EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.81 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e603-il-1000000-n5.txt Download as CSV file: xf-e603-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 603 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.6606 0.12181 0.11945 -0.0566 1.0000 0.0055
-18.500 -0.7187 0.10671 0.10415 -0.0641 1.0000 0.0055
-18.250 -0.7567 0.09576 0.09305 -0.0698 1.0000 0.0054
-18.000 -0.7999 0.08365 0.08074 -0.0767 0.9998 0.0054
-17.750 -0.8276 0.07529 0.07223 -0.0806 0.9914 0.0053
-17.500 -0.8300 0.06584 0.06255 -0.0917 0.9623 0.0054
-17.250 -0.7976 0.05686 0.05326 -0.1091 0.9326 0.0054
-17.000 -0.7836 0.05159 0.04735 -0.1173 0.8255 0.0055
-16.750 -0.7918 0.04835 0.04386 -0.1176 0.7920 0.0055
-16.500 -0.7928 0.04584 0.04118 -0.1179 0.7713 0.0055
-16.000 -0.7932 0.04110 0.03615 -0.1181 0.7437 0.0056
-15.750 -0.7948 0.03877 0.03368 -0.1178 0.7337 0.0056
-15.500 -0.7892 0.03714 0.03193 -0.1175 0.7241 0.0057
-15.250 -0.7841 0.03551 0.03019 -0.1171 0.7165 0.0057
-15.000 -0.7825 0.03367 0.02824 -0.1163 0.7091 0.0058
-14.750 -0.7721 0.03258 0.02705 -0.1158 0.7024 0.0058
-14.500 -0.7641 0.03133 0.02572 -0.1151 0.6966 0.0058
-14.250 -0.7617 0.02973 0.02401 -0.1139 0.6903 0.0059
-14.000 -0.7566 0.02838 0.02256 -0.1128 0.6849 0.0061
-13.750 -0.7484 0.02723 0.02133 -0.1118 0.6803 0.0062
-13.500 -0.7401 0.02612 0.02013 -0.1106 0.6751 0.0062
-13.250 -0.7284 0.02526 0.01920 -0.1097 0.6707 0.0063
-13.000 -0.7168 0.02437 0.01825 -0.1086 0.6671 0.0064
-12.750 -0.7033 0.02361 0.01744 -0.1077 0.6637 0.0065
-12.500 -0.6903 0.02282 0.01659 -0.1066 0.6600 0.0066
-12.250 -0.6758 0.02215 0.01586 -0.1057 0.6566 0.0067
-12.000 -0.6614 0.02149 0.01514 -0.1046 0.6532 0.0069
-11.750 -0.6465 0.02083 0.01443 -0.1036 0.6506 0.0069
-11.500 -0.6306 0.02023 0.01378 -0.1026 0.6480 0.0071
-11.250 -0.6140 0.01969 0.01319 -0.1017 0.6454 0.0073
-11.000 -0.5983 0.01909 0.01254 -0.1006 0.6427 0.0074
-10.750 -0.5823 0.01853 0.01192 -0.0995 0.6399 0.0074
-10.500 -0.5645 0.01809 0.01144 -0.0986 0.6371 0.0076
-10.250 -0.5470 0.01763 0.01093 -0.0977 0.6347 0.0077
-10.000 -0.5290 0.01717 0.01043 -0.0967 0.6327 0.0079
-9.750 -0.5119 0.01666 0.00988 -0.0956 0.6307 0.0081
-9.500 -0.4947 0.01617 0.00937 -0.0945 0.6287 0.0083
-9.250 -0.4768 0.01574 0.00891 -0.0935 0.6267 0.0085
-9.000 -0.4587 0.01533 0.00848 -0.0924 0.6247 0.0090
-8.750 -0.4406 0.01494 0.00806 -0.0913 0.6227 0.0091
-8.500 -0.4224 0.01458 0.00767 -0.0902 0.6208 0.0095
-8.000 -0.3867 0.01392 0.00695 -0.0877 0.6174 0.0102
-7.750 -0.3716 0.01360 0.00662 -0.0860 0.6161 0.0108
-7.500 -0.3551 0.01331 0.00633 -0.0845 0.6144 0.0115
-7.250 -0.3348 0.01302 0.00603 -0.0837 0.6127 0.0123
-7.000 -0.3132 0.01276 0.00574 -0.0830 0.6109 0.0131
-6.750 -0.2914 0.01249 0.00547 -0.0824 0.6093 0.0147
-6.500 -0.2685 0.01226 0.00523 -0.0819 0.6078 0.0163
-6.250 -0.2454 0.01202 0.00499 -0.0815 0.6062 0.0186
-6.000 -0.2217 0.01180 0.00477 -0.0811 0.6047 0.0212
-5.750 -0.1974 0.01161 0.00456 -0.0808 0.6031 0.0241
-5.500 -0.1731 0.01139 0.00436 -0.0806 0.6015 0.0289
-5.250 -0.1480 0.01116 0.00416 -0.0804 0.6004 0.0349
-5.000 -0.1227 0.01092 0.00397 -0.0804 0.5991 0.0438
-4.750 -0.0970 0.01070 0.00379 -0.0804 0.5978 0.0543
-4.500 -0.0709 0.01048 0.00362 -0.0804 0.5965 0.0662
-4.250 -0.0450 0.01023 0.00345 -0.0805 0.5951 0.0847
-4.000 -0.0192 0.00994 0.00327 -0.0806 0.5936 0.1128
-3.750 0.0068 0.00963 0.00309 -0.0808 0.5919 0.1494
-3.500 0.0333 0.00930 0.00291 -0.0811 0.5904 0.1922
-3.250 0.0601 0.00896 0.00274 -0.0815 0.5890 0.2435
-3.000 0.0869 0.00844 0.00251 -0.0821 0.5874 0.3288
-2.750 0.1146 0.00762 0.00217 -0.0833 0.5856 0.4677
-2.500 0.1447 0.00700 0.00196 -0.0846 0.5844 0.5858
-2.250 0.1748 0.00690 0.00197 -0.0853 0.5833 0.6274
-2.000 0.2049 0.00691 0.00199 -0.0859 0.5820 0.6451
-1.750 0.2349 0.00693 0.00203 -0.0865 0.5805 0.6592
-1.500 0.2648 0.00698 0.00208 -0.0870 0.5790 0.6705
-1.250 0.2947 0.00705 0.00213 -0.0875 0.5774 0.6806
-1.000 0.3243 0.00716 0.00223 -0.0880 0.5758 0.6892
-0.750 0.3542 0.00724 0.00228 -0.0885 0.5741 0.6947
-0.500 0.3835 0.00728 0.00231 -0.0890 0.5725 0.6973
-0.250 0.4129 0.00732 0.00232 -0.0895 0.5707 0.6983
0.000 0.4423 0.00737 0.00233 -0.0900 0.5688 0.6993
0.250 0.4721 0.00738 0.00235 -0.0906 0.5675 0.7004
0.500 0.5018 0.00740 0.00237 -0.0911 0.5660 0.7016
0.750 0.5315 0.00742 0.00239 -0.0917 0.5642 0.7026
1.000 0.5611 0.00745 0.00240 -0.0923 0.5623 0.7036
1.250 0.5905 0.00748 0.00242 -0.0928 0.5602 0.7046
1.500 0.6198 0.00751 0.00245 -0.0933 0.5581 0.7057
1.750 0.6489 0.00756 0.00247 -0.0938 0.5559 0.7068
2.000 0.6778 0.00762 0.00250 -0.0942 0.5536 0.7078
2.250 0.7072 0.00765 0.00254 -0.0948 0.5516 0.7087
2.500 0.7367 0.00767 0.00258 -0.0954 0.5492 0.7094
2.750 0.7659 0.00771 0.00262 -0.0959 0.5465 0.7101
3.000 0.7949 0.00775 0.00266 -0.0963 0.5435 0.7108
3.250 0.8233 0.00779 0.00270 -0.0967 0.5403 0.7120
3.500 0.8514 0.00784 0.00275 -0.0970 0.5367 0.7131
3.750 0.8803 0.00787 0.00282 -0.0975 0.5327 0.7140
4.000 0.9086 0.00792 0.00287 -0.0978 0.5278 0.7149
4.250 0.9360 0.00799 0.00294 -0.0980 0.5228 0.7157
4.500 0.9643 0.00805 0.00302 -0.0984 0.5180 0.7165
4.750 0.9920 0.00812 0.00310 -0.0986 0.5117 0.7174
5.000 1.0188 0.00822 0.00319 -0.0987 0.5052 0.7183
5.250 1.0460 0.00832 0.00329 -0.0989 0.4970 0.7193
5.500 1.0719 0.00845 0.00341 -0.0988 0.4882 0.7204
5.750 1.0971 0.00861 0.00354 -0.0987 0.4773 0.7214
6.000 1.1222 0.00878 0.00369 -0.0984 0.4658 0.7223
6.250 1.1461 0.00898 0.00387 -0.0980 0.4536 0.7232
6.500 1.1685 0.00924 0.00408 -0.0974 0.4393 0.7241
6.750 1.1896 0.00954 0.00432 -0.0965 0.4229 0.7250
7.000 1.2091 0.00988 0.00459 -0.0953 0.4051 0.7258
7.250 1.2262 0.01028 0.00492 -0.0937 0.3856 0.7266
7.500 1.2409 0.01069 0.00525 -0.0917 0.3676 0.7274
7.750 1.2517 0.01110 0.00560 -0.0889 0.3492 0.7285
8.000 1.2624 0.01158 0.00602 -0.0861 0.3314 0.7299
8.250 1.2708 0.01216 0.00654 -0.0831 0.3117 0.7311
8.500 1.2781 0.01280 0.00712 -0.0801 0.2928 0.7322
8.750 1.2837 0.01353 0.00778 -0.0769 0.2748 0.7334
9.000 1.2880 0.01437 0.00855 -0.0737 0.2576 0.7345
9.250 1.2910 0.01533 0.00945 -0.0706 0.2404 0.7357
9.500 1.2937 0.01641 0.01049 -0.0677 0.2245 0.7368
9.750 1.2997 0.01746 0.01152 -0.0654 0.2130 0.7379
10.000 1.3024 0.01877 0.01279 -0.0630 0.1988 0.7391
10.250 1.3081 0.02003 0.01403 -0.0611 0.1880 0.7402
10.500 1.3094 0.02162 0.01557 -0.0590 0.1736 0.7414
10.750 1.3091 0.02342 0.01731 -0.0569 0.1580 0.7426
11.000 1.3141 0.02493 0.01881 -0.0554 0.1488 0.7436
11.250 1.3154 0.02674 0.02057 -0.0537 0.1361 0.7445
11.500 1.3175 0.02853 0.02232 -0.0521 0.1250 0.7454
11.750 1.3218 0.03020 0.02398 -0.0508 0.1151 0.7466
12.000 1.3261 0.03191 0.02568 -0.0496 0.1061 0.7478
12.250 1.3287 0.03380 0.02755 -0.0484 0.0966 0.7489
12.500 1.3324 0.03566 0.02939 -0.0473 0.0881 0.7500
12.750 1.3385 0.03737 0.03111 -0.0465 0.0811 0.7511
13.000 1.3433 0.03924 0.03297 -0.0457 0.0747 0.7522
13.250 1.3501 0.04099 0.03473 -0.0450 0.0689 0.7533
13.500 1.3558 0.04287 0.03661 -0.0444 0.0636 0.7544
13.750 1.3627 0.04467 0.03844 -0.0439 0.0589 0.7555
14.000 1.3689 0.04659 0.04036 -0.0434 0.0542 0.7566
14.250 1.3731 0.04874 0.04250 -0.0429 0.0485 0.7577
14.500 1.3814 0.05053 0.04432 -0.0426 0.0454 0.7588
14.750 1.3850 0.05282 0.04661 -0.0423 0.0406 0.7597
15.000 1.3923 0.05477 0.04858 -0.0421 0.0374 0.7608
15.250 1.3972 0.05703 0.05085 -0.0419 0.0341 0.7618
15.500 1.4034 0.05917 0.05303 -0.0418 0.0312 0.7631
15.750 1.4081 0.06150 0.05538 -0.0418 0.0281 0.7645
16.000 1.4130 0.06386 0.05779 -0.0418 0.0253 0.7658
16.250 1.4177 0.06627 0.06022 -0.0419 0.0226 0.7670
16.500 1.4209 0.06893 0.06292 -0.0420 0.0202 0.7683
16.750 1.4252 0.07148 0.06551 -0.0422 0.0178 0.7696
17.000 1.4273 0.07435 0.06842 -0.0425 0.0158 0.7708
17.250 1.4314 0.07700 0.07112 -0.0429 0.0143 0.7721
17.500 1.4336 0.07997 0.07413 -0.0434 0.0131 0.7734
17.750 1.4380 0.08267 0.07689 -0.0439 0.0123 0.7747
18.000 1.4401 0.08573 0.08000 -0.0445 0.0114 0.7759
18.250 1.4425 0.08876 0.08308 -0.0451 0.0107 0.7771
18.500 1.4447 0.09186 0.08625 -0.0459 0.0101 0.7782
19.000 1.4490 0.09820 0.09274 -0.0477 0.0093 0.7810
19.250 1.4505 0.10150 0.09612 -0.0487 0.0089 0.7825
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 603 AIRFOIL (e603-il)