EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 1,000,000 Max Cl/Cd: 152 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e662-il-1000000.txt Download as CSV file: xf-e662-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E662 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.0210 0.09622 0.09362 -0.1279 0.8290 0.0152
-12.750 -0.0223 0.09130 0.08869 -0.1297 0.8281 0.0152
-12.000 -0.2928 0.04186 0.03877 -0.1665 0.8298 0.0113
-11.750 -0.0868 0.07892 0.07620 -0.1477 0.8310 0.0158
-11.250 -0.3444 0.03261 0.02901 -0.1641 0.8236 0.0114
-11.000 -0.3617 0.03051 0.02669 -0.1608 0.8220 0.0117
-10.750 -0.3701 0.02882 0.02486 -0.1575 0.8204 0.0117
-10.500 -0.3972 0.02559 0.02132 -0.1517 0.8183 0.0119
-10.250 -0.3932 0.02391 0.01948 -0.1494 0.8169 0.0121
-10.000 -0.3819 0.02278 0.01823 -0.1479 0.8155 0.0123
-9.750 -0.3657 0.02210 0.01747 -0.1468 0.8145 0.0126
-9.500 -0.3501 0.02108 0.01633 -0.1457 0.8134 0.0128
-9.250 -0.3308 0.02048 0.01566 -0.1450 0.8124 0.0132
-9.000 -0.3114 0.01972 0.01479 -0.1443 0.8112 0.0135
-8.750 -0.2911 0.01899 0.01394 -0.1436 0.8098 0.0139
-8.500 -0.2697 0.01840 0.01324 -0.1430 0.8091 0.0144
-8.250 -0.2479 0.01771 0.01244 -0.1424 0.8083 0.0148
-8.000 -0.2249 0.01718 0.01181 -0.1420 0.8075 0.0150
-7.750 -0.2014 0.01666 0.01120 -0.1416 0.8067 0.0152
-7.500 -0.1800 0.01530 0.00970 -0.1410 0.8057 0.0155
-7.250 -0.1588 0.01412 0.00845 -0.1403 0.8046 0.0160
-7.000 -0.1355 0.01350 0.00781 -0.1399 0.8035 0.0164
-6.750 -0.1109 0.01308 0.00737 -0.1397 0.8025 0.0170
-6.500 -0.0857 0.01274 0.00701 -0.1396 0.8015 0.0177
-6.250 -0.0606 0.01236 0.00659 -0.1394 0.8005 0.0182
-6.000 -0.0354 0.01198 0.00616 -0.1392 0.7994 0.0186
-5.750 -0.0098 0.01163 0.00578 -0.1391 0.7984 0.0190
-5.500 0.0164 0.01136 0.00547 -0.1391 0.7974 0.0194
-5.250 0.0429 0.01113 0.00520 -0.1392 0.7962 0.0196
-5.000 0.0675 0.01072 0.00473 -0.1389 0.7947 0.0205
-4.750 0.0934 0.01042 0.00442 -0.1389 0.7939 0.0216
-4.500 0.1200 0.01019 0.00420 -0.1389 0.7930 0.0228
-4.250 0.1469 0.01000 0.00400 -0.1390 0.7919 0.0240
-4.000 0.1742 0.00984 0.00382 -0.1391 0.7906 0.0250
-3.750 0.2013 0.00962 0.00361 -0.1392 0.7893 0.0286
-3.500 0.2284 0.00935 0.00344 -0.1394 0.7879 0.0479
-3.250 0.2554 0.00900 0.00329 -0.1397 0.7864 0.0982
-3.000 0.2830 0.00868 0.00316 -0.1401 0.7849 0.1529
-2.750 0.3109 0.00831 0.00303 -0.1406 0.7834 0.2301
-2.500 0.3392 0.00787 0.00292 -0.1414 0.7819 0.3352
-2.250 0.3683 0.00739 0.00283 -0.1424 0.7802 0.4674
-2.000 0.3974 0.00676 0.00280 -0.1435 0.7786 0.6558
-1.750 0.4254 0.00669 0.00290 -0.1436 0.7771 0.7202
-1.500 0.4541 0.00671 0.00292 -0.1439 0.7751 0.7408
-1.250 0.4829 0.00676 0.00297 -0.1441 0.7730 0.7565
-1.000 0.5115 0.00684 0.00305 -0.1442 0.7710 0.7675
-0.750 0.5405 0.00688 0.00308 -0.1445 0.7691 0.7743
-0.500 0.5697 0.00693 0.00311 -0.1448 0.7673 0.7792
-0.250 0.5993 0.00702 0.00316 -0.1453 0.7652 0.7847
0.000 0.6270 0.00708 0.00322 -0.1453 0.7630 0.7894
0.250 0.6535 0.00712 0.00331 -0.1450 0.7605 0.7944
0.500 0.6814 0.00717 0.00335 -0.1450 0.7577 0.8000
0.750 0.7095 0.00717 0.00336 -0.1451 0.7550 0.8043
1.000 0.7372 0.00718 0.00337 -0.1451 0.7524 0.8074
1.250 0.7662 0.00723 0.00339 -0.1454 0.7497 0.8100
1.500 0.7930 0.00720 0.00340 -0.1454 0.7466 0.8122
1.750 0.8207 0.00717 0.00337 -0.1455 0.7429 0.8142
2.000 0.8492 0.00712 0.00331 -0.1458 0.7392 0.8157
2.250 0.8783 0.00710 0.00326 -0.1463 0.7356 0.8170
2.500 0.9049 0.00704 0.00324 -0.1462 0.7309 0.8183
2.750 0.9314 0.00698 0.00320 -0.1461 0.7256 0.8196
3.000 0.9586 0.00695 0.00316 -0.1461 0.7204 0.8207
3.250 0.9845 0.00693 0.00319 -0.1459 0.7130 0.8218
3.500 1.0104 0.00692 0.00317 -0.1456 0.7052 0.8230
3.750 1.0354 0.00693 0.00318 -0.1452 0.6943 0.8242
4.000 1.0594 0.00698 0.00320 -0.1446 0.6807 0.8254
4.500 1.1020 0.00725 0.00335 -0.1422 0.6437 0.8282
4.750 1.1202 0.00748 0.00348 -0.1404 0.6216 0.8295
5.000 1.1363 0.00776 0.00367 -0.1382 0.5967 0.8308
5.250 1.1485 0.00809 0.00388 -0.1353 0.5716 0.8321
5.500 1.1583 0.00838 0.00409 -0.1318 0.5480 0.8337
5.750 1.1675 0.00876 0.00437 -0.1283 0.5238 0.8351
6.000 1.1753 0.00922 0.00473 -0.1246 0.4987 0.8365
6.250 1.1858 0.00966 0.00510 -0.1215 0.4746 0.8379
6.500 1.1950 0.01016 0.00551 -0.1182 0.4522 0.8393
6.750 1.2046 0.01068 0.00595 -0.1152 0.4285 0.8410
7.000 1.2134 0.01128 0.00645 -0.1121 0.4057 0.8428
7.250 1.2234 0.01188 0.00697 -0.1093 0.3828 0.8443
7.500 1.2317 0.01261 0.00759 -0.1064 0.3584 0.8458
7.750 1.2394 0.01342 0.00828 -0.1035 0.3324 0.8471
8.000 1.2490 0.01418 0.00894 -0.1010 0.3073 0.8484
8.500 1.2680 0.01582 0.01038 -0.0962 0.2601 0.8514
8.750 1.2777 0.01669 0.01115 -0.0939 0.2372 0.8528
9.000 1.2887 0.01753 0.01191 -0.0919 0.2168 0.8545
9.250 1.2992 0.01842 0.01271 -0.0899 0.1969 0.8562
9.500 1.3105 0.01930 0.01351 -0.0881 0.1776 0.8578
9.750 1.3206 0.02028 0.01439 -0.0861 0.1573 0.8593
10.000 1.3320 0.02121 0.01525 -0.0844 0.1416 0.8607
10.250 1.3438 0.02214 0.01611 -0.0829 0.1263 0.8620
10.500 1.3551 0.02311 0.01702 -0.0812 0.1116 0.8635
10.750 1.3657 0.02412 0.01797 -0.0796 0.0974 0.8651
11.000 1.3769 0.02513 0.01893 -0.0780 0.0853 0.8667
11.250 1.3874 0.02620 0.01997 -0.0764 0.0743 0.8683
11.500 1.3982 0.02729 0.02101 -0.0749 0.0644 0.8700
11.750 1.4084 0.02844 0.02213 -0.0735 0.0551 0.8717
12.000 1.4206 0.02949 0.02319 -0.0722 0.0490 0.8735
12.250 1.4314 0.03066 0.02434 -0.0709 0.0422 0.8753
12.500 1.4407 0.03199 0.02564 -0.0695 0.0356 0.8770
12.750 1.4516 0.03316 0.02684 -0.0683 0.0311 0.8793
13.000 1.4600 0.03456 0.02823 -0.0669 0.0250 0.8814
13.250 1.4658 0.03624 0.02989 -0.0654 0.0183 0.8835
13.500 1.4713 0.03800 0.03164 -0.0639 0.0125 0.8856
13.750 1.4761 0.03989 0.03354 -0.0625 0.0092 0.8878
14.000 1.4824 0.04169 0.03539 -0.0613 0.0078 0.8900
14.250 1.4910 0.04332 0.03709 -0.0603 0.0073 0.8923
14.500 1.4988 0.04501 0.03886 -0.0594 0.0068 0.8950
14.750 1.5048 0.04694 0.04086 -0.0584 0.0064 0.8979
15.000 1.5076 0.04926 0.04328 -0.0573 0.0059 0.9009
15.250 1.5121 0.05147 0.04558 -0.0565 0.0057 0.9040
15.500 1.5181 0.05355 0.04776 -0.0558 0.0055 0.9076
15.750 1.5229 0.05577 0.05009 -0.0551 0.0054 0.9120
16.000 1.5269 0.05815 0.05257 -0.0546 0.0052 0.9171
16.250 1.5297 0.06066 0.05519 -0.0540 0.0051 0.9240
16.750 1.5299 0.06609 0.06089 -0.0528 0.0048 1.0000
17.000 1.5299 0.06939 0.06429 -0.0529 0.0047 1.0000
17.250 1.5298 0.07275 0.06774 -0.0532 0.0046 1.0000
17.500 1.5285 0.07637 0.07145 -0.0536 0.0045 1.0000
17.750 1.5235 0.08055 0.07575 -0.0541 0.0044 1.0000
18.000 1.5189 0.08481 0.08012 -0.0549 0.0043 1.0000
18.250 1.5115 0.08959 0.08501 -0.0560 0.0042 1.0000
18.500 1.5002 0.09510 0.09066 -0.0574 0.0041 1.0000
18.750 1.4901 0.10053 0.09622 -0.0591 0.0041 1.0000
19.000 1.4789 0.10625 0.10208 -0.0611 0.0040 1.0000
19.250 1.4635 0.11284 0.10881 -0.0636 0.0040 1.0000
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