EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 500,000 Max Cl/Cd: 106.66 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e604-il-500000.txt Download as CSV file: xf-e604-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3184 0.09952 0.09727 -0.0891 0.9857 0.0145
-13.250 -0.5550 0.04832 0.04468 -0.1175 0.9734 0.0102
-13.000 -0.5598 0.04389 0.03999 -0.1202 0.9613 0.0100
-12.750 -0.5598 0.03915 0.03491 -0.1238 0.9513 0.0099
-12.500 -0.5445 0.03521 0.03062 -0.1284 0.9440 0.0099
-12.250 -0.5201 0.03209 0.02718 -0.1330 0.9349 0.0101
-12.000 -0.4894 0.02961 0.02442 -0.1374 0.9247 0.0101
-11.750 -0.4600 0.02780 0.02236 -0.1406 0.9111 0.0101
-11.250 -0.4227 0.02536 0.01952 -0.1412 0.8807 0.0104
-11.000 -0.4089 0.02452 0.01848 -0.1402 0.8678 0.0108
-10.750 -0.3980 0.02333 0.01719 -0.1388 0.8568 0.0114
-10.500 -0.3847 0.02256 0.01632 -0.1376 0.8470 0.0115
-10.250 -0.3722 0.02182 0.01552 -0.1362 0.8378 0.0118
-10.000 -0.3589 0.02111 0.01471 -0.1349 0.8299 0.0123
-9.750 -0.3460 0.02043 0.01396 -0.1335 0.8221 0.0129
-9.500 -0.3324 0.01979 0.01321 -0.1321 0.8150 0.0133
-9.250 -0.3226 0.01896 0.01234 -0.1303 0.8082 0.0142
-9.000 -0.3111 0.01827 0.01159 -0.1286 0.8013 0.0148
-8.750 -0.2960 0.01775 0.01100 -0.1273 0.7955 0.0161
-8.500 -0.2863 0.01702 0.01023 -0.1253 0.7895 0.0174
-8.250 -0.2735 0.01646 0.00964 -0.1236 0.7840 0.0192
-8.000 -0.2620 0.01588 0.00900 -0.1217 0.7790 0.0219
-7.750 -0.2519 0.01544 0.00854 -0.1194 0.7737 0.0248
-7.500 -0.2421 0.01499 0.00808 -0.1171 0.7685 0.0280
-7.250 -0.2265 0.01454 0.00759 -0.1157 0.7641 0.0332
-7.000 -0.2099 0.01413 0.00720 -0.1144 0.7599 0.0394
-6.750 -0.1919 0.01373 0.00682 -0.1133 0.7556 0.0475
-6.500 -0.1725 0.01333 0.00643 -0.1125 0.7517 0.0586
-6.250 -0.1523 0.01291 0.00606 -0.1118 0.7480 0.0755
-6.000 -0.1321 0.01249 0.00574 -0.1111 0.7443 0.0995
-5.750 -0.1118 0.01200 0.00541 -0.1105 0.7404 0.1353
-5.500 -0.0916 0.01138 0.00503 -0.1100 0.7368 0.1917
-5.250 -0.0711 0.01059 0.00458 -0.1099 0.7336 0.2811
-5.000 -0.0500 0.00953 0.00403 -0.1102 0.7303 0.4182
-4.750 -0.0257 0.00898 0.00395 -0.1103 0.7270 0.5434
-4.500 0.0029 0.00901 0.00398 -0.1106 0.7237 0.5764
-4.250 0.0318 0.00910 0.00405 -0.1108 0.7206 0.5964
-4.000 0.0611 0.00923 0.00411 -0.1111 0.7177 0.6114
-3.750 0.0911 0.00941 0.00419 -0.1116 0.7148 0.6221
-3.500 0.1194 0.00952 0.00429 -0.1117 0.7119 0.6296
-3.250 0.1478 0.00963 0.00437 -0.1119 0.7089 0.6366
-3.000 0.1768 0.00972 0.00440 -0.1122 0.7058 0.6431
-2.750 0.2053 0.00987 0.00454 -0.1123 0.7029 0.6489
-2.500 0.2351 0.01009 0.00466 -0.1127 0.7002 0.6576
-2.250 0.2634 0.01033 0.00492 -0.1127 0.6975 0.6633
-2.000 0.2908 0.01049 0.00509 -0.1125 0.6946 0.6692
-1.750 0.3196 0.01059 0.00514 -0.1129 0.6916 0.6748
-1.500 0.3476 0.01061 0.00517 -0.1130 0.6887 0.6774
-1.250 0.3765 0.01063 0.00515 -0.1134 0.6859 0.6793
-1.000 0.4061 0.01067 0.00514 -0.1139 0.6833 0.6812
-0.750 0.4351 0.01072 0.00515 -0.1144 0.6806 0.6831
-0.500 0.4630 0.01071 0.00514 -0.1147 0.6776 0.6852
-0.250 0.4916 0.01070 0.00511 -0.1151 0.6745 0.6875
0.000 0.5210 0.01070 0.00506 -0.1158 0.6715 0.6894
0.250 0.5509 0.01071 0.00501 -0.1165 0.6688 0.6911
0.500 0.5807 0.01074 0.00500 -0.1171 0.6659 0.6928
0.750 0.6075 0.01074 0.00504 -0.1171 0.6630 0.6944
1.000 0.6348 0.01075 0.00508 -0.1173 0.6596 0.6961
1.250 0.6631 0.01076 0.00510 -0.1176 0.6564 0.6977
1.500 0.6920 0.01078 0.00510 -0.1180 0.6534 0.6994
1.750 0.7219 0.01085 0.00512 -0.1187 0.6504 0.7013
2.000 0.7494 0.01089 0.00518 -0.1190 0.6471 0.7033
2.250 0.7766 0.01091 0.00521 -0.1191 0.6435 0.7055
2.500 0.8050 0.01094 0.00523 -0.1195 0.6399 0.7076
2.750 0.8335 0.01092 0.00521 -0.1199 0.6364 0.7093
3.000 0.8622 0.01099 0.00527 -0.1203 0.6327 0.7109
3.250 0.8870 0.01098 0.00534 -0.1200 0.6283 0.7126
3.500 0.9136 0.01099 0.00538 -0.1199 0.6239 0.7144
3.750 0.9414 0.01102 0.00540 -0.1202 0.6198 0.7163
4.000 0.9686 0.01108 0.00547 -0.1203 0.6154 0.7185
4.250 0.9934 0.01110 0.00554 -0.1200 0.6102 0.7209
4.500 1.0200 0.01112 0.00556 -0.1200 0.6053 0.7233
4.750 1.0480 0.01119 0.00561 -0.1203 0.6006 0.7253
5.000 1.0706 0.01118 0.00570 -0.1195 0.5950 0.7272
5.250 1.0951 0.01121 0.00576 -0.1191 0.5894 0.7291
5.500 1.1204 0.01128 0.00584 -0.1188 0.5838 0.7311
5.750 1.1422 0.01131 0.00596 -0.1179 0.5770 0.7334
6.000 1.1666 0.01138 0.00601 -0.1175 0.5707 0.7358
6.250 1.1879 0.01145 0.00616 -0.1165 0.5633 0.7384
6.500 1.2099 0.01155 0.00624 -0.1156 0.5557 0.7409
6.750 1.2294 0.01161 0.00638 -0.1142 0.5471 0.7434
7.000 1.2471 0.01173 0.00649 -0.1125 0.5383 0.7458
7.250 1.2618 0.01183 0.00667 -0.1101 0.5282 0.7483
7.500 1.2767 0.01201 0.00687 -0.1079 0.5180 0.7510
7.750 1.2905 0.01228 0.00711 -0.1056 0.5067 0.7540
8.000 1.3044 0.01257 0.00741 -0.1033 0.4940 0.7569
8.250 1.3168 0.01290 0.00776 -0.1008 0.4805 0.7596
8.500 1.3271 0.01330 0.00817 -0.0981 0.4659 0.7623
8.750 1.3359 0.01380 0.00866 -0.0951 0.4503 0.7654
9.000 1.3427 0.01442 0.00925 -0.0920 0.4333 0.7690
9.250 1.3475 0.01518 0.00996 -0.0887 0.4152 0.7727
9.500 1.3502 0.01607 0.01079 -0.0853 0.3962 0.7759
9.750 1.3532 0.01702 0.01172 -0.0821 0.3766 0.7792
10.000 1.3544 0.01815 0.01281 -0.0789 0.3564 0.7827
10.250 1.3539 0.01948 0.01407 -0.0757 0.3361 0.7866
10.500 1.3539 0.02090 0.01542 -0.0727 0.3166 0.7903
10.750 1.3545 0.02234 0.01683 -0.0700 0.2972 0.7939
11.000 1.3550 0.02387 0.01833 -0.0674 0.2788 0.7979
11.250 1.3559 0.02549 0.01990 -0.0651 0.2614 0.8023
11.500 1.3577 0.02715 0.02151 -0.0631 0.2451 0.8068
11.750 1.3584 0.02888 0.02322 -0.0610 0.2287 0.8110
12.000 1.3600 0.03066 0.02497 -0.0591 0.2131 0.8156
12.250 1.3630 0.03242 0.02671 -0.0576 0.1987 0.8205
12.500 1.3652 0.03429 0.02856 -0.0560 0.1842 0.8252
12.750 1.3679 0.03615 0.03042 -0.0546 0.1709 0.8304
13.000 1.3712 0.03808 0.03233 -0.0534 0.1583 0.8362
13.250 1.3741 0.04006 0.03431 -0.0522 0.1464 0.8421
13.500 1.3763 0.04213 0.03638 -0.0511 0.1357 0.8490
13.750 1.3798 0.04414 0.03840 -0.0501 0.1248 0.8567
14.000 1.3841 0.04608 0.04039 -0.0491 0.1158 0.8661
14.250 1.3864 0.04821 0.04256 -0.0482 0.1071 0.8773
14.500 1.3883 0.05032 0.04472 -0.0471 0.0989 0.8935
14.750 1.3918 0.05231 0.04683 -0.0463 0.0913 0.9380
15.000 1.3940 0.05474 0.04925 -0.0460 0.0840 1.0000
15.250 1.3989 0.05712 0.05164 -0.0459 0.0771 1.0000
15.500 1.4027 0.05962 0.05415 -0.0458 0.0710 1.0000
15.750 1.4049 0.06235 0.05688 -0.0457 0.0648 1.0000
16.000 1.4088 0.06493 0.05949 -0.0457 0.0596 1.0000
16.250 1.4096 0.06791 0.06246 -0.0458 0.0545 1.0000
16.500 1.4129 0.07063 0.06524 -0.0460 0.0502 1.0000
16.750 1.4129 0.07379 0.06840 -0.0462 0.0460 1.0000
17.000 1.4152 0.07674 0.07141 -0.0465 0.0426 1.0000
17.250 1.4154 0.08001 0.07471 -0.0470 0.0394 1.0000
17.500 1.4155 0.08334 0.07809 -0.0475 0.0365 1.0000
17.750 1.4164 0.08660 0.08140 -0.0481 0.0337 1.0000
18.250 1.4150 0.09373 0.08866 -0.0497 0.0294 1.0000
18.500 1.4134 0.09749 0.09247 -0.0507 0.0275 1.0000
18.750 1.4090 0.10173 0.09677 -0.0519 0.0257 1.0000
19.000 1.4104 0.10511 0.10024 -0.0530 0.0241 1.0000
19.250 1.4078 0.10914 0.10434 -0.0543 0.0228 1.0000
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Polar data table (+)
Polar graphs
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