E475 (15.01%) (e475-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.59 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e475-il-1000000-n5.txt Download as CSV file: xf-e475-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -1.1947 0.08406 0.08003 -0.0372 1.0000 0.0178
-18.500 -1.2292 0.07595 0.07178 -0.0409 1.0000 0.0177
-18.250 -1.2664 0.06762 0.06329 -0.0446 1.0000 0.0177
-18.000 -1.2968 0.06020 0.05570 -0.0480 1.0000 0.0174
-17.750 -1.3227 0.05342 0.04877 -0.0512 1.0000 0.0175
-17.500 -1.3417 0.04764 0.04284 -0.0539 1.0000 0.0177
-17.250 -1.3554 0.04278 0.03786 -0.0560 1.0000 0.0183
-16.750 -1.3731 0.03521 0.03008 -0.0583 1.0000 0.0197
-16.500 -1.3761 0.03254 0.02732 -0.0583 1.0000 0.0204
-16.250 -1.3770 0.03032 0.02502 -0.0578 1.0000 0.0213
-16.000 -1.3770 0.02839 0.02304 -0.0569 1.0000 0.0225
-15.750 -1.3763 0.02670 0.02128 -0.0555 1.0000 0.0237
-15.500 -1.3733 0.02532 0.01985 -0.0538 1.0000 0.0250
-15.250 -1.3691 0.02410 0.01859 -0.0519 1.0000 0.0266
-15.000 -1.3653 0.02297 0.01742 -0.0497 1.0000 0.0285
-14.750 -1.3588 0.02205 0.01646 -0.0475 1.0000 0.0303
-14.500 -1.3530 0.02116 0.01554 -0.0450 1.0000 0.0323
-14.250 -1.3460 0.02038 0.01474 -0.0425 1.0000 0.0346
-14.000 -1.3387 0.01968 0.01401 -0.0398 1.0000 0.0369
-13.750 -1.3317 0.01902 0.01334 -0.0369 1.0000 0.0395
-13.500 -1.3243 0.01848 0.01277 -0.0338 1.0000 0.0421
-13.250 -1.3207 0.01795 0.01223 -0.0300 1.0000 0.0447
-13.000 -1.3205 0.01757 0.01184 -0.0252 1.0000 0.0471
-12.750 -1.3021 0.01702 0.01129 -0.0241 0.9987 0.0506
-12.500 -1.2799 0.01647 0.01073 -0.0237 0.9967 0.0549
-12.250 -1.2579 0.01588 0.01017 -0.0233 0.9945 0.0605
-12.000 -1.2331 0.01544 0.00972 -0.0232 0.9929 0.0646
-11.750 -1.2117 0.01496 0.00926 -0.0224 0.9909 0.0688
-11.500 -1.1878 0.01455 0.00885 -0.0220 0.9891 0.0735
-11.250 -1.1635 0.01409 0.00842 -0.0217 0.9875 0.0787
-11.000 -1.1374 0.01374 0.00806 -0.0216 0.9862 0.0830
-10.750 -1.1113 0.01335 0.00769 -0.0216 0.9851 0.0881
-10.500 -1.0840 0.01301 0.00736 -0.0218 0.9842 0.0932
-10.250 -1.0563 0.01264 0.00702 -0.0221 0.9833 0.0995
-10.000 -1.0278 0.01232 0.00672 -0.0224 0.9826 0.1060
-9.750 -0.9996 0.01199 0.00642 -0.0228 0.9819 0.1118
-9.500 -0.9708 0.01173 0.00616 -0.0231 0.9812 0.1165
-9.250 -0.9461 0.01154 0.00596 -0.0225 0.9795 0.1195
-9.000 -0.9221 0.01129 0.00573 -0.0218 0.9776 0.1243
-8.750 -0.8962 0.01108 0.00553 -0.0215 0.9760 0.1286
-8.500 -0.8687 0.01090 0.00534 -0.0215 0.9746 0.1320
-8.250 -0.8411 0.01067 0.00513 -0.0215 0.9732 0.1365
-8.000 -0.8132 0.01048 0.00494 -0.0215 0.9721 0.1408
-7.750 -0.7846 0.01031 0.00478 -0.0217 0.9710 0.1446
-7.500 -0.7536 0.01009 0.00457 -0.0223 0.9691 0.1490
-7.250 -0.7289 0.00987 0.00435 -0.0214 0.9614 0.1533
-7.000 -0.7030 0.00965 0.00412 -0.0207 0.9515 0.1571
-6.750 -0.6802 0.00950 0.00393 -0.0193 0.9403 0.1596
-6.500 -0.6566 0.00933 0.00376 -0.0183 0.9315 0.1636
-6.250 -0.6315 0.00917 0.00361 -0.0175 0.9245 0.1679
-6.000 -0.6057 0.00904 0.00347 -0.0169 0.9188 0.1711
-5.750 -0.5799 0.00892 0.00335 -0.0163 0.9117 0.1738
-5.500 -0.5541 0.00878 0.00320 -0.0157 0.9043 0.1777
-5.250 -0.5283 0.00865 0.00308 -0.0151 0.8948 0.1816
-5.000 -0.5025 0.00853 0.00294 -0.0144 0.8784 0.1848
-4.750 -0.4788 0.00850 0.00275 -0.0132 0.8274 0.1879
-4.500 -0.4578 0.00864 0.00262 -0.0115 0.7565 0.1907
-4.250 -0.4356 0.00874 0.00254 -0.0102 0.6998 0.1944
-4.000 -0.4125 0.00884 0.00247 -0.0090 0.6485 0.1978
-3.750 -0.3888 0.00893 0.00241 -0.0081 0.5998 0.2013
-3.500 -0.3644 0.00904 0.00235 -0.0072 0.5518 0.2043
-3.000 -0.3145 0.00913 0.00222 -0.0058 0.4800 0.2115
-2.750 -0.2889 0.00916 0.00217 -0.0052 0.4512 0.2153
-2.500 -0.2631 0.00921 0.00213 -0.0047 0.4237 0.2190
-2.250 -0.2372 0.00926 0.00209 -0.0041 0.3971 0.2225
-1.750 -0.1854 0.00930 0.00201 -0.0031 0.3557 0.2314
-1.500 -0.1589 0.00932 0.00198 -0.0026 0.3399 0.2357
-1.250 -0.1325 0.00932 0.00196 -0.0022 0.3256 0.2409
-1.000 -0.1062 0.00932 0.00194 -0.0017 0.3119 0.2466
-0.750 -0.0796 0.00935 0.00192 -0.0013 0.2992 0.2515
-0.250 -0.0266 0.00934 0.00191 -0.0004 0.2807 0.2651
0.000 0.0000 0.00936 0.00190 0.0000 0.2722 0.2722
0.250 0.0266 0.00934 0.00191 0.0004 0.2652 0.2807
0.750 0.0797 0.00935 0.00192 0.0013 0.2515 0.2992
1.000 0.1062 0.00933 0.00194 0.0017 0.2467 0.3114
1.250 0.1325 0.00932 0.00196 0.0022 0.2411 0.3255
1.500 0.1589 0.00932 0.00198 0.0026 0.2358 0.3397
1.750 0.1854 0.00930 0.00201 0.0031 0.2314 0.3556
2.250 0.2372 0.00926 0.00209 0.0041 0.2225 0.3970
2.500 0.2632 0.00921 0.00213 0.0047 0.2190 0.4234
2.750 0.2889 0.00916 0.00217 0.0052 0.2152 0.4512
3.000 0.3145 0.00913 0.00222 0.0058 0.2115 0.4801
3.250 0.3397 0.00911 0.00228 0.0065 0.2076 0.5119
3.500 0.3647 0.00905 0.00235 0.0072 0.2042 0.5489
3.750 0.3887 0.00893 0.00241 0.0081 0.2013 0.6003
4.000 0.4125 0.00883 0.00247 0.0091 0.1978 0.6498
4.250 0.4356 0.00874 0.00254 0.0102 0.1944 0.7000
4.750 0.4786 0.00849 0.00275 0.0133 0.1880 0.8293
5.000 0.5025 0.00853 0.00294 0.0144 0.1849 0.8792
5.250 0.5284 0.00865 0.00308 0.0151 0.1815 0.8947
5.500 0.5541 0.00878 0.00320 0.0157 0.1777 0.9043
5.750 0.5800 0.00892 0.00335 0.0163 0.1738 0.9117
6.000 0.6057 0.00904 0.00347 0.0169 0.1712 0.9190
6.250 0.6316 0.00916 0.00360 0.0175 0.1679 0.9243
6.500 0.6566 0.00933 0.00376 0.0183 0.1636 0.9317
6.750 0.6803 0.00950 0.00393 0.0193 0.1596 0.9403
7.000 0.7030 0.00965 0.00412 0.0207 0.1572 0.9516
7.250 0.7290 0.00987 0.00436 0.0214 0.1533 0.9615
7.500 0.7537 0.01009 0.00457 0.0223 0.1490 0.9691
7.750 0.7847 0.01031 0.00478 0.0216 0.1448 0.9710
8.000 0.8133 0.01047 0.00494 0.0215 0.1410 0.9721
8.250 0.8412 0.01068 0.00513 0.0214 0.1363 0.9733
8.500 0.8689 0.01090 0.00534 0.0214 0.1317 0.9746
8.750 0.8963 0.01108 0.00552 0.0215 0.1283 0.9761
9.000 0.9223 0.01129 0.00573 0.0218 0.1243 0.9776
9.250 0.9463 0.01153 0.00595 0.0225 0.1197 0.9796
9.500 0.9711 0.01173 0.00616 0.0230 0.1165 0.9813
9.750 0.9999 0.01199 0.00642 0.0227 0.1118 0.9819
10.000 1.0281 0.01232 0.00672 0.0224 0.1055 0.9826
10.250 1.0566 0.01264 0.00702 0.0220 0.0992 0.9833
10.500 1.0844 0.01301 0.00736 0.0217 0.0932 0.9842
10.750 1.1116 0.01336 0.00770 0.0216 0.0876 0.9851
11.000 1.1379 0.01374 0.00806 0.0216 0.0832 0.9863
11.250 1.1639 0.01409 0.00841 0.0216 0.0787 0.9875
11.750 1.2126 0.01493 0.00924 0.0222 0.0696 0.9908
12.000 1.2337 0.01545 0.00973 0.0231 0.0644 0.9929
12.250 1.2585 0.01589 0.01017 0.0232 0.0602 0.9945
12.500 1.2807 0.01646 0.01073 0.0236 0.0551 0.9967
12.750 1.3034 0.01698 0.01125 0.0239 0.0513 0.9987
13.000 1.3211 0.01755 0.01183 0.0251 0.0475 1.0000
13.250 1.3207 0.01795 0.01224 0.0300 0.0444 1.0000
13.500 1.3237 0.01852 0.01280 0.0339 0.0414 1.0000
13.750 1.3321 0.01903 0.01334 0.0368 0.0393 1.0000
14.000 1.3389 0.01970 0.01402 0.0397 0.0366 1.0000
14.250 1.3465 0.02038 0.01474 0.0424 0.0345 1.0000
14.500 1.3540 0.02114 0.01552 0.0449 0.0324 1.0000
14.750 1.3597 0.02205 0.01645 0.0474 0.0302 1.0000
15.000 1.3661 0.02297 0.01742 0.0496 0.0283 1.0000
15.250 1.3700 0.02411 0.01858 0.0518 0.0265 1.0000
15.500 1.3746 0.02530 0.01982 0.0536 0.0250 1.0000
15.750 1.3773 0.02671 0.02128 0.0553 0.0235 1.0000
16.000 1.3768 0.02849 0.02312 0.0567 0.0220 1.0000
16.250 1.3783 0.03031 0.02501 0.0576 0.0211 1.0000
16.500 1.3772 0.03256 0.02734 0.0581 0.0202 1.0000
16.750 1.3729 0.03538 0.03025 0.0580 0.0193 1.0000
17.000 1.3680 0.03857 0.03353 0.0573 0.0189 1.0000
17.250 1.3579 0.04270 0.03777 0.0558 0.0182 1.0000
17.500 1.3448 0.04749 0.04269 0.0536 0.0177 1.0000
17.750 1.3257 0.05330 0.04864 0.0509 0.0174 1.0000
18.000 1.3007 0.05997 0.05547 0.0478 0.0174 1.0000
18.250 1.2687 0.06765 0.06331 0.0442 0.0175 1.0000
18.500 1.2356 0.07542 0.07124 0.0407 0.0179 1.0000
18.750 1.1978 0.08399 0.07996 0.0368 0.0177 1.0000
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