E474 (14.09%) (e474-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.71 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e474-il-1000000-n5.txt Download as CSV file: xf-e474-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
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
------ -------- --------- --------- -------- -------- --------
-18.250 -1.2049 0.08537 0.08144 -0.0261 1.0000 0.0157
-18.000 -1.2450 0.07626 0.07218 -0.0306 1.0000 0.0155
-17.750 -1.2881 0.06691 0.06266 -0.0352 1.0000 0.0154
-17.500 -1.3275 0.05804 0.05360 -0.0396 1.0000 0.0152
-17.250 -1.3573 0.05041 0.04580 -0.0436 1.0000 0.0152
-17.000 -1.3776 0.04417 0.03940 -0.0470 1.0000 0.0153
-16.750 -1.3900 0.03934 0.03443 -0.0494 1.0000 0.0156
-16.500 -1.3975 0.03555 0.03053 -0.0509 1.0000 0.0159
-16.250 -1.4036 0.03239 0.02726 -0.0515 1.0000 0.0164
-16.000 -1.4085 0.02975 0.02454 -0.0512 1.0000 0.0173
-15.750 -1.4081 0.02788 0.02258 -0.0503 1.0000 0.0178
-15.500 -1.4061 0.02630 0.02094 -0.0489 1.0000 0.0186
-15.250 -1.4033 0.02494 0.01951 -0.0472 1.0000 0.0196
-15.000 -1.3997 0.02373 0.01825 -0.0452 1.0000 0.0206
-14.750 -1.3953 0.02266 0.01714 -0.0429 1.0000 0.0225
-14.500 -1.3887 0.02176 0.01619 -0.0405 1.0000 0.0237
-14.250 -1.3826 0.02089 0.01529 -0.0379 1.0000 0.0258
-14.000 -1.3742 0.02018 0.01455 -0.0354 1.0000 0.0276
-13.750 -1.3672 0.01946 0.01382 -0.0324 1.0000 0.0300
-13.500 -1.3583 0.01891 0.01323 -0.0295 1.0000 0.0320
-13.250 -1.3510 0.01831 0.01262 -0.0263 1.0000 0.0345
-13.000 -1.3384 0.01779 0.01209 -0.0239 1.0000 0.0370
-12.750 -1.3257 0.01724 0.01152 -0.0214 1.0000 0.0398
-12.500 -1.3121 0.01673 0.01101 -0.0191 1.0000 0.0435
-12.250 -1.2983 0.01623 0.01050 -0.0168 1.0000 0.0467
-12.000 -1.2835 0.01579 0.01006 -0.0145 1.0000 0.0502
-11.750 -1.2697 0.01531 0.00959 -0.0121 1.0000 0.0545
-11.500 -1.2548 0.01490 0.00919 -0.0098 1.0000 0.0586
-11.250 -1.2399 0.01450 0.00879 -0.0075 1.0000 0.0624
-11.000 -1.2244 0.01412 0.00841 -0.0052 1.0000 0.0668
-10.750 -1.2007 0.01370 0.00802 -0.0046 0.9993 0.0717
-10.500 -1.1734 0.01332 0.00764 -0.0048 0.9982 0.0765
-10.250 -1.1453 0.01297 0.00729 -0.0050 0.9970 0.0810
-10.000 -1.1170 0.01261 0.00695 -0.0053 0.9957 0.0863
-9.750 -1.0884 0.01230 0.00665 -0.0056 0.9946 0.0911
-9.500 -1.0600 0.01195 0.00634 -0.0059 0.9936 0.0985
-9.250 -1.0315 0.01164 0.00606 -0.0061 0.9926 0.1049
-9.000 -1.0048 0.01136 0.00580 -0.0059 0.9910 0.1103
-8.750 -0.9766 0.01114 0.00557 -0.0060 0.9895 0.1142
-8.500 -0.9483 0.01088 0.00534 -0.0061 0.9880 0.1189
-8.250 -0.9185 0.01067 0.00513 -0.0065 0.9866 0.1234
-8.000 -0.8859 0.01047 0.00492 -0.0074 0.9851 0.1269
-7.750 -0.8487 0.01020 0.00468 -0.0094 0.9832 0.1323
-7.500 -0.8061 0.00994 0.00444 -0.0124 0.9809 0.1374
-7.250 -0.7737 0.00970 0.00420 -0.0131 0.9723 0.1415
-7.000 -0.7416 0.00947 0.00399 -0.0139 0.9648 0.1468
-6.750 -0.7123 0.00929 0.00380 -0.0139 0.9550 0.1507
-6.500 -0.6851 0.00915 0.00364 -0.0136 0.9456 0.1534
-6.250 -0.6574 0.00897 0.00347 -0.0133 0.9377 0.1582
-6.000 -0.6311 0.00882 0.00333 -0.0128 0.9293 0.1621
-5.750 -0.6040 0.00870 0.00319 -0.0124 0.9182 0.1654
-5.500 -0.5775 0.00860 0.00304 -0.0118 0.9015 0.1684
-5.250 -0.5518 0.00848 0.00289 -0.0111 0.8745 0.1725
-5.000 -0.5282 0.00850 0.00272 -0.0098 0.8152 0.1759
-4.750 -0.5055 0.00864 0.00261 -0.0085 0.7436 0.1793
-4.500 -0.4814 0.00877 0.00252 -0.0075 0.6809 0.1818
-4.250 -0.4568 0.00884 0.00242 -0.0067 0.6258 0.1855
-4.000 -0.4313 0.00889 0.00234 -0.0060 0.5821 0.1890
-3.750 -0.4053 0.00894 0.00227 -0.0055 0.5413 0.1925
-3.500 -0.3792 0.00901 0.00220 -0.0050 0.4995 0.1959
-3.250 -0.3529 0.00906 0.00213 -0.0045 0.4632 0.1988
-3.000 -0.3264 0.00908 0.00206 -0.0040 0.4326 0.2026
-2.750 -0.2996 0.00909 0.00200 -0.0036 0.4081 0.2063
-2.500 -0.2726 0.00911 0.00196 -0.0033 0.3855 0.2103
-2.250 -0.2455 0.00915 0.00191 -0.0029 0.3638 0.2131
-2.000 -0.2187 0.00915 0.00186 -0.0025 0.3438 0.2173
-1.750 -0.1916 0.00916 0.00183 -0.0022 0.3273 0.2214
-1.500 -0.1643 0.00916 0.00180 -0.0019 0.3139 0.2258
-1.250 -0.1368 0.00917 0.00177 -0.0016 0.3027 0.2297
-1.000 -0.1096 0.00916 0.00175 -0.0012 0.2919 0.2351
-0.750 -0.0823 0.00917 0.00173 -0.0009 0.2811 0.2399
-0.500 -0.0547 0.00918 0.00172 -0.0006 0.2721 0.2448
-0.250 -0.0275 0.00917 0.00171 -0.0003 0.2642 0.2517
0.000 0.0000 0.00917 0.00171 0.0000 0.2582 0.2581
0.250 0.0275 0.00917 0.00171 0.0003 0.2518 0.2642
0.500 0.0547 0.00918 0.00172 0.0006 0.2447 0.2722
0.750 0.0823 0.00917 0.00173 0.0009 0.2399 0.2808
1.000 0.1096 0.00916 0.00175 0.0012 0.2350 0.2920
1.250 0.1368 0.00917 0.00177 0.0016 0.2299 0.3027
1.500 0.1643 0.00917 0.00180 0.0019 0.2258 0.3139
1.750 0.1916 0.00916 0.00183 0.0022 0.2214 0.3273
2.000 0.2187 0.00915 0.00186 0.0025 0.2174 0.3436
2.250 0.2455 0.00915 0.00191 0.0029 0.2130 0.3636
2.500 0.2726 0.00911 0.00196 0.0033 0.2102 0.3855
2.750 0.2996 0.00909 0.00200 0.0036 0.2064 0.4080
3.000 0.3264 0.00908 0.00206 0.0040 0.2026 0.4325
3.250 0.3529 0.00906 0.00213 0.0045 0.1987 0.4627
3.500 0.3792 0.00900 0.00220 0.0050 0.1959 0.5002
3.750 0.4053 0.00894 0.00227 0.0055 0.1926 0.5413
4.000 0.4313 0.00889 0.00234 0.0060 0.1890 0.5819
4.250 0.4568 0.00884 0.00242 0.0067 0.1855 0.6259
4.500 0.4815 0.00878 0.00252 0.0075 0.1818 0.6794
4.750 0.5055 0.00864 0.00261 0.0085 0.1793 0.7434
5.000 0.5283 0.00850 0.00272 0.0098 0.1759 0.8138
5.250 0.5518 0.00848 0.00289 0.0111 0.1725 0.8744
5.500 0.5775 0.00859 0.00304 0.0118 0.1687 0.9023
5.750 0.6040 0.00870 0.00319 0.0124 0.1654 0.9186
6.000 0.6311 0.00882 0.00333 0.0128 0.1621 0.9294
6.250 0.6574 0.00897 0.00347 0.0133 0.1580 0.9378
6.500 0.6851 0.00915 0.00364 0.0136 0.1532 0.9458
6.750 0.7124 0.00929 0.00380 0.0139 0.1507 0.9552
7.000 0.7416 0.00947 0.00399 0.0139 0.1463 0.9646
7.250 0.7737 0.00970 0.00420 0.0131 0.1417 0.9722
7.500 0.8061 0.00994 0.00444 0.0124 0.1376 0.9810
7.750 0.8488 0.01019 0.00468 0.0094 0.1324 0.9832
8.000 0.8860 0.01047 0.00492 0.0074 0.1270 0.9851
8.250 0.9186 0.01067 0.00513 0.0065 0.1235 0.9866
8.500 0.9483 0.01088 0.00534 0.0061 0.1189 0.9880
8.750 0.9767 0.01114 0.00557 0.0060 0.1142 0.9895
9.000 1.0049 0.01136 0.00580 0.0059 0.1105 0.9910
9.250 1.0315 0.01164 0.00605 0.0061 0.1049 0.9926
9.500 1.0601 0.01195 0.00634 0.0059 0.0984 0.9936
9.750 1.0885 0.01231 0.00666 0.0055 0.0907 0.9946
10.000 1.1172 0.01261 0.00695 0.0053 0.0863 0.9957
10.250 1.1455 0.01296 0.00729 0.0050 0.0811 0.9970
10.500 1.1735 0.01332 0.00764 0.0047 0.0766 0.9983
10.750 1.2007 0.01372 0.00803 0.0046 0.0712 0.9994
11.000 1.2243 0.01412 0.00841 0.0052 0.0667 1.0000
11.250 1.2400 0.01449 0.00878 0.0075 0.0626 1.0000
11.500 1.2546 0.01491 0.00919 0.0098 0.0583 1.0000
11.750 1.2696 0.01531 0.00960 0.0121 0.0544 1.0000
12.000 1.2836 0.01578 0.01006 0.0145 0.0503 1.0000
12.250 1.2980 0.01625 0.01052 0.0168 0.0463 1.0000
12.500 1.3119 0.01675 0.01102 0.0191 0.0430 1.0000
12.750 1.3256 0.01725 0.01153 0.0214 0.0396 1.0000
13.000 1.3386 0.01779 0.01208 0.0238 0.0371 1.0000
13.250 1.3512 0.01831 0.01262 0.0262 0.0344 1.0000
13.500 1.3587 0.01891 0.01323 0.0295 0.0320 1.0000
13.750 1.3675 0.01947 0.01382 0.0324 0.0299 1.0000
14.000 1.3747 0.02018 0.01454 0.0353 0.0276 1.0000
14.250 1.3826 0.02091 0.01531 0.0379 0.0255 1.0000
14.500 1.3904 0.02170 0.01614 0.0403 0.0241 1.0000
14.750 1.3958 0.02266 0.01714 0.0428 0.0223 1.0000
15.000 1.4018 0.02365 0.01818 0.0449 0.0210 1.0000
15.250 1.4058 0.02483 0.01941 0.0470 0.0200 1.0000
15.500 1.4071 0.02628 0.02092 0.0488 0.0186 1.0000
15.750 1.4095 0.02783 0.02253 0.0501 0.0179 1.0000
16.000 1.4083 0.02984 0.02462 0.0511 0.0170 1.0000
16.250 1.4062 0.03222 0.02709 0.0513 0.0166 1.0000
16.500 1.3990 0.03551 0.03048 0.0507 0.0158 1.0000
16.750 1.3918 0.03927 0.03435 0.0492 0.0155 1.0000
17.000 1.3795 0.04411 0.03934 0.0468 0.0153 1.0000
17.250 1.3600 0.05026 0.04564 0.0434 0.0151 1.0000
17.500 1.3310 0.05780 0.05336 0.0394 0.0153 1.0000
17.750 1.2925 0.06656 0.06230 0.0351 0.0154 1.0000
18.000 1.2487 0.07602 0.07194 0.0304 0.0155 1.0000
18.250 1.2075 0.08527 0.08134 0.0259 0.0157 1.0000
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Polar data table (+)
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