E475 (15.01%) (e475-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 500,000 Max Cl/Cd: 71.03 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e475-il-500000-n5.txt Download as CSV file: xf-e475-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E475 (15.01%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1167 0.08840 0.08398 -0.0355 1.0000 0.0315
-18.000 -1.1425 0.08133 0.07679 -0.0388 1.0000 0.0318
-17.750 -1.1718 0.07391 0.06926 -0.0423 1.0000 0.0324
-17.500 -1.1990 0.06692 0.06212 -0.0455 1.0000 0.0324
-17.250 -1.2274 0.05976 0.05483 -0.0488 1.0000 0.0333
-17.000 -1.2490 0.05361 0.04853 -0.0516 1.0000 0.0337
-16.750 -1.2656 0.04823 0.04300 -0.0540 1.0000 0.0344
-16.500 -1.2782 0.04362 0.03826 -0.0559 1.0000 0.0354
-16.250 -1.2898 0.03944 0.03397 -0.0573 1.0000 0.0369
-16.000 -1.2964 0.03619 0.03062 -0.0578 1.0000 0.0379
-15.750 -1.3013 0.03345 0.02779 -0.0577 1.0000 0.0401
-15.500 -1.3026 0.03128 0.02554 -0.0570 1.0000 0.0420
-15.250 -1.3040 0.02931 0.02351 -0.0558 1.0000 0.0438
-15.000 -1.3030 0.02770 0.02184 -0.0543 1.0000 0.0463
-14.750 -1.2990 0.02643 0.02049 -0.0526 1.0000 0.0485
-14.500 -1.2971 0.02510 0.01913 -0.0504 1.0000 0.0514
-14.250 -1.2919 0.02406 0.01805 -0.0483 1.0000 0.0546
-14.000 -1.2859 0.02313 0.01708 -0.0459 1.0000 0.0572
-13.750 -1.2803 0.02225 0.01617 -0.0434 1.0000 0.0606
-13.500 -1.2722 0.02156 0.01544 -0.0409 1.0000 0.0640
-13.250 -1.2664 0.02082 0.01469 -0.0379 1.0000 0.0674
-13.000 -1.2591 0.02023 0.01407 -0.0350 1.0000 0.0706
-12.750 -1.2513 0.01975 0.01355 -0.0319 1.0000 0.0737
-12.500 -1.2478 0.01923 0.01303 -0.0280 1.0000 0.0771
-12.250 -1.2454 0.01884 0.01262 -0.0237 1.0000 0.0803
-12.000 -1.2440 0.01856 0.01229 -0.0189 1.0000 0.0831
-11.750 -1.2422 0.01822 0.01193 -0.0143 1.0000 0.0861
-11.500 -1.2349 0.01782 0.01153 -0.0107 1.0000 0.0897
-11.250 -1.2217 0.01747 0.01114 -0.0082 0.9998 0.0938
-11.000 -1.1979 0.01700 0.01067 -0.0079 0.9984 0.0986
-10.750 -1.1735 0.01660 0.01026 -0.0076 0.9970 0.1047
-10.500 -1.1488 0.01619 0.00986 -0.0073 0.9955 0.1104
-10.250 -1.1225 0.01584 0.00951 -0.0074 0.9941 0.1165
-10.000 -1.0947 0.01552 0.00916 -0.0076 0.9929 0.1206
-9.750 -1.0713 0.01518 0.00884 -0.0070 0.9914 0.1254
-9.500 -1.0469 0.01491 0.00854 -0.0065 0.9898 0.1294
-9.250 -1.0210 0.01466 0.00825 -0.0062 0.9882 0.1331
-9.000 -0.9946 0.01436 0.00797 -0.0062 0.9865 0.1376
-8.750 -0.9673 0.01413 0.00772 -0.0062 0.9852 0.1420
-8.500 -0.9383 0.01393 0.00748 -0.0065 0.9839 0.1457
-8.250 -0.9094 0.01366 0.00723 -0.0069 0.9827 0.1503
-8.000 -0.8791 0.01345 0.00703 -0.0075 0.9818 0.1551
-7.750 -0.8495 0.01327 0.00682 -0.0078 0.9805 0.1588
-7.500 -0.8263 0.01306 0.00660 -0.0069 0.9775 0.1626
-7.250 -0.7983 0.01285 0.00641 -0.0070 0.9750 0.1669
-7.000 -0.7653 0.01265 0.00620 -0.0080 0.9728 0.1712
-6.750 -0.7265 0.01244 0.00596 -0.0102 0.9706 0.1751
-6.500 -0.6794 0.01209 0.00565 -0.0142 0.9685 0.1801
-6.250 -0.6445 0.01181 0.00537 -0.0154 0.9612 0.1845
-6.000 -0.6025 0.01151 0.00505 -0.0181 0.9554 0.1886
-5.750 -0.5751 0.01128 0.00482 -0.0178 0.9479 0.1920
-5.500 -0.5462 0.01105 0.00461 -0.0179 0.9414 0.1962
-5.250 -0.5176 0.01087 0.00443 -0.0178 0.9363 0.2004
-5.000 -0.4935 0.01074 0.00428 -0.0168 0.9289 0.2036
-4.750 -0.4648 0.01055 0.00409 -0.0168 0.9227 0.2068
-4.500 -0.4417 0.01039 0.00396 -0.0156 0.9138 0.2109
-4.250 -0.4143 0.01022 0.00379 -0.0153 0.9050 0.2152
-4.000 -0.3895 0.01009 0.00364 -0.0144 0.8910 0.2187
-3.750 -0.3631 0.00994 0.00346 -0.0137 0.8668 0.2219
-3.500 -0.3353 0.00977 0.00316 -0.0133 0.8154 0.2264
-3.250 -0.3123 0.00984 0.00297 -0.0119 0.7488 0.2311
-3.000 -0.2911 0.01001 0.00288 -0.0102 0.6834 0.2351
-2.750 -0.2694 0.01017 0.00281 -0.0088 0.6247 0.2387
-2.500 -0.2472 0.01027 0.00275 -0.0075 0.5742 0.2435
-2.250 -0.2239 0.01036 0.00270 -0.0065 0.5317 0.2489
-2.000 -0.1997 0.01045 0.00265 -0.0056 0.4958 0.2538
-1.750 -0.1756 0.01049 0.00260 -0.0047 0.4630 0.2596
-1.500 -0.1511 0.01055 0.00256 -0.0040 0.4319 0.2656
-1.250 -0.1263 0.01061 0.00253 -0.0032 0.4042 0.2719
-1.000 -0.1014 0.01062 0.00250 -0.0025 0.3823 0.2801
-0.500 -0.0507 0.01065 0.00247 -0.0013 0.3477 0.2971
-0.250 -0.0252 0.01068 0.00246 -0.0006 0.3325 0.3064
0.000 0.0000 0.01069 0.00246 0.0000 0.3183 0.3183
0.250 0.0252 0.01068 0.00246 0.0006 0.3064 0.3325
0.500 0.0507 0.01065 0.00247 0.0013 0.2971 0.3477
0.750 0.0759 0.01065 0.00248 0.0019 0.2881 0.3640
1.000 0.1014 0.01062 0.00250 0.0025 0.2801 0.3826
1.250 0.1262 0.01061 0.00253 0.0032 0.2720 0.4050
1.500 0.1511 0.01055 0.00256 0.0039 0.2656 0.4314
1.750 0.1757 0.01049 0.00260 0.0047 0.2596 0.4625
2.000 0.1997 0.01045 0.00265 0.0056 0.2538 0.4958
2.250 0.2239 0.01036 0.00270 0.0065 0.2489 0.5318
2.500 0.2473 0.01027 0.00275 0.0075 0.2434 0.5738
2.750 0.2694 0.01017 0.00281 0.0088 0.2387 0.6252
3.000 0.2911 0.01001 0.00288 0.0102 0.2352 0.6837
3.250 0.3123 0.00984 0.00297 0.0118 0.2310 0.7478
3.500 0.3353 0.00977 0.00316 0.0132 0.2265 0.8155
3.750 0.3631 0.00994 0.00345 0.0137 0.2219 0.8661
4.000 0.3894 0.01009 0.00364 0.0144 0.2187 0.8905
4.250 0.4143 0.01022 0.00379 0.0153 0.2151 0.9051
4.500 0.4417 0.01039 0.00396 0.0156 0.2108 0.9138
4.750 0.4648 0.01055 0.00408 0.0168 0.2067 0.9227
5.000 0.4935 0.01074 0.00428 0.0168 0.2035 0.9290
5.250 0.5178 0.01087 0.00443 0.0178 0.2003 0.9361
5.500 0.5463 0.01105 0.00461 0.0178 0.1962 0.9415
5.750 0.5751 0.01128 0.00482 0.0178 0.1920 0.9478
6.000 0.6026 0.01151 0.00505 0.0181 0.1887 0.9554
6.250 0.6445 0.01181 0.00537 0.0154 0.1846 0.9612
6.500 0.6794 0.01209 0.00565 0.0142 0.1800 0.9685
6.750 0.7266 0.01243 0.00596 0.0102 0.1751 0.9706
7.000 0.7655 0.01265 0.00619 0.0080 0.1709 0.9728
7.250 0.7984 0.01285 0.00641 0.0070 0.1669 0.9751
7.500 0.8263 0.01306 0.00660 0.0069 0.1625 0.9775
7.750 0.8494 0.01328 0.00682 0.0079 0.1590 0.9805
8.000 0.8793 0.01345 0.00702 0.0074 0.1551 0.9818
8.250 0.9095 0.01366 0.00723 0.0068 0.1504 0.9828
8.500 0.9385 0.01393 0.00748 0.0064 0.1457 0.9840
8.750 0.9675 0.01412 0.00772 0.0061 0.1420 0.9852
9.000 0.9948 0.01436 0.00797 0.0061 0.1377 0.9866
9.250 1.0212 0.01466 0.00825 0.0062 0.1330 0.9882
9.500 1.0471 0.01491 0.00854 0.0064 0.1294 0.9899
9.750 1.0715 0.01518 0.00883 0.0070 0.1253 0.9914
10.000 1.0950 0.01552 0.00916 0.0076 0.1206 0.9930
10.250 1.1228 0.01583 0.00950 0.0073 0.1165 0.9942
10.500 1.1492 0.01618 0.00986 0.0073 0.1106 0.9956
10.750 1.1738 0.01659 0.01026 0.0075 0.1044 0.9970
11.000 1.1982 0.01701 0.01067 0.0078 0.0983 0.9985
11.250 1.2222 0.01747 0.01113 0.0081 0.0937 0.9998
11.500 1.2349 0.01782 0.01152 0.0107 0.0899 1.0000
11.750 1.2425 0.01820 0.01192 0.0143 0.0863 1.0000
12.000 1.2442 0.01855 0.01229 0.0189 0.0830 1.0000
12.250 1.2456 0.01884 0.01261 0.0236 0.0803 1.0000
12.500 1.2481 0.01922 0.01302 0.0279 0.0772 1.0000
12.750 1.2517 0.01974 0.01354 0.0318 0.0738 1.0000
13.000 1.2595 0.02022 0.01406 0.0349 0.0706 1.0000
13.250 1.2667 0.02082 0.01469 0.0379 0.0672 1.0000
13.500 1.2727 0.02155 0.01543 0.0408 0.0637 1.0000
13.750 1.2810 0.02224 0.01616 0.0433 0.0607 1.0000
14.000 1.2870 0.02311 0.01706 0.0458 0.0574 1.0000
14.250 1.2929 0.02404 0.01803 0.0481 0.0547 1.0000
14.500 1.2982 0.02507 0.01911 0.0503 0.0514 1.0000
14.750 1.3004 0.02638 0.02045 0.0524 0.0486 1.0000
15.000 1.3044 0.02767 0.02180 0.0542 0.0464 1.0000
15.250 1.3060 0.02923 0.02343 0.0557 0.0442 1.0000
15.500 1.3030 0.03132 0.02558 0.0569 0.0415 1.0000
15.750 1.3026 0.03342 0.02776 0.0575 0.0398 1.0000
16.000 1.2987 0.03608 0.03051 0.0576 0.0381 1.0000
16.250 1.2911 0.03943 0.03396 0.0571 0.0367 1.0000
16.500 1.2800 0.04355 0.03819 0.0557 0.0354 1.0000
16.750 1.2684 0.04806 0.04283 0.0539 0.0344 1.0000
17.000 1.2511 0.05353 0.04844 0.0514 0.0335 1.0000
17.250 1.2264 0.06014 0.05519 0.0483 0.0324 1.0000
17.500 1.2034 0.06656 0.06177 0.0454 0.0327 1.0000
17.750 1.1730 0.07401 0.06935 0.0419 0.0321 1.0000
18.000 1.1462 0.08107 0.07654 0.0387 0.0319 1.0000
18.250 1.1192 0.08834 0.08391 0.0352 0.0315 1.0000
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