EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.28 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e604-il-1000000.txt Download as CSV file: xf-e604-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 604 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5821 0.09543 0.09324 -0.0770 1.0000 0.0060
-16.000 -0.6278 0.08266 0.08026 -0.0837 1.0000 0.0059
-15.750 -0.6526 0.07492 0.07238 -0.0876 1.0000 0.0059
-15.500 -0.6672 0.06698 0.06426 -0.0939 0.9992 0.0058
-15.250 -0.6763 0.06005 0.05715 -0.1000 0.9979 0.0058
-15.000 -0.6813 0.05413 0.05103 -0.1053 0.9959 0.0057
-14.750 -0.6882 0.04851 0.04518 -0.1098 0.9930 0.0057
-14.500 -0.6864 0.04460 0.04111 -0.1127 0.9888 0.0057
-14.250 -0.6826 0.04085 0.03719 -0.1158 0.9841 0.0057
-14.000 -0.6770 0.03830 0.03452 -0.1170 0.9726 0.0057
-13.750 -0.6671 0.03537 0.03142 -0.1196 0.9593 0.0057
-13.500 -0.6427 0.03257 0.02844 -0.1245 0.9487 0.0057
-13.250 -0.6055 0.03010 0.02580 -0.1314 0.9409 0.0057
-13.000 -0.5640 0.02793 0.02344 -0.1386 0.9288 0.0057
-12.750 -0.5331 0.02607 0.02134 -0.1432 0.9064 0.0058
-12.500 -0.5201 0.02487 0.01993 -0.1432 0.8823 0.0059
-12.250 -0.5108 0.02394 0.01884 -0.1420 0.8643 0.0061
-12.000 -0.5025 0.02301 0.01778 -0.1405 0.8495 0.0060
-11.750 -0.4933 0.02215 0.01681 -0.1391 0.8375 0.0060
-11.500 -0.4834 0.02134 0.01589 -0.1376 0.8268 0.0060
-11.250 -0.4731 0.02054 0.01500 -0.1361 0.8171 0.0061
-11.000 -0.4611 0.01984 0.01420 -0.1347 0.8088 0.0063
-10.750 -0.4535 0.01890 0.01316 -0.1329 0.8003 0.0065
-10.500 -0.4424 0.01818 0.01236 -0.1313 0.7931 0.0066
-10.250 -0.4313 0.01746 0.01157 -0.1297 0.7857 0.0067
-10.000 -0.4206 0.01676 0.01080 -0.1279 0.7788 0.0070
-9.750 -0.4064 0.01620 0.01020 -0.1266 0.7727 0.0073
-9.500 -0.3922 0.01570 0.00964 -0.1251 0.7665 0.0075
-9.250 -0.3773 0.01522 0.00911 -0.1237 0.7613 0.0082
-9.000 -0.3637 0.01469 0.00853 -0.1221 0.7560 0.0082
-8.750 -0.3533 0.01411 0.00790 -0.1200 0.7506 0.0092
-8.500 -0.3428 0.01368 0.00742 -0.1177 0.7455 0.0098
-8.250 -0.3303 0.01334 0.00705 -0.1157 0.7409 0.0108
-8.000 -0.3149 0.01289 0.00658 -0.1142 0.7361 0.0126
-7.750 -0.2966 0.01256 0.00620 -0.1131 0.7318 0.0147
-7.500 -0.2757 0.01226 0.00589 -0.1124 0.7281 0.0170
-7.250 -0.2547 0.01193 0.00557 -0.1117 0.7244 0.0207
-7.000 -0.2327 0.01164 0.00527 -0.1111 0.7206 0.0245
-6.750 -0.2102 0.01138 0.00500 -0.1106 0.7167 0.0293
-6.500 -0.1868 0.01112 0.00474 -0.1102 0.7131 0.0353
-6.250 -0.1630 0.01083 0.00450 -0.1100 0.7100 0.0435
-6.000 -0.1389 0.01053 0.00425 -0.1098 0.7068 0.0557
-5.750 -0.1147 0.01023 0.00401 -0.1096 0.7034 0.0729
-5.500 -0.0900 0.00994 0.00379 -0.1095 0.6999 0.0949
-5.250 -0.0655 0.00956 0.00355 -0.1096 0.6968 0.1301
-5.000 -0.0410 0.00907 0.00328 -0.1097 0.6941 0.1845
-4.750 -0.0162 0.00846 0.00297 -0.1100 0.6911 0.2607
-4.500 0.0091 0.00776 0.00262 -0.1105 0.6881 0.3617
-4.250 0.0354 0.00691 0.00227 -0.1114 0.6851 0.5059
-4.000 0.0646 0.00682 0.00225 -0.1119 0.6818 0.5529
-3.750 0.0941 0.00680 0.00224 -0.1124 0.6796 0.5761
-3.500 0.1235 0.00680 0.00224 -0.1129 0.6769 0.5906
-3.250 0.1529 0.00681 0.00225 -0.1133 0.6742 0.5997
-3.000 0.1824 0.00686 0.00224 -0.1138 0.6715 0.6072
-2.750 0.2116 0.00689 0.00223 -0.1142 0.6687 0.6126
-2.500 0.2412 0.00699 0.00228 -0.1147 0.6655 0.6187
-2.250 0.2707 0.00703 0.00229 -0.1152 0.6635 0.6243
-2.000 0.2997 0.00705 0.00234 -0.1155 0.6610 0.6312
-1.750 0.3289 0.00713 0.00240 -0.1159 0.6583 0.6376
-1.500 0.3581 0.00720 0.00244 -0.1163 0.6557 0.6435
-1.250 0.3869 0.00727 0.00251 -0.1166 0.6530 0.6482
-1.000 0.4163 0.00736 0.00255 -0.1171 0.6498 0.6508
-0.750 0.4454 0.00737 0.00255 -0.1175 0.6476 0.6527
-0.500 0.4744 0.00737 0.00255 -0.1180 0.6450 0.6545
-0.250 0.5035 0.00739 0.00254 -0.1184 0.6423 0.6560
0.000 0.5326 0.00742 0.00254 -0.1189 0.6395 0.6573
0.250 0.5614 0.00743 0.00253 -0.1193 0.6366 0.6591
0.500 0.5904 0.00749 0.00256 -0.1198 0.6333 0.6610
0.750 0.6189 0.00748 0.00258 -0.1201 0.6310 0.6627
1.000 0.6475 0.00750 0.00261 -0.1204 0.6281 0.6643
1.250 0.6760 0.00752 0.00264 -0.1208 0.6251 0.6659
1.500 0.7044 0.00756 0.00267 -0.1211 0.6220 0.6676
1.750 0.7328 0.00763 0.00271 -0.1215 0.6185 0.6693
2.000 0.7612 0.00767 0.00276 -0.1218 0.6154 0.6711
2.250 0.7892 0.00769 0.00279 -0.1220 0.6117 0.6728
2.500 0.8171 0.00773 0.00282 -0.1223 0.6078 0.6742
2.750 0.8445 0.00776 0.00285 -0.1224 0.6038 0.6762
3.000 0.8720 0.00780 0.00291 -0.1226 0.5998 0.6781
3.250 0.8993 0.00781 0.00296 -0.1227 0.5955 0.6798
3.500 0.9263 0.00786 0.00302 -0.1228 0.5908 0.6816
3.750 0.9527 0.00796 0.00309 -0.1227 0.5859 0.6834
4.000 0.9799 0.00798 0.00316 -0.1228 0.5815 0.6853
4.250 1.0065 0.00803 0.00323 -0.1228 0.5762 0.6873
4.500 1.0319 0.00814 0.00331 -0.1226 0.5707 0.6892
4.750 1.0585 0.00820 0.00340 -0.1226 0.5651 0.6908
5.000 1.0837 0.00825 0.00347 -0.1223 0.5584 0.6931
5.250 1.1081 0.00833 0.00357 -0.1219 0.5520 0.6952
5.500 1.1329 0.00841 0.00368 -0.1215 0.5444 0.6971
5.750 1.1558 0.00854 0.00380 -0.1208 0.5365 0.6992
6.000 1.1787 0.00866 0.00393 -0.1201 0.5270 0.7013
6.250 1.1993 0.00880 0.00407 -0.1189 0.5172 0.7035
6.500 1.2166 0.00898 0.00422 -0.1171 0.5058 0.7056
6.750 1.2347 0.00918 0.00440 -0.1154 0.4940 0.7075
7.000 1.2527 0.00939 0.00461 -0.1138 0.4814 0.7102
7.250 1.2687 0.00967 0.00488 -0.1118 0.4674 0.7128
7.500 1.2836 0.01000 0.00518 -0.1097 0.4525 0.7152
7.750 1.2975 0.01038 0.00552 -0.1074 0.4368 0.7176
8.000 1.3093 0.01083 0.00592 -0.1049 0.4187 0.7202
8.250 1.3186 0.01138 0.00639 -0.1019 0.3993 0.7226
8.500 1.3267 0.01200 0.00693 -0.0989 0.3793 0.7247
8.750 1.3341 0.01265 0.00753 -0.0959 0.3582 0.7278
9.000 1.3393 0.01344 0.00825 -0.0926 0.3372 0.7306
9.250 1.3437 0.01432 0.00906 -0.0894 0.3170 0.7335
9.500 1.3488 0.01525 0.00993 -0.0865 0.2971 0.7365
9.750 1.3528 0.01630 0.01090 -0.0835 0.2774 0.7394
10.000 1.3571 0.01740 0.01192 -0.0808 0.2595 0.7422
10.250 1.3600 0.01861 0.01308 -0.0780 0.2412 0.7455
10.500 1.3654 0.01977 0.01421 -0.0757 0.2260 0.7486
10.750 1.3693 0.02108 0.01546 -0.0733 0.2099 0.7518
11.000 1.3750 0.02234 0.01669 -0.0713 0.1960 0.7549
11.250 1.3788 0.02377 0.01806 -0.0692 0.1807 0.7577
11.500 1.3836 0.02518 0.01944 -0.0673 0.1668 0.7613
11.750 1.3894 0.02658 0.02083 -0.0656 0.1548 0.7648
12.000 1.3942 0.02810 0.02232 -0.0639 0.1425 0.7684
12.250 1.4004 0.02958 0.02379 -0.0624 0.1326 0.7721
12.500 1.4051 0.03121 0.02539 -0.0609 0.1221 0.7758
12.750 1.4103 0.03284 0.02702 -0.0596 0.1122 0.7799
13.000 1.4176 0.03436 0.02855 -0.0585 0.1043 0.7841
13.250 1.4223 0.03615 0.03032 -0.0573 0.0956 0.7883
13.500 1.4276 0.03792 0.03209 -0.0562 0.0876 0.7924
13.750 1.4335 0.03967 0.03386 -0.0552 0.0798 0.7970
14.000 1.4378 0.04162 0.03581 -0.0542 0.0730 0.8020
14.250 1.4439 0.04347 0.03766 -0.0535 0.0665 0.8070
14.500 1.4491 0.04542 0.03964 -0.0527 0.0610 0.8129
14.750 1.4527 0.04755 0.04177 -0.0520 0.0545 0.8193
15.000 1.4578 0.04960 0.04386 -0.0514 0.0492 0.8262
15.250 1.4617 0.05179 0.04608 -0.0508 0.0446 0.8345
15.500 1.4659 0.05401 0.04834 -0.0503 0.0400 0.8436
16.000 1.4736 0.05854 0.05299 -0.0494 0.0332 0.8708
16.250 1.4759 0.06076 0.05534 -0.0487 0.0303 0.9025
16.500 1.4793 0.06298 0.05770 -0.0484 0.0280 1.0000
16.750 1.4823 0.06564 0.06039 -0.0484 0.0257 1.0000
17.000 1.4873 0.06811 0.06290 -0.0485 0.0239 1.0000
17.250 1.4885 0.07107 0.06589 -0.0487 0.0217 1.0000
17.500 1.4933 0.07362 0.06849 -0.0489 0.0203 1.0000
17.750 1.4954 0.07657 0.07149 -0.0492 0.0191 1.0000
18.000 1.4963 0.07970 0.07466 -0.0496 0.0176 1.0000
18.250 1.4995 0.08260 0.07763 -0.0501 0.0166 1.0000
18.500 1.5004 0.08582 0.08089 -0.0507 0.0154 1.0000
18.750 1.4998 0.08929 0.08441 -0.0514 0.0143 1.0000
19.000 1.5016 0.09248 0.08767 -0.0522 0.0135 1.0000
19.250 1.5021 0.09588 0.09114 -0.0531 0.0128 1.0000
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Polar data table (+)
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