EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 200,000 Max Cl/Cd: 58.1 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e682-il-200000-n5.txt Download as CSV file: xf-e682-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.1879 0.11751 0.11346 -0.0769 0.8392 0.0329
-13.000 -0.1907 0.10963 0.10554 -0.0785 0.8384 0.0211
-12.750 -0.2585 0.11128 0.10699 -0.0858 0.8548 0.0210
-12.500 -0.2494 0.10908 0.10475 -0.0863 0.8524 0.0203
-12.250 -0.2459 0.10547 0.10113 -0.0878 0.8501 0.0196
-11.750 -0.2739 0.08833 0.08405 -0.0956 0.8451 0.0165
-11.500 -0.2788 0.08312 0.07885 -0.0982 0.8423 0.0164
-11.250 -0.2813 0.07887 0.07460 -0.1005 0.8397 0.0161
-11.000 -0.3031 0.06813 0.06382 -0.1077 0.8372 0.0159
-10.750 -0.3294 0.06069 0.05625 -0.1122 0.8344 0.0158
-10.500 -0.3480 0.05639 0.05184 -0.1132 0.8315 0.0155
-10.250 -0.3718 0.05213 0.04740 -0.1124 0.8285 0.0155
-10.000 -0.3905 0.04875 0.04383 -0.1103 0.8258 0.0154
-9.750 -0.4060 0.04586 0.04073 -0.1073 0.8233 0.0153
-9.500 -0.4211 0.04323 0.03785 -0.1034 0.8211 0.0152
-9.250 -0.4310 0.04063 0.03499 -0.0996 0.8189 0.0152
-9.000 -0.4349 0.03800 0.03204 -0.0964 0.8163 0.0153
-8.750 -0.4337 0.03557 0.02925 -0.0934 0.8139 0.0156
-8.500 -0.4295 0.03328 0.02649 -0.0905 0.8119 0.0162
-8.250 -0.4184 0.03138 0.02425 -0.0885 0.8103 0.0163
-8.000 -0.4038 0.02962 0.02214 -0.0869 0.8088 0.0163
-7.750 -0.3863 0.02799 0.02020 -0.0857 0.8074 0.0164
-7.500 -0.3661 0.02655 0.01848 -0.0847 0.8063 0.0165
-7.250 -0.3436 0.02526 0.01697 -0.0841 0.8051 0.0166
-7.000 -0.3202 0.02388 0.01547 -0.0838 0.8034 0.0168
-6.750 -0.2965 0.02276 0.01428 -0.0835 0.8017 0.0171
-6.500 -0.2730 0.02187 0.01333 -0.0831 0.8001 0.0175
-6.250 -0.2498 0.02110 0.01251 -0.0827 0.7987 0.0180
-6.000 -0.2271 0.02043 0.01179 -0.0821 0.7972 0.0185
-5.750 -0.2049 0.01983 0.01113 -0.0813 0.7956 0.0190
-5.500 -0.1828 0.01932 0.01055 -0.0806 0.7939 0.0200
-5.250 -0.1607 0.01887 0.01002 -0.0798 0.7925 0.0213
-5.000 -0.1398 0.01834 0.00946 -0.0789 0.7913 0.0224
-4.750 -0.1175 0.01794 0.00900 -0.0781 0.7900 0.0234
-4.500 -0.0966 0.01765 0.00866 -0.0772 0.7880 0.0248
-4.250 -0.0754 0.01741 0.00837 -0.0762 0.7860 0.0265
-4.000 -0.0543 0.01713 0.00811 -0.0752 0.7837 0.0296
-3.750 -0.0331 0.01683 0.00784 -0.0743 0.7817 0.0400
-3.500 -0.0139 0.01634 0.00759 -0.0731 0.7797 0.0868
-3.250 0.0045 0.01579 0.00738 -0.0718 0.7779 0.1647
-3.000 0.0192 0.01503 0.00715 -0.0700 0.7761 0.2938
-2.750 0.0300 0.01411 0.00692 -0.0674 0.7745 0.4641
-2.500 0.0539 0.01471 0.00886 -0.0635 0.7726 0.7436
-2.250 0.0607 0.01503 0.00914 -0.0597 0.7689 0.7988
-2.000 0.0810 0.01554 0.00958 -0.0578 0.7663 0.8201
-1.750 0.1037 0.01586 0.00980 -0.0564 0.7640 0.8333
-1.500 0.1289 0.01632 0.01018 -0.0551 0.7621 0.8477
-1.250 0.1629 0.01681 0.01060 -0.0552 0.7607 0.8585
-1.000 0.1938 0.01699 0.01067 -0.0554 0.7592 0.8659
-0.750 0.2166 0.01722 0.01089 -0.0544 0.7558 0.8720
-0.500 0.2317 0.01733 0.01097 -0.0521 0.7519 0.8787
-0.250 0.2614 0.01736 0.01094 -0.0525 0.7492 0.8814
0.000 0.2898 0.01731 0.01083 -0.0527 0.7469 0.8845
0.250 0.3141 0.01722 0.01067 -0.0521 0.7449 0.8887
0.500 0.3343 0.01714 0.01054 -0.0508 0.7424 0.8924
0.750 0.3519 0.01727 0.01070 -0.0492 0.7371 0.8948
1.000 0.3766 0.01722 0.01063 -0.0488 0.7337 0.8968
1.250 0.4035 0.01709 0.01047 -0.0488 0.7311 0.8986
1.500 0.4317 0.01693 0.01026 -0.0490 0.7290 0.9004
1.750 0.4401 0.01699 0.01035 -0.0457 0.7235 0.9041
2.000 0.4561 0.01692 0.01028 -0.0438 0.7188 0.9065
2.250 0.4847 0.01674 0.01009 -0.0441 0.7158 0.9074
2.500 0.5161 0.01653 0.00986 -0.0449 0.7135 0.9082
2.750 0.5260 0.01662 0.01001 -0.0418 0.7061 0.9103
3.000 0.5507 0.01645 0.00986 -0.0414 0.7018 0.9114
3.250 0.5814 0.01620 0.00959 -0.0421 0.6988 0.9124
3.500 0.5887 0.01627 0.00973 -0.0386 0.6907 0.9147
3.750 0.6139 0.01605 0.00953 -0.0383 0.6859 0.9156
4.000 0.6295 0.01599 0.00952 -0.0363 0.6791 0.9176
4.250 0.6481 0.01586 0.00942 -0.0348 0.6721 0.9191
4.500 0.6634 0.01582 0.00942 -0.0328 0.6641 0.9204
4.750 0.6851 0.01564 0.00928 -0.0318 0.6567 0.9213
5.000 0.6935 0.01565 0.00935 -0.0285 0.6462 0.9228
5.250 0.7148 0.01552 0.00925 -0.0275 0.6375 0.9240
5.500 0.7386 0.01534 0.00910 -0.0268 0.6277 0.9252
5.750 0.7592 0.01529 0.00908 -0.0258 0.6158 0.9263
6.000 0.7852 0.01514 0.00893 -0.0256 0.6028 0.9271
6.250 0.8125 0.01499 0.00876 -0.0256 0.5877 0.9277
6.500 0.8387 0.01492 0.00864 -0.0255 0.5704 0.9284
6.750 0.8620 0.01499 0.00866 -0.0249 0.5520 0.9293
7.000 0.8812 0.01519 0.00883 -0.0238 0.5333 0.9304
7.250 0.8988 0.01547 0.00906 -0.0225 0.5127 0.9316
7.500 0.9152 0.01582 0.00937 -0.0211 0.4928 0.9329
7.750 0.9285 0.01626 0.00978 -0.0192 0.4715 0.9346
8.000 0.9394 0.01677 0.01023 -0.0170 0.4491 0.9364
8.250 0.9502 0.01735 0.01077 -0.0149 0.4276 0.9380
8.500 0.9602 0.01803 0.01139 -0.0129 0.4047 0.9398
8.750 0.9699 0.01877 0.01210 -0.0109 0.3819 0.9416
9.000 0.9772 0.01968 0.01291 -0.0088 0.3562 0.9436
9.250 0.9835 0.02069 0.01383 -0.0067 0.3278 0.9456
9.750 0.9946 0.02298 0.01588 -0.0028 0.2696 0.9498
10.000 1.0009 0.02417 0.01698 -0.0010 0.2420 0.9521
10.250 1.0079 0.02540 0.01812 0.0005 0.2160 0.9545
10.500 1.0143 0.02673 0.01934 0.0019 0.1887 0.9573
10.750 1.0216 0.02809 0.02059 0.0032 0.1642 0.9604
11.000 1.0299 0.02951 0.02191 0.0041 0.1388 0.9636
11.250 1.0392 0.03093 0.02327 0.0048 0.1173 0.9671
11.500 1.0470 0.03254 0.02476 0.0054 0.0936 0.9710
11.750 1.0558 0.03417 0.02633 0.0058 0.0737 0.9762
12.250 1.0708 0.03733 0.02943 0.0072 0.0460 1.0000
12.500 1.0750 0.03932 0.03135 0.0080 0.0329 1.0000
12.750 1.0806 0.04127 0.03330 0.0086 0.0248 1.0000
13.000 1.0862 0.04327 0.03531 0.0092 0.0199 1.0000
13.250 1.0932 0.04519 0.03732 0.0096 0.0175 1.0000
13.500 1.0981 0.04737 0.03955 0.0100 0.0160 1.0000
13.750 1.1049 0.04944 0.04176 0.0102 0.0153 1.0000
14.000 1.1096 0.05176 0.04421 0.0104 0.0144 1.0000
14.250 1.1139 0.05419 0.04674 0.0104 0.0136 1.0000
14.500 1.1174 0.05676 0.04944 0.0104 0.0133 1.0000
14.750 1.1183 0.05971 0.05249 0.0102 0.0128 1.0000
15.000 1.1172 0.06297 0.05586 0.0100 0.0125 1.0000
15.250 1.1187 0.06601 0.05903 0.0095 0.0123 1.0000
15.500 1.1192 0.06924 0.06240 0.0090 0.0120 1.0000
15.750 1.1193 0.07261 0.06592 0.0083 0.0119 1.0000
16.000 1.1189 0.07608 0.06953 0.0075 0.0116 1.0000
16.250 1.1182 0.07968 0.07326 0.0066 0.0114 1.0000
16.500 1.1177 0.08331 0.07701 0.0056 0.0111 1.0000
16.750 1.1168 0.08706 0.08088 0.0044 0.0109 1.0000
17.000 1.1155 0.09094 0.08488 0.0031 0.0106 1.0000
17.250 1.1146 0.09479 0.08884 0.0017 0.0105 1.0000
17.500 1.1132 0.09878 0.09294 0.0002 0.0103 1.0000
17.750 1.1102 0.10309 0.09734 -0.0017 0.0099 1.0000
18.000 1.1088 0.10713 0.10148 -0.0033 0.0098 1.0000
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