EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 500,000 Max Cl/Cd: 125.41 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e656-il-500000.txt Download as CSV file: xf-e656-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 656 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.0240 0.10506 0.10163 -0.0989 0.7521 0.0207
-12.000 -0.0367 0.09804 0.09462 -0.1028 0.7511 0.0219
-11.750 -0.0384 0.09310 0.08968 -0.1048 0.7495 0.0221
-11.500 -0.0293 0.09084 0.08739 -0.1052 0.7476 0.0223
-11.250 -0.0220 0.08821 0.08473 -0.1060 0.7456 0.0225
-11.000 -0.0160 0.08531 0.08184 -0.1070 0.7440 0.0229
-10.750 -0.0130 0.08174 0.07829 -0.1083 0.7426 0.0232
-10.500 -0.0117 0.07786 0.07442 -0.1097 0.7411 0.0238
-10.250 -0.0136 0.07333 0.06991 -0.1115 0.7396 0.0244
-10.000 -0.0524 0.07540 0.07177 -0.1233 0.7440 0.0235
-8.500 -0.2697 0.02852 0.02319 -0.1270 0.7305 0.0127
-8.250 -0.2599 0.02606 0.02050 -0.1255 0.7285 0.0122
-8.000 -0.2479 0.02359 0.01768 -0.1240 0.7264 0.0116
-7.750 -0.2338 0.02084 0.01441 -0.1222 0.7250 0.0108
-7.500 -0.2124 0.01960 0.01297 -0.1215 0.7234 0.0107
-7.250 -0.1902 0.01855 0.01180 -0.1209 0.7218 0.0107
-7.000 -0.1672 0.01769 0.01085 -0.1204 0.7200 0.0108
-6.750 -0.1439 0.01692 0.01000 -0.1199 0.7183 0.0110
-6.500 -0.1202 0.01624 0.00927 -0.1195 0.7165 0.0112
-6.250 -0.0959 0.01565 0.00861 -0.1191 0.7147 0.0116
-6.000 -0.0714 0.01510 0.00799 -0.1188 0.7131 0.0122
-5.750 -0.0461 0.01466 0.00747 -0.1185 0.7116 0.0127
-5.500 -0.0217 0.01413 0.00691 -0.1183 0.7100 0.0140
-5.250 0.0042 0.01383 0.00656 -0.1182 0.7085 0.0154
-5.000 0.0297 0.01339 0.00612 -0.1180 0.7071 0.0181
-4.750 0.0555 0.01297 0.00573 -0.1178 0.7055 0.0251
-4.500 0.0813 0.01255 0.00541 -0.1178 0.7037 0.0411
-4.250 0.1078 0.01224 0.00521 -0.1178 0.7020 0.0619
-4.000 0.1345 0.01194 0.00504 -0.1180 0.7005 0.0912
-3.750 0.1612 0.01161 0.00487 -0.1182 0.6989 0.1345
-3.500 0.1884 0.01131 0.00481 -0.1185 0.6973 0.2009
-3.250 0.2165 0.01116 0.00468 -0.1188 0.6958 0.2316
-3.000 0.2444 0.01092 0.00453 -0.1191 0.6942 0.2603
-2.750 0.2719 0.01063 0.00449 -0.1196 0.6927 0.3407
-2.500 0.2992 0.01037 0.00451 -0.1200 0.6911 0.4303
-2.250 0.3261 0.00997 0.00448 -0.1203 0.6898 0.5347
-2.000 0.3529 0.00969 0.00452 -0.1204 0.6881 0.6294
-1.750 0.3797 0.00962 0.00465 -0.1202 0.6862 0.6925
-1.500 0.4071 0.00968 0.00478 -0.1200 0.6845 0.7289
-1.250 0.4350 0.00977 0.00488 -0.1200 0.6827 0.7528
-1.000 0.4631 0.00987 0.00497 -0.1200 0.6809 0.7705
-0.750 0.4916 0.00997 0.00503 -0.1201 0.6792 0.7833
-0.500 0.5205 0.01008 0.00510 -0.1204 0.6776 0.7950
-0.250 0.5483 0.01022 0.00521 -0.1203 0.6759 0.8046
0.000 0.5771 0.01046 0.00539 -0.1205 0.6739 0.8134
0.250 0.6037 0.01049 0.00545 -0.1203 0.6720 0.8188
0.500 0.6303 0.01056 0.00554 -0.1202 0.6698 0.8243
0.750 0.6582 0.01062 0.00559 -0.1203 0.6674 0.8304
1.000 0.6859 0.01066 0.00563 -0.1204 0.6651 0.8351
1.250 0.7133 0.01070 0.00566 -0.1203 0.6629 0.8395
1.500 0.7419 0.01074 0.00567 -0.1205 0.6608 0.8450
1.750 0.7712 0.01080 0.00569 -0.1209 0.6588 0.8509
2.000 0.7972 0.01095 0.00585 -0.1205 0.6564 0.8564
2.250 0.8221 0.01099 0.00594 -0.1200 0.6537 0.8631
2.500 0.8479 0.01101 0.00599 -0.1197 0.6507 0.8686
2.750 0.8731 0.01100 0.00601 -0.1192 0.6477 0.8734
3.000 0.9007 0.01098 0.00599 -0.1192 0.6449 0.8784
3.250 0.9308 0.01098 0.00594 -0.1198 0.6423 0.8831
3.500 0.9572 0.01103 0.00598 -0.1196 0.6394 0.8865
3.750 0.9804 0.01101 0.00604 -0.1188 0.6360 0.8906
4.000 1.0062 0.01099 0.00607 -0.1185 0.6323 0.8950
4.500 1.0608 0.01088 0.00596 -0.1186 0.6258 0.9026
4.750 1.0870 0.01089 0.00598 -0.1184 0.6223 0.9062
5.000 1.1104 0.01086 0.00604 -0.1177 0.6177 0.9102
5.250 1.1372 0.01082 0.00602 -0.1177 0.6130 0.9138
5.500 1.1632 0.01072 0.00593 -0.1175 0.6088 0.9170
5.750 1.1857 0.01070 0.00597 -0.1166 0.6037 0.9209
6.000 1.2085 0.01067 0.00600 -0.1158 0.5977 0.9253
6.250 1.2343 0.01062 0.00595 -0.1156 0.5923 0.9296
6.500 1.2530 0.01060 0.00602 -0.1140 0.5856 0.9346
6.750 1.2743 0.01057 0.00603 -0.1129 0.5783 0.9396
7.000 1.2945 0.01059 0.00610 -0.1116 0.5704 0.9452
7.250 1.3112 0.01058 0.00612 -0.1095 0.5613 0.9524
7.500 1.3274 0.01063 0.00622 -0.1075 0.5507 0.9603
7.750 1.3431 0.01071 0.00632 -0.1054 0.5383 0.9719
8.000 1.3649 0.01089 0.00650 -0.1049 0.5231 1.0000
8.250 1.3808 0.01125 0.00682 -0.1033 0.5057 1.0000
8.500 1.3933 0.01175 0.00726 -0.1013 0.4858 1.0000
8.750 1.4021 0.01242 0.00784 -0.0988 0.4656 1.0000
9.000 1.4081 0.01323 0.00858 -0.0959 0.4452 1.0000
9.250 1.4125 0.01418 0.00947 -0.0930 0.4254 1.0000
9.500 1.4145 0.01532 0.01053 -0.0900 0.4058 1.0000
9.750 1.4152 0.01662 0.01178 -0.0870 0.3867 1.0000
10.000 1.4154 0.01807 0.01316 -0.0842 0.3683 1.0000
10.250 1.4152 0.01963 0.01465 -0.0815 0.3502 1.0000
10.500 1.4155 0.02126 0.01621 -0.0791 0.3328 1.0000
10.750 1.4162 0.02292 0.01782 -0.0768 0.3158 1.0000
11.000 1.4173 0.02462 0.01947 -0.0746 0.2992 1.0000
11.250 1.4185 0.02637 0.02116 -0.0726 0.2822 1.0000
11.750 1.4236 0.02983 0.02452 -0.0691 0.2515 1.0000
12.000 1.4274 0.03155 0.02622 -0.0676 0.2372 1.0000
12.250 1.4310 0.03334 0.02797 -0.0661 0.2224 1.0000
12.500 1.4350 0.03516 0.02975 -0.0648 0.2083 1.0000
12.750 1.4389 0.03702 0.03157 -0.0636 0.1944 1.0000
13.000 1.4430 0.03892 0.03343 -0.0624 0.1814 1.0000
13.250 1.4473 0.04085 0.03533 -0.0614 0.1693 1.0000
13.500 1.4508 0.04290 0.03735 -0.0604 0.1579 1.0000
13.750 1.4558 0.04486 0.03928 -0.0595 0.1468 1.0000
14.000 1.4609 0.04687 0.04128 -0.0587 0.1362 1.0000
14.250 1.4659 0.04891 0.04331 -0.0580 0.1264 1.0000
14.500 1.4690 0.05119 0.04558 -0.0573 0.1171 1.0000
14.750 1.4733 0.05339 0.04777 -0.0567 0.1081 1.0000
15.000 1.4778 0.05564 0.05003 -0.0562 0.0995 1.0000
15.250 1.4811 0.05805 0.05244 -0.0558 0.0917 1.0000
15.500 1.4829 0.06069 0.05506 -0.0554 0.0839 1.0000
15.750 1.4865 0.06315 0.05755 -0.0551 0.0770 1.0000
16.000 1.4896 0.06574 0.06016 -0.0550 0.0706 1.0000
16.250 1.4902 0.06868 0.06311 -0.0548 0.0649 1.0000
16.500 1.4927 0.07146 0.06592 -0.0548 0.0595 1.0000
16.750 1.4943 0.07437 0.06887 -0.0549 0.0545 1.0000
17.000 1.4926 0.07777 0.07228 -0.0550 0.0503 1.0000
17.250 1.4952 0.08069 0.07525 -0.0553 0.0459 1.0000
17.500 1.4943 0.08413 0.07875 -0.0557 0.0424 1.0000
17.750 1.4933 0.08763 0.08229 -0.0562 0.0392 1.0000
18.000 1.4929 0.09109 0.08583 -0.0568 0.0361 1.0000
18.250 1.4891 0.09510 0.08986 -0.0576 0.0334 1.0000
18.500 1.4894 0.09858 0.09344 -0.0584 0.0310 1.0000
18.750 1.4851 0.10279 0.09770 -0.0595 0.0291 1.0000
19.000 1.4844 0.10649 0.10148 -0.0606 0.0269 1.0000
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Polar data table (+)
Polar graphs
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