EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.69 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e66-il-1000000-n5.txt Download as CSV file: xf-e66-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3803 0.12714 0.12540 -0.0407 0.9973 0.0033
-12.000 -0.3807 0.12045 0.11872 -0.0438 0.9967 0.0036
-11.500 -0.6689 0.03287 0.03051 -0.1144 0.9804 0.0034
-11.250 -0.6573 0.02819 0.02551 -0.1206 0.9753 0.0034
-11.000 -0.6347 0.02545 0.02252 -0.1243 0.9733 0.0035
-10.750 -0.6099 0.02294 0.01975 -0.1275 0.9719 0.0035
-10.500 -0.5965 0.02143 0.01804 -0.1266 0.9656 0.0036
-10.250 -0.5714 0.01992 0.01634 -0.1280 0.9632 0.0036
-10.000 -0.5440 0.01858 0.01482 -0.1295 0.9614 0.0036
-9.750 -0.5149 0.01750 0.01359 -0.1309 0.9602 0.0037
-9.500 -0.4892 0.01654 0.01249 -0.1315 0.9572 0.0038
-9.250 -0.4662 0.01549 0.01129 -0.1314 0.9526 0.0038
-9.000 -0.4378 0.01425 0.00985 -0.1326 0.9501 0.0040
-8.750 -0.4059 0.01336 0.00883 -0.1342 0.9484 0.0042
-8.500 -0.3732 0.01271 0.00809 -0.1358 0.9468 0.0045
-8.250 -0.3454 0.01222 0.00754 -0.1362 0.9428 0.0048
-8.000 -0.3157 0.01175 0.00699 -0.1369 0.9390 0.0051
-7.750 -0.2838 0.01124 0.00639 -0.1381 0.9359 0.0054
-7.500 -0.2508 0.01078 0.00584 -0.1396 0.9332 0.0058
-7.250 -0.2222 0.01037 0.00535 -0.1400 0.9283 0.0059
-7.000 -0.1922 0.00993 0.00483 -0.1407 0.9235 0.0063
-6.750 -0.1607 0.00952 0.00435 -0.1416 0.9193 0.0071
-6.500 -0.1325 0.00922 0.00401 -0.1419 0.9137 0.0079
-6.250 -0.1031 0.00895 0.00368 -0.1423 0.9081 0.0088
-6.000 -0.0738 0.00868 0.00337 -0.1428 0.9029 0.0104
-5.750 -0.0457 0.00847 0.00314 -0.1429 0.8965 0.0126
-5.250 0.0111 0.00808 0.00267 -0.1433 0.8840 0.0170
-5.000 0.0395 0.00793 0.00246 -0.1435 0.8775 0.0185
-4.750 0.0672 0.00774 0.00225 -0.1435 0.8708 0.0216
-4.500 0.0953 0.00760 0.00207 -0.1436 0.8636 0.0249
-4.250 0.1229 0.00740 0.00190 -0.1436 0.8564 0.0354
-4.000 0.1505 0.00721 0.00173 -0.1436 0.8490 0.0505
-3.750 0.1782 0.00708 0.00160 -0.1436 0.8414 0.0620
-3.500 0.2058 0.00697 0.00148 -0.1436 0.8337 0.0741
-3.250 0.2334 0.00685 0.00138 -0.1436 0.8256 0.0879
-3.000 0.2609 0.00676 0.00128 -0.1435 0.8176 0.1036
-2.750 0.2883 0.00665 0.00120 -0.1435 0.8088 0.1245
-2.500 0.3157 0.00651 0.00114 -0.1435 0.8002 0.1557
-2.250 0.3428 0.00642 0.00107 -0.1434 0.7911 0.1833
-2.000 0.3702 0.00635 0.00103 -0.1433 0.7812 0.2033
-1.750 0.3974 0.00629 0.00099 -0.1432 0.7710 0.2294
-1.500 0.4243 0.00625 0.00097 -0.1430 0.7600 0.2542
-1.250 0.4510 0.00622 0.00095 -0.1428 0.7481 0.2799
-1.000 0.4780 0.00616 0.00095 -0.1427 0.7362 0.3159
-0.750 0.5048 0.00613 0.00095 -0.1425 0.7240 0.3460
-0.500 0.5316 0.00611 0.00096 -0.1423 0.7114 0.3770
-0.250 0.5581 0.00610 0.00099 -0.1421 0.6982 0.4088
0.000 0.5846 0.00611 0.00102 -0.1418 0.6839 0.4403
0.250 0.6109 0.00613 0.00106 -0.1415 0.6691 0.4734
0.500 0.6370 0.00616 0.00112 -0.1412 0.6531 0.5070
0.750 0.6629 0.00621 0.00118 -0.1408 0.6363 0.5397
1.000 0.6887 0.00628 0.00126 -0.1404 0.6189 0.5734
1.250 0.7146 0.00634 0.00134 -0.1400 0.6006 0.6064
1.500 0.7402 0.00643 0.00143 -0.1396 0.5811 0.6384
2.000 0.7907 0.00664 0.00166 -0.1386 0.5400 0.7064
2.250 0.8153 0.00678 0.00179 -0.1379 0.5167 0.7392
2.500 0.8398 0.00694 0.00193 -0.1373 0.4919 0.7723
2.750 0.8637 0.00711 0.00209 -0.1365 0.4666 0.8039
3.000 0.8870 0.00729 0.00226 -0.1356 0.4415 0.8370
3.250 0.9092 0.00749 0.00243 -0.1344 0.4154 0.8719
3.500 0.9293 0.00766 0.00259 -0.1327 0.3896 0.9110
3.750 0.9504 0.00781 0.00272 -0.1312 0.3637 1.0000
4.000 0.9744 0.00812 0.00291 -0.1306 0.3367 1.0000
4.250 0.9975 0.00851 0.00314 -0.1298 0.3041 1.0000
4.500 1.0199 0.00893 0.00339 -0.1289 0.2688 1.0000
4.750 1.0432 0.00930 0.00364 -0.1281 0.2429 1.0000
5.000 1.0670 0.00961 0.00387 -0.1275 0.2225 1.0000
5.250 1.0894 0.01002 0.00415 -0.1266 0.1959 1.0000
5.500 1.1099 0.01057 0.00450 -0.1254 0.1594 1.0000
5.750 1.1316 0.01102 0.00483 -0.1244 0.1347 1.0000
6.000 1.1536 0.01144 0.00515 -0.1234 0.1143 1.0000
6.500 1.1966 0.01230 0.00584 -0.1213 0.0801 1.0000
6.750 1.2182 0.01271 0.00619 -0.1203 0.0678 1.0000
7.000 1.2395 0.01312 0.00656 -0.1192 0.0570 1.0000
7.250 1.2603 0.01355 0.00695 -0.1180 0.0471 1.0000
7.500 1.2803 0.01397 0.00733 -0.1167 0.0388 1.0000
7.750 1.2995 0.01440 0.00774 -0.1152 0.0316 1.0000
8.000 1.3173 0.01490 0.00820 -0.1135 0.0236 1.0000
8.250 1.3347 0.01542 0.00868 -0.1117 0.0178 1.0000
8.500 1.3521 0.01592 0.00918 -0.1100 0.0144 1.0000
8.750 1.3707 0.01636 0.00965 -0.1084 0.0129 1.0000
9.000 1.3883 0.01683 0.01014 -0.1068 0.0115 1.0000
9.250 1.4051 0.01737 0.01070 -0.1050 0.0102 1.0000
9.500 1.4225 0.01787 0.01124 -0.1034 0.0095 1.0000
9.750 1.4398 0.01835 0.01177 -0.1018 0.0089 1.0000
10.000 1.4564 0.01889 0.01235 -0.1001 0.0084 1.0000
10.250 1.4721 0.01949 0.01299 -0.0983 0.0076 1.0000
10.500 1.4866 0.02016 0.01370 -0.0964 0.0069 1.0000
10.750 1.5017 0.02081 0.01440 -0.0946 0.0064 1.0000
11.000 1.5168 0.02144 0.01508 -0.0928 0.0058 1.0000
11.250 1.5307 0.02216 0.01584 -0.0910 0.0052 1.0000
11.500 1.5434 0.02298 0.01669 -0.0891 0.0045 1.0000
11.750 1.5559 0.02382 0.01759 -0.0871 0.0041 1.0000
12.000 1.5680 0.02470 0.01853 -0.0853 0.0037 1.0000
12.250 1.5794 0.02565 0.01955 -0.0834 0.0034 1.0000
12.500 1.5895 0.02672 0.02067 -0.0814 0.0030 1.0000
12.750 1.5981 0.02793 0.02195 -0.0794 0.0027 1.0000
13.000 1.6075 0.02910 0.02320 -0.0775 0.0026 1.0000
13.250 1.6162 0.03037 0.02454 -0.0757 0.0025 1.0000
13.500 1.6240 0.03173 0.02600 -0.0739 0.0024 1.0000
13.750 1.6312 0.03319 0.02754 -0.0722 0.0023 1.0000
14.000 1.6371 0.03480 0.02924 -0.0706 0.0022 1.0000
14.250 1.6424 0.03652 0.03105 -0.0690 0.0021 1.0000
14.500 1.6467 0.03841 0.03303 -0.0675 0.0020 1.0000
14.750 1.6498 0.04046 0.03517 -0.0661 0.0019 1.0000
15.000 1.6525 0.04263 0.03745 -0.0649 0.0019 1.0000
15.250 1.6536 0.04506 0.03999 -0.0639 0.0018 1.0000
15.500 1.6530 0.04781 0.04285 -0.0629 0.0017 1.0000
15.750 1.6507 0.05085 0.04601 -0.0623 0.0016 1.0000
16.000 1.6473 0.05419 0.04947 -0.0618 0.0016 1.0000
16.250 1.6409 0.05807 0.05350 -0.0617 0.0015 1.0000
16.500 1.6353 0.06203 0.05758 -0.0619 0.0015 1.0000
16.750 1.6299 0.06614 0.06182 -0.0625 0.0015 1.0000
17.000 1.6243 0.07046 0.06627 -0.0633 0.0015 1.0000
17.250 1.6165 0.07532 0.07126 -0.0645 0.0014 1.0000
17.500 1.6074 0.08056 0.07665 -0.0662 0.0014 1.0000
17.750 1.5970 0.08626 0.08248 -0.0682 0.0014 1.0000
18.000 1.5851 0.09242 0.08878 -0.0707 0.0014 1.0000
18.250 1.5712 0.09919 0.09570 -0.0737 0.0014 1.0000
18.500 1.5560 0.10640 0.10307 -0.0771 0.0014 1.0000
18.750 1.5389 0.11422 0.11104 -0.0811 0.0014 1.0000
19.000 1.5211 0.12243 0.11940 -0.0856 0.0014 1.0000
19.250 1.5012 0.13125 0.12837 -0.0906 0.0014 1.0000
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Polar data table (+)
Polar graphs
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