EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.47 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e668-il-1000000.txt Download as CSV file: xf-e668-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1154 0.08507 0.08247 -0.1273 0.8409 0.0112
-11.250 -0.1282 0.07875 0.07617 -0.1299 0.8396 0.0114
-11.000 -0.1296 0.07492 0.07236 -0.1317 0.8384 0.0115
-10.750 -0.1358 0.06971 0.06715 -0.1342 0.8369 0.0115
-10.500 -0.3342 0.03400 0.03069 -0.1496 0.8316 0.0066
-10.250 -0.3322 0.03251 0.02922 -0.1483 0.8302 0.0063
-10.000 -0.3643 0.02951 0.02603 -0.1434 0.8277 0.0061
-9.750 -0.3795 0.02650 0.02272 -0.1398 0.8256 0.0058
-9.500 -0.3841 0.02350 0.01935 -0.1369 0.8239 0.0055
-9.250 -0.3883 0.01957 0.01482 -0.1335 0.8222 0.0050
-9.000 -0.3728 0.01811 0.01312 -0.1322 0.8208 0.0049
-8.750 -0.3537 0.01713 0.01198 -0.1314 0.8191 0.0049
-8.500 -0.3339 0.01613 0.01085 -0.1306 0.8183 0.0049
-8.250 -0.3123 0.01533 0.00995 -0.1300 0.8174 0.0049
-8.000 -0.2898 0.01462 0.00915 -0.1295 0.8165 0.0049
-7.750 -0.2669 0.01395 0.00840 -0.1291 0.8153 0.0050
-7.500 -0.2433 0.01334 0.00772 -0.1287 0.8141 0.0052
-7.250 -0.2186 0.01284 0.00716 -0.1285 0.8128 0.0053
-7.000 -0.1936 0.01237 0.00664 -0.1283 0.8117 0.0055
-6.750 -0.1679 0.01194 0.00615 -0.1282 0.8105 0.0057
-6.500 -0.1418 0.01156 0.00571 -0.1282 0.8094 0.0060
-6.250 -0.1156 0.01115 0.00524 -0.1281 0.8082 0.0067
-6.000 -0.0890 0.01080 0.00485 -0.1282 0.8070 0.0079
-5.750 -0.0620 0.01049 0.00452 -0.1282 0.8058 0.0107
-5.500 -0.0350 0.01023 0.00427 -0.1283 0.8046 0.0160
-5.250 -0.0077 0.01008 0.00413 -0.1285 0.8032 0.0210
-5.000 0.0197 0.00983 0.00392 -0.1286 0.8022 0.0273
-4.750 0.0472 0.00961 0.00374 -0.1288 0.8011 0.0357
-4.500 0.0746 0.00937 0.00356 -0.1290 0.7997 0.0498
-4.250 0.1021 0.00911 0.00340 -0.1292 0.7982 0.0719
-4.000 0.1296 0.00881 0.00325 -0.1295 0.7966 0.1070
-3.750 0.1572 0.00849 0.00310 -0.1298 0.7949 0.1524
-3.500 0.1853 0.00821 0.00296 -0.1302 0.7933 0.1988
-3.250 0.2136 0.00795 0.00285 -0.1307 0.7918 0.2481
-3.000 0.2421 0.00770 0.00274 -0.1311 0.7903 0.3046
-2.750 0.2704 0.00745 0.00271 -0.1316 0.7884 0.3774
-2.500 0.2984 0.00717 0.00265 -0.1320 0.7867 0.4500
-2.250 0.3266 0.00685 0.00256 -0.1324 0.7848 0.5254
-2.000 0.3551 0.00658 0.00250 -0.1328 0.7827 0.5963
-1.750 0.3838 0.00639 0.00246 -0.1332 0.7805 0.6533
-1.500 0.4126 0.00628 0.00245 -0.1334 0.7785 0.6950
-1.250 0.4417 0.00624 0.00244 -0.1337 0.7765 0.7223
-1.000 0.4711 0.00623 0.00243 -0.1341 0.7745 0.7412
-0.750 0.5002 0.00629 0.00248 -0.1344 0.7721 0.7545
-0.500 0.5284 0.00627 0.00248 -0.1345 0.7698 0.7657
-0.250 0.5570 0.00626 0.00247 -0.1347 0.7670 0.7750
0.000 0.5856 0.00624 0.00245 -0.1349 0.7641 0.7817
0.250 0.6146 0.00622 0.00243 -0.1351 0.7614 0.7883
0.500 0.6439 0.00622 0.00240 -0.1355 0.7588 0.7947
0.750 0.6720 0.00623 0.00243 -0.1355 0.7558 0.7999
1.000 0.6998 0.00622 0.00244 -0.1356 0.7520 0.8053
1.250 0.7284 0.00620 0.00242 -0.1358 0.7481 0.8100
1.500 0.7564 0.00616 0.00238 -0.1359 0.7444 0.8141
1.750 0.7841 0.00617 0.00241 -0.1359 0.7401 0.8185
2.000 0.8118 0.00617 0.00243 -0.1359 0.7346 0.8231
2.250 0.8397 0.00615 0.00239 -0.1360 0.7291 0.8270
2.500 0.8665 0.00615 0.00243 -0.1359 0.7221 0.8305
2.750 0.8934 0.00616 0.00244 -0.1357 0.7146 0.8343
3.000 0.9203 0.00620 0.00248 -0.1356 0.7054 0.8382
3.250 0.9470 0.00626 0.00252 -0.1355 0.6951 0.8413
3.500 0.9721 0.00631 0.00255 -0.1350 0.6821 0.8442
3.750 0.9964 0.00641 0.00262 -0.1344 0.6659 0.8470
4.000 1.0199 0.00656 0.00272 -0.1336 0.6468 0.8497
4.250 1.0416 0.00678 0.00285 -0.1325 0.6241 0.8525
4.500 1.0624 0.00705 0.00302 -0.1312 0.5977 0.8551
4.750 1.0812 0.00735 0.00321 -0.1296 0.5700 0.8575
5.000 1.0978 0.00770 0.00345 -0.1275 0.5408 0.8602
5.250 1.1133 0.00807 0.00371 -0.1253 0.5116 0.8629
5.500 1.1277 0.00847 0.00400 -0.1228 0.4832 0.8658
5.750 1.1414 0.00883 0.00426 -0.1203 0.4568 0.8688
6.000 1.1528 0.00921 0.00455 -0.1172 0.4329 0.8716
6.250 1.1623 0.00965 0.00489 -0.1139 0.4061 0.8751
6.500 1.1736 0.01009 0.00525 -0.1110 0.3814 0.8785
6.750 1.1842 0.01060 0.00566 -0.1081 0.3575 0.8820
7.000 1.1955 0.01113 0.00610 -0.1053 0.3319 0.8855
7.250 1.2059 0.01170 0.00657 -0.1026 0.3075 0.8889
7.500 1.2154 0.01233 0.00710 -0.0997 0.2825 0.8929
7.750 1.2271 0.01293 0.00763 -0.0974 0.2612 0.8970
8.000 1.2378 0.01363 0.00824 -0.0950 0.2377 0.9011
8.250 1.2482 0.01433 0.00886 -0.0925 0.2152 0.9057
8.500 1.2581 0.01509 0.00953 -0.0901 0.1928 0.9114
8.750 1.2696 0.01584 0.01020 -0.0880 0.1730 0.9172
9.000 1.2811 0.01652 0.01086 -0.0859 0.1565 0.9250
9.250 1.2916 0.01723 0.01154 -0.0837 0.1404 0.9373
9.500 1.3044 0.01795 0.01225 -0.0821 0.1236 1.0000
9.750 1.3183 0.01881 0.01303 -0.0807 0.1094 1.0000
10.000 1.3323 0.01966 0.01383 -0.0794 0.0967 1.0000
10.250 1.3458 0.02054 0.01466 -0.0780 0.0851 1.0000
10.500 1.3590 0.02144 0.01551 -0.0767 0.0744 1.0000
10.750 1.3714 0.02240 0.01642 -0.0753 0.0644 1.0000
11.000 1.3843 0.02334 0.01734 -0.0739 0.0566 1.0000
11.250 1.3958 0.02437 0.01833 -0.0724 0.0482 1.0000
11.500 1.4068 0.02546 0.01939 -0.0710 0.0413 1.0000
11.750 1.4178 0.02657 0.02046 -0.0695 0.0346 1.0000
12.000 1.4296 0.02764 0.02153 -0.0682 0.0302 1.0000
12.250 1.4408 0.02876 0.02266 -0.0669 0.0262 1.0000
12.500 1.4515 0.02995 0.02385 -0.0656 0.0230 1.0000
12.750 1.4625 0.03113 0.02506 -0.0644 0.0208 1.0000
13.000 1.4731 0.03238 0.02634 -0.0632 0.0186 1.0000
13.250 1.4836 0.03365 0.02765 -0.0620 0.0169 1.0000
13.500 1.4923 0.03510 0.02912 -0.0608 0.0154 1.0000
13.750 1.5035 0.03638 0.03046 -0.0598 0.0143 1.0000
14.000 1.5119 0.03792 0.03203 -0.0587 0.0130 1.0000
14.250 1.5210 0.03945 0.03362 -0.0577 0.0120 1.0000
14.500 1.5299 0.04100 0.03523 -0.0568 0.0111 1.0000
14.750 1.5363 0.04285 0.03711 -0.0558 0.0101 1.0000
15.000 1.5447 0.04453 0.03886 -0.0551 0.0092 1.0000
15.250 1.5516 0.04640 0.04079 -0.0543 0.0084 1.0000
15.500 1.5555 0.04866 0.04309 -0.0535 0.0076 1.0000
15.750 1.5633 0.05052 0.04504 -0.0529 0.0068 1.0000
16.000 1.5670 0.05288 0.04745 -0.0523 0.0059 1.0000
16.250 1.5712 0.05527 0.04992 -0.0519 0.0053 1.0000
16.500 1.5746 0.05780 0.05251 -0.0515 0.0047 1.0000
16.750 1.5747 0.06080 0.05558 -0.0512 0.0039 1.0000
17.000 1.5762 0.06371 0.05858 -0.0511 0.0035 1.0000
17.250 1.5744 0.06709 0.06204 -0.0512 0.0031 1.0000
17.500 1.5707 0.07089 0.06595 -0.0514 0.0026 1.0000
17.750 1.5695 0.07441 0.06958 -0.0518 0.0025 1.0000
18.000 1.5666 0.07830 0.07357 -0.0524 0.0023 1.0000
18.250 1.5598 0.08285 0.07823 -0.0533 0.0021 1.0000
18.500 1.5542 0.08732 0.08282 -0.0544 0.0020 1.0000
18.750 1.5439 0.09270 0.08833 -0.0560 0.0019 1.0000
19.000 1.5314 0.09859 0.09436 -0.0579 0.0018 1.0000
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Polar data table (+)
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