EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.39 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e556-il-1000000.txt Download as CSV file: xf-e556-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 556 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6981 0.11493 0.11262 -0.0431 1.0000 0.0054
-16.500 -0.7261 0.10498 0.10252 -0.0481 1.0000 0.0053
-16.250 -0.7528 0.09585 0.09323 -0.0528 1.0000 0.0053
-16.000 -0.7664 0.08961 0.08688 -0.0559 1.0000 0.0052
-15.750 -0.7842 0.08293 0.08006 -0.0591 1.0000 0.0051
-15.500 -0.7973 0.07730 0.07431 -0.0617 1.0000 0.0051
-15.250 -0.8090 0.07218 0.06906 -0.0640 1.0000 0.0051
-15.000 -0.8223 0.06706 0.06381 -0.0660 1.0000 0.0051
-14.750 -0.8289 0.06308 0.05972 -0.0675 1.0000 0.0050
-14.500 -0.8376 0.05904 0.05557 -0.0687 1.0000 0.0051
-14.250 -0.8422 0.05572 0.05216 -0.0696 1.0000 0.0050
-14.000 -0.8487 0.05235 0.04868 -0.0702 1.0000 0.0051
-13.750 -0.8534 0.04940 0.04565 -0.0705 1.0000 0.0051
-13.500 -0.8570 0.04678 0.04295 -0.0705 1.0000 0.0050
-13.250 -0.8608 0.04427 0.04036 -0.0703 1.0000 0.0050
-13.000 -0.8663 0.04178 0.03779 -0.0698 1.0000 0.0051
-12.750 -0.8712 0.03953 0.03546 -0.0689 1.0000 0.0051
-12.500 -0.8783 0.03732 0.03318 -0.0676 1.0000 0.0051
-12.250 -0.8838 0.03549 0.03130 -0.0660 1.0000 0.0051
-12.000 -0.8829 0.03348 0.02922 -0.0658 0.9994 0.0051
-11.750 -0.8638 0.03112 0.02677 -0.0695 0.9970 0.0052
-11.500 -0.8422 0.02893 0.02448 -0.0734 0.9946 0.0052
-11.250 -0.8227 0.02695 0.02242 -0.0763 0.9910 0.0053
-11.000 -0.8022 0.02483 0.02022 -0.0799 0.9868 0.0053
-10.750 -0.7725 0.02275 0.01804 -0.0849 0.9845 0.0055
-10.500 -0.7500 0.02079 0.01601 -0.0880 0.9779 0.0055
-10.250 -0.7168 0.01924 0.01437 -0.0923 0.9753 0.0057
-10.000 -0.6831 0.01814 0.01318 -0.0956 0.9737 0.0058
-9.750 -0.6628 0.01659 0.01154 -0.0966 0.9662 0.0061
-9.500 -0.6308 0.01544 0.01033 -0.0992 0.9636 0.0066
-9.250 -0.5967 0.01466 0.00951 -0.1016 0.9619 0.0070
-9.000 -0.5724 0.01402 0.00882 -0.1017 0.9550 0.0076
-8.750 -0.5401 0.01325 0.00800 -0.1035 0.9516 0.0084
-8.500 -0.5041 0.01256 0.00728 -0.1059 0.9493 0.0097
-8.250 -0.4725 0.01198 0.00667 -0.1073 0.9432 0.0113
-8.000 -0.4350 0.01138 0.00607 -0.1100 0.9387 0.0150
-7.750 -0.3928 0.01082 0.00553 -0.1137 0.9354 0.0220
-7.500 -0.3525 0.01035 0.00507 -0.1169 0.9295 0.0293
-7.250 -0.3118 0.00991 0.00466 -0.1201 0.9222 0.0386
-7.000 -0.2742 0.00948 0.00425 -0.1227 0.9130 0.0527
-6.750 -0.2385 0.00900 0.00385 -0.1249 0.9022 0.0770
-6.500 -0.2076 0.00854 0.00347 -0.1261 0.8895 0.1101
-6.250 -0.1791 0.00796 0.00305 -0.1269 0.8763 0.1598
-6.000 -0.1525 0.00687 0.00242 -0.1280 0.8634 0.2818
-5.750 -0.1243 0.00652 0.00223 -0.1284 0.8513 0.3439
-5.500 -0.0959 0.00646 0.00214 -0.1285 0.8395 0.3654
-5.250 -0.0678 0.00644 0.00207 -0.1286 0.8276 0.3776
-5.000 -0.0398 0.00642 0.00201 -0.1286 0.8162 0.3870
-4.750 -0.0117 0.00646 0.00195 -0.1285 0.8052 0.3953
-4.500 0.0161 0.00647 0.00192 -0.1285 0.7940 0.4049
-4.250 0.0443 0.00651 0.00188 -0.1284 0.7831 0.4109
-4.000 0.0721 0.00650 0.00184 -0.1284 0.7724 0.4163
-3.500 0.1279 0.00660 0.00183 -0.1283 0.7507 0.4304
-3.250 0.1559 0.00667 0.00185 -0.1282 0.7403 0.4365
-3.000 0.1835 0.00672 0.00181 -0.1281 0.7296 0.4394
-2.750 0.2118 0.00675 0.00178 -0.1281 0.7193 0.4414
-2.500 0.2396 0.00673 0.00173 -0.1281 0.7096 0.4444
-2.250 0.2673 0.00675 0.00171 -0.1280 0.6993 0.4473
-2.000 0.2955 0.00677 0.00170 -0.1280 0.6895 0.4499
-1.750 0.3232 0.00682 0.00168 -0.1280 0.6800 0.4524
-1.500 0.3512 0.00686 0.00167 -0.1279 0.6699 0.4549
-1.250 0.3793 0.00691 0.00167 -0.1279 0.6604 0.4570
-0.750 0.4350 0.00695 0.00167 -0.1279 0.6409 0.4630
-0.500 0.4627 0.00700 0.00168 -0.1278 0.6315 0.4657
-0.250 0.4905 0.00705 0.00170 -0.1278 0.6216 0.4683
0.000 0.5184 0.00711 0.00172 -0.1277 0.6121 0.4708
0.250 0.5458 0.00720 0.00175 -0.1276 0.6024 0.4730
0.500 0.5737 0.00722 0.00177 -0.1276 0.5926 0.4763
0.750 0.6013 0.00727 0.00181 -0.1276 0.5832 0.4794
1.000 0.6287 0.00735 0.00187 -0.1274 0.5732 0.4824
1.250 0.6565 0.00741 0.00191 -0.1274 0.5635 0.4852
1.500 0.6837 0.00751 0.00197 -0.1272 0.5536 0.4879
1.750 0.7110 0.00759 0.00202 -0.1271 0.5429 0.4905
2.000 0.7384 0.00765 0.00208 -0.1271 0.5325 0.4940
2.250 0.7653 0.00775 0.00216 -0.1269 0.5217 0.4974
2.500 0.7923 0.00785 0.00224 -0.1267 0.5105 0.5008
2.750 0.8196 0.00795 0.00232 -0.1266 0.5003 0.5039
3.000 0.8463 0.00807 0.00241 -0.1263 0.4898 0.5070
3.250 0.8730 0.00817 0.00251 -0.1261 0.4787 0.5107
3.500 0.8999 0.00827 0.00261 -0.1260 0.4679 0.5144
3.750 0.9263 0.00840 0.00273 -0.1257 0.4567 0.5181
4.000 0.9522 0.00857 0.00285 -0.1253 0.4447 0.5216
4.250 0.9787 0.00868 0.00297 -0.1251 0.4331 0.5261
4.500 1.0050 0.00882 0.00311 -0.1248 0.4217 0.5304
4.750 1.0307 0.00898 0.00325 -0.1245 0.4099 0.5347
5.000 1.0561 0.00917 0.00341 -0.1240 0.3975 0.5386
5.250 1.0815 0.00934 0.00357 -0.1236 0.3846 0.5436
5.500 1.1069 0.00951 0.00375 -0.1232 0.3717 0.5488
5.750 1.1317 0.00973 0.00393 -0.1227 0.3577 0.5539
6.000 1.1563 0.00994 0.00413 -0.1221 0.3441 0.5597
6.250 1.1806 0.01017 0.00434 -0.1215 0.3303 0.5658
6.500 1.2042 0.01043 0.00457 -0.1208 0.3146 0.5717
6.750 1.2273 0.01071 0.00482 -0.1200 0.2977 0.5783
7.000 1.2496 0.01104 0.00510 -0.1191 0.2795 0.5854
7.250 1.2708 0.01141 0.00541 -0.1180 0.2596 0.5929
7.500 1.2914 0.01182 0.00575 -0.1168 0.2376 0.6014
8.000 1.3298 0.01270 0.00650 -0.1139 0.1987 0.6192
8.250 1.3470 0.01313 0.00689 -0.1121 0.1807 0.6292
8.500 1.3638 0.01356 0.00729 -0.1102 0.1654 0.6396
8.750 1.3799 0.01404 0.00773 -0.1082 0.1503 0.6515
9.000 1.3953 0.01454 0.00820 -0.1062 0.1356 0.6649
9.250 1.4107 0.01506 0.00870 -0.1042 0.1223 0.6794
9.500 1.4256 0.01558 0.00922 -0.1021 0.1104 0.6953
9.750 1.4402 0.01612 0.00977 -0.1000 0.1003 0.7127
10.000 1.4537 0.01671 0.01037 -0.0978 0.0903 0.7323
10.250 1.4678 0.01726 0.01096 -0.0958 0.0821 0.7566
10.500 1.4809 0.01784 0.01161 -0.0936 0.0744 0.7876
10.750 1.4910 0.01850 0.01235 -0.0910 0.0665 0.8359
11.000 1.4972 0.01884 0.01294 -0.0875 0.0617 1.0000
11.250 1.5074 0.01969 0.01377 -0.0852 0.0552 1.0000
11.500 1.5181 0.02055 0.01462 -0.0831 0.0499 1.0000
11.750 1.5277 0.02149 0.01556 -0.0810 0.0447 1.0000
12.000 1.5359 0.02256 0.01661 -0.0789 0.0399 1.0000
12.250 1.5455 0.02358 0.01765 -0.0770 0.0364 1.0000
12.500 1.5523 0.02483 0.01890 -0.0749 0.0324 1.0000
12.750 1.5606 0.02604 0.02013 -0.0732 0.0296 1.0000
13.000 1.5679 0.02736 0.02148 -0.0715 0.0272 1.0000
13.250 1.5730 0.02891 0.02305 -0.0697 0.0246 1.0000
13.500 1.5810 0.03029 0.02449 -0.0684 0.0230 1.0000
13.750 1.5860 0.03198 0.02621 -0.0669 0.0212 1.0000
14.000 1.5899 0.03384 0.02811 -0.0656 0.0196 1.0000
14.250 1.5964 0.03554 0.02987 -0.0645 0.0185 1.0000
14.500 1.6004 0.03753 0.03191 -0.0635 0.0174 1.0000
14.750 1.6019 0.03984 0.03427 -0.0626 0.0161 1.0000
15.000 1.6051 0.04208 0.03658 -0.0618 0.0154 1.0000
15.250 1.6091 0.04431 0.03889 -0.0613 0.0146 1.0000
15.500 1.6112 0.04682 0.04146 -0.0609 0.0138 1.0000
15.750 1.6112 0.04966 0.04436 -0.0606 0.0130 1.0000
16.000 1.6091 0.05286 0.04763 -0.0604 0.0122 1.0000
16.250 1.6112 0.05565 0.05050 -0.0605 0.0118 1.0000
16.500 1.6113 0.05876 0.05370 -0.0607 0.0113 1.0000
16.750 1.6104 0.06211 0.05712 -0.0610 0.0107 1.0000
17.000 1.6073 0.06583 0.06091 -0.0616 0.0102 1.0000
17.250 1.6020 0.06998 0.06515 -0.0624 0.0097 1.0000
17.500 1.5980 0.07405 0.06931 -0.0634 0.0093 1.0000
17.750 1.5959 0.07796 0.07332 -0.0644 0.0090 1.0000
18.000 1.5919 0.08221 0.07767 -0.0657 0.0087 1.0000
18.250 1.5869 0.08673 0.08229 -0.0671 0.0083 1.0000
18.500 1.5802 0.09158 0.08722 -0.0688 0.0080 1.0000
18.750 1.5719 0.09682 0.09256 -0.0708 0.0077 1.0000
19.000 1.5614 0.10253 0.09837 -0.0731 0.0074 1.0000
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Polar data table (+)
Polar graphs
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