EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 500,000 Max Cl/Cd: 122.96 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e668-il-500000.txt Download as CSV file: xf-e668-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 668 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0515 0.08640 0.08354 -0.1169 0.8763 0.0207
-11.250 -0.0633 0.07894 0.07610 -0.1206 0.8750 0.0211
-11.000 -0.0693 0.07316 0.07034 -0.1226 0.8738 0.0213
-10.750 -0.0659 0.06998 0.06716 -0.1234 0.8725 0.0215
-10.500 -0.0615 0.06718 0.06437 -0.1240 0.8711 0.0218
-10.250 -0.0624 0.06306 0.06026 -0.1256 0.8697 0.0219
-10.000 -0.0652 0.05874 0.05594 -0.1272 0.8681 0.0222
-9.750 -0.0743 0.05300 0.05021 -0.1298 0.8663 0.0224
-9.500 -0.1242 0.03828 0.03542 -0.1407 0.8643 0.0220
-9.250 -0.2975 0.03358 0.02955 -0.1439 0.8606 0.0115
-9.000 -0.2899 0.03169 0.02758 -0.1424 0.8587 0.0107
-8.750 -0.3151 0.02500 0.01993 -0.1374 0.8554 0.0089
-8.500 -0.3014 0.02324 0.01782 -0.1360 0.8536 0.0088
-8.250 -0.2837 0.02186 0.01620 -0.1350 0.8521 0.0087
-8.000 -0.2640 0.02073 0.01486 -0.1342 0.8506 0.0087
-7.750 -0.2455 0.01920 0.01314 -0.1333 0.8492 0.0088
-7.500 -0.2263 0.01788 0.01173 -0.1324 0.8476 0.0090
-7.250 -0.2047 0.01711 0.01089 -0.1317 0.8459 0.0093
-7.000 -0.1822 0.01645 0.01017 -0.1312 0.8442 0.0098
-6.750 -0.1592 0.01585 0.00950 -0.1307 0.8426 0.0105
-6.500 -0.1356 0.01529 0.00884 -0.1302 0.8411 0.0113
-6.250 -0.1125 0.01467 0.00821 -0.1298 0.8394 0.0127
-6.000 -0.0880 0.01415 0.00762 -0.1295 0.8378 0.0146
-5.750 -0.0626 0.01373 0.00716 -0.1293 0.8364 0.0178
-5.500 -0.0371 0.01342 0.00685 -0.1292 0.8350 0.0235
-5.250 -0.0118 0.01318 0.00661 -0.1290 0.8335 0.0310
-5.000 0.0131 0.01284 0.00635 -0.1289 0.8316 0.0415
-4.750 0.0383 0.01250 0.00609 -0.1287 0.8296 0.0569
-4.500 0.0640 0.01216 0.00587 -0.1287 0.8277 0.0846
-4.250 0.0900 0.01182 0.00568 -0.1288 0.8257 0.1252
-4.000 0.1167 0.01149 0.00552 -0.1290 0.8239 0.1749
-3.750 0.1437 0.01116 0.00538 -0.1292 0.8222 0.2326
-3.500 0.1711 0.01085 0.00526 -0.1296 0.8206 0.2999
-3.250 0.1983 0.01059 0.00525 -0.1299 0.8189 0.3796
-3.000 0.2235 0.01022 0.00520 -0.1299 0.8166 0.4689
-2.750 0.2496 0.00990 0.00518 -0.1300 0.8140 0.5590
-2.500 0.2762 0.00969 0.00521 -0.1299 0.8116 0.6385
-2.250 0.3033 0.00962 0.00528 -0.1297 0.8094 0.6909
-2.000 0.3314 0.00964 0.00534 -0.1296 0.8074 0.7260
-1.750 0.3601 0.00971 0.00538 -0.1296 0.8055 0.7482
-1.500 0.3892 0.00984 0.00547 -0.1298 0.8037 0.7646
-1.250 0.4148 0.00994 0.00556 -0.1294 0.8006 0.7781
-1.000 0.4407 0.01003 0.00567 -0.1289 0.7974 0.7886
-0.750 0.4681 0.01008 0.00570 -0.1287 0.7946 0.7980
-0.500 0.4966 0.01011 0.00570 -0.1287 0.7922 0.8068
-0.250 0.5252 0.01010 0.00567 -0.1287 0.7901 0.8137
0.000 0.5544 0.01016 0.00568 -0.1288 0.7881 0.8210
0.250 0.5788 0.01020 0.00575 -0.1282 0.7842 0.8280
0.500 0.6041 0.01019 0.00577 -0.1276 0.7804 0.8340
0.750 0.6333 0.01014 0.00569 -0.1278 0.7774 0.8407
1.000 0.6609 0.01004 0.00559 -0.1276 0.7748 0.8454
1.250 0.6905 0.00999 0.00551 -0.1278 0.7725 0.8509
1.500 0.7148 0.00999 0.00555 -0.1272 0.7677 0.8571
1.750 0.7397 0.00988 0.00548 -0.1265 0.7636 0.8615
2.000 0.7680 0.00974 0.00534 -0.1265 0.7602 0.8665
2.250 0.7996 0.00963 0.00518 -0.1272 0.7573 0.8715
2.500 0.8205 0.00955 0.00518 -0.1258 0.7514 0.8757
2.750 0.8470 0.00940 0.00506 -0.1255 0.7466 0.8798
3.000 0.8771 0.00923 0.00487 -0.1259 0.7427 0.8838
3.250 0.9011 0.00916 0.00486 -0.1252 0.7352 0.8876
3.500 0.9273 0.00897 0.00469 -0.1248 0.7293 0.8907
3.750 0.9508 0.00890 0.00467 -0.1240 0.7210 0.8941
4.000 0.9783 0.00878 0.00453 -0.1239 0.7135 0.8974
4.250 1.0028 0.00876 0.00455 -0.1234 0.7021 0.9008
4.500 1.0264 0.00871 0.00451 -0.1226 0.6898 0.9038
4.750 1.0487 0.00870 0.00449 -0.1215 0.6751 0.9070
5.000 1.0707 0.00875 0.00451 -0.1204 0.6581 0.9105
5.250 1.0919 0.00888 0.00458 -0.1191 0.6379 0.9142
5.500 1.1103 0.00906 0.00470 -0.1174 0.6132 0.9177
5.750 1.1241 0.00930 0.00484 -0.1147 0.5874 0.9220
6.000 1.1354 0.00963 0.00507 -0.1116 0.5598 0.9271
6.250 1.1428 0.00996 0.00531 -0.1077 0.5333 0.9327
6.500 1.1484 0.01033 0.00561 -0.1035 0.5078 0.9396
6.750 1.1534 0.01079 0.00598 -0.0994 0.4831 0.9479
7.000 1.1599 0.01122 0.00637 -0.0957 0.4587 0.9590
7.250 1.1726 0.01179 0.00686 -0.0936 0.4309 0.9951
7.500 1.1849 0.01254 0.00750 -0.0917 0.4035 1.0000
7.750 1.1968 0.01335 0.00819 -0.0899 0.3758 1.0000
8.000 1.2088 0.01419 0.00892 -0.0881 0.3480 1.0000
8.250 1.2201 0.01510 0.00971 -0.0862 0.3207 1.0000
8.500 1.2313 0.01604 0.01053 -0.0844 0.2950 1.0000
8.750 1.2433 0.01695 0.01134 -0.0828 0.2696 1.0000
9.000 1.2546 0.01793 0.01220 -0.0810 0.2446 1.0000
9.250 1.2648 0.01898 0.01313 -0.0792 0.2201 1.0000
9.500 1.2763 0.01997 0.01402 -0.0776 0.1961 1.0000
9.750 1.2867 0.02105 0.01499 -0.0759 0.1752 1.0000
10.000 1.2986 0.02205 0.01592 -0.0744 0.1556 1.0000
10.250 1.3096 0.02313 0.01691 -0.0728 0.1377 1.0000
10.500 1.3202 0.02424 0.01795 -0.0712 0.1212 1.0000
10.750 1.3303 0.02541 0.01905 -0.0697 0.1061 1.0000
11.000 1.3408 0.02657 0.02017 -0.0682 0.0932 1.0000
11.250 1.3511 0.02777 0.02133 -0.0667 0.0814 1.0000
11.500 1.3609 0.02903 0.02256 -0.0653 0.0710 1.0000
11.750 1.3710 0.03029 0.02382 -0.0639 0.0620 1.0000
12.000 1.3802 0.03164 0.02517 -0.0625 0.0542 1.0000
12.250 1.3885 0.03310 0.02662 -0.0611 0.0475 1.0000
12.500 1.3946 0.03478 0.02828 -0.0596 0.0415 1.0000
12.750 1.4044 0.03617 0.02972 -0.0584 0.0370 1.0000
13.000 1.4114 0.03786 0.03144 -0.0572 0.0329 1.0000
13.250 1.4183 0.03960 0.03320 -0.0560 0.0298 1.0000
13.500 1.4244 0.04145 0.03512 -0.0548 0.0271 1.0000
13.750 1.4315 0.04325 0.03696 -0.0539 0.0247 1.0000
14.000 1.4362 0.04533 0.03910 -0.0529 0.0226 1.0000
14.250 1.4436 0.04720 0.04104 -0.0521 0.0207 1.0000
14.500 1.4450 0.04976 0.04363 -0.0512 0.0191 1.0000
14.750 1.4519 0.05178 0.04578 -0.0507 0.0178 1.0000
15.000 1.4575 0.05398 0.04802 -0.0502 0.0162 1.0000
15.250 1.4580 0.05684 0.05097 -0.0497 0.0152 1.0000
15.500 1.4621 0.05938 0.05362 -0.0494 0.0142 1.0000
15.750 1.4651 0.06210 0.05642 -0.0492 0.0131 1.0000
16.000 1.4614 0.06574 0.06014 -0.0491 0.0123 1.0000
16.250 1.4636 0.06873 0.06326 -0.0492 0.0114 1.0000
16.500 1.4638 0.07204 0.06667 -0.0495 0.0106 1.0000
16.750 1.4554 0.07668 0.07140 -0.0501 0.0099 1.0000
17.000 1.4552 0.08026 0.07512 -0.0507 0.0092 1.0000
17.250 1.4528 0.08424 0.07922 -0.0516 0.0085 1.0000
17.500 1.4469 0.08886 0.08394 -0.0528 0.0079 1.0000
17.750 1.4336 0.09481 0.09000 -0.0546 0.0076 1.0000
18.000 1.4303 0.09928 0.09464 -0.0561 0.0071 1.0000
18.250 1.4249 0.10416 0.09964 -0.0579 0.0065 1.0000
18.500 1.4172 0.10952 0.10513 -0.0600 0.0063 1.0000
18.750 1.4079 0.11526 0.11098 -0.0625 0.0060 1.0000
19.000 1.3945 0.12183 0.11767 -0.0656 0.0058 1.0000
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