1.0000
5.250 1.0045 0.01215 0.00694 -0.1077 0.6292 1.0000
5.500 1.0260 0.01217 0.00704 -0.1062 0.6055 1.0000
5.750 1.0467 0.01222 0.00708 -0.1045 0.5741 1.0000
6.000 1.0641 0.01239 0.00720 -0.1021 0.5248 1.0000
6.250 1.0743 0.01301 0.00742 -0.0986 0.4354 1.0000
6.500 1.0720 0.01454 0.00820 -0.0934 0.3121 1.0000
6.750 1.0697 0.01633 0.00931 -0.0887 0.2036 1.0000
7.000 1.0715 0.01797 0.01046 -0.0848 0.1303 1.0000
7.250 1.0755 0.01936 0.01163 -0.0810 0.0924 1.0000
7.500 1.0798 0.02076 0.01286 -0.0774 0.0692 1.0000
7.750 1.0874 0.02203 0.01412 -0.0743 0.0532 1.0000
8.000 1.0942 0.02343 0.01551 -0.0712 0.0411 1.0000
8.250 1.1000 0.02501 0.01709 -0.0682 0.0319 1.0000
8.500 1.1073 0.02660 0.01870 -0.0655 0.0256 1.0000
8.750 1.1161 0.02863 0.02083 -0.0629 0.0216 1.0000
9.000 1.1290 0.02972 0.02197 -0.0613 0.0180 1.0000
9.250 1.1481 0.03344 0.02576 -0.0603 0.0155 1.0000
9.500 1.1696 0.03539 0.02793 -0.0594 0.0149 1.0000
9.750 1.1930 0.03809 0.03092 -0.0588 0.0145 1.0000
10.000 1.2115 0.04129 0.03447 -0.0577 0.0143 1.0000
10.250 1.2217 0.04482 0.03838 -0.0558 0.0142 1.0000
10.500 1.2240 0.04843 0.04241 -0.0532 0.0144 1.0000
10.750 1.2198 0.05217 0.04648 -0.0503 0.0146 1.0000
11.000 1.2106 0.05615 0.05078 -0.0474 0.0148 1.0000
11.250 1.1977 0.06043 0.05535 -0.0449 0.0150 1.0000
12.500 1.1008 0.08680 0.08327 -0.0417 0.0191 1.0000
12.750 1.0756 0.09381 0.09044 -0.0444 0.0194 1.0000
13.000 1.0513 0.10138 0.09818 -0.0482 0.0196 1.0000
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Polar data table (+)
Polar graphs
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