E474 (14.09%) (e474-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E474 (14.09%) (e474-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.38 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e474-il-1000000.txt Download as CSV file: xf-e474-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.2163 0.08700 0.08331 -0.0258 1.0000 0.0225
-18.250 -1.2576 0.07770 0.07386 -0.0305 1.0000 0.0222
-18.000 -1.3005 0.06844 0.06443 -0.0350 1.0000 0.0219
-17.750 -1.3412 0.05945 0.05527 -0.0394 1.0000 0.0217
-17.500 -1.3740 0.05144 0.04708 -0.0436 1.0000 0.0217
-17.250 -1.3970 0.04486 0.04034 -0.0471 1.0000 0.0220
-17.000 -1.4118 0.03971 0.03504 -0.0497 1.0000 0.0225
-16.750 -1.4206 0.03575 0.03097 -0.0513 1.0000 0.0230
-16.500 -1.4310 0.03215 0.02726 -0.0520 1.0000 0.0240
-16.250 -1.4359 0.02954 0.02457 -0.0517 1.0000 0.0251
-16.000 -1.4373 0.02755 0.02250 -0.0507 1.0000 0.0266
-15.750 -1.4376 0.02585 0.02073 -0.0492 1.0000 0.0280
-15.500 -1.4378 0.02432 0.01916 -0.0471 1.0000 0.0300
-15.250 -1.4328 0.02322 0.01800 -0.0451 1.0000 0.0319
-15.000 -1.4301 0.02206 0.01682 -0.0426 1.0000 0.0344
-14.750 -1.4238 0.02116 0.01589 -0.0402 1.0000 0.0371
-14.500 -1.4173 0.02031 0.01501 -0.0376 1.0000 0.0396
-14.250 -1.4100 0.01955 0.01423 -0.0349 1.0000 0.0427
-14.000 -1.4010 0.01893 0.01358 -0.0321 1.0000 0.0454
-13.750 -1.3943 0.01828 0.01292 -0.0289 1.0000 0.0487
-13.500 -1.3834 0.01781 0.01243 -0.0262 1.0000 0.0512
-13.250 -1.3722 0.01719 0.01182 -0.0236 1.0000 0.0550
-13.000 -1.3579 0.01671 0.01132 -0.0214 1.0000 0.0584
-12.750 -1.3437 0.01622 0.01082 -0.0192 1.0000 0.0621
-12.500 -1.3293 0.01573 0.01034 -0.0169 1.0000 0.0665
-12.250 -1.3135 0.01533 0.00993 -0.0148 1.0000 0.0702
-12.000 -1.2990 0.01488 0.00949 -0.0125 1.0000 0.0748
-11.500 -1.2679 0.01411 0.00874 -0.0081 1.0000 0.0841
-11.250 -1.2512 0.01380 0.00841 -0.0060 1.0000 0.0880
-11.000 -1.2346 0.01346 0.00807 -0.0039 1.0000 0.0925
-10.750 -1.2178 0.01313 0.00776 -0.0019 1.0000 0.0973
-10.500 -1.1990 0.01290 0.00750 -0.0001 1.0000 0.1005
-10.250 -1.1815 0.01257 0.00718 0.0018 1.0000 0.1053
-10.000 -1.1626 0.01230 0.00691 0.0036 1.0000 0.1096
-9.750 -1.1424 0.01210 0.00669 0.0051 1.0000 0.1127
-9.500 -1.1234 0.01180 0.00641 0.0068 1.0000 0.1180
-9.250 -1.1031 0.01157 0.00619 0.0083 1.0000 0.1226
-9.000 -1.0817 0.01141 0.00601 0.0096 1.0000 0.1262
-8.750 -1.0617 0.01114 0.00577 0.0112 1.0000 0.1321
-8.500 -1.0383 0.01096 0.00560 0.0121 0.9998 0.1365
-8.250 -1.0040 0.01083 0.00544 0.0108 0.9985 0.1397
-8.000 -0.9692 0.01058 0.00523 0.0093 0.9967 0.1457
-7.750 -0.9311 0.01043 0.00509 0.0073 0.9948 0.1503
-7.500 -0.8891 0.01032 0.00495 0.0044 0.9931 0.1540
-7.250 -0.8520 0.01005 0.00474 0.0026 0.9899 0.1598
-7.000 -0.8104 0.00987 0.00457 -0.0002 0.9866 0.1646
-6.750 -0.7657 0.00971 0.00439 -0.0035 0.9840 0.1684
-6.500 -0.7214 0.00944 0.00417 -0.0068 0.9821 0.1744
-6.250 -0.6847 0.00927 0.00402 -0.0085 0.9799 0.1787
-6.000 -0.6536 0.00916 0.00389 -0.0090 0.9765 0.1816
-5.750 -0.6185 0.00893 0.00369 -0.0103 0.9739 0.1863
-5.500 -0.5825 0.00874 0.00353 -0.0119 0.9712 0.1910
-5.250 -0.5474 0.00859 0.00339 -0.0131 0.9687 0.1948
-5.000 -0.5199 0.00850 0.00327 -0.0128 0.9630 0.1970
-4.750 -0.4911 0.00828 0.00309 -0.0127 0.9566 0.2021
-4.500 -0.4629 0.00813 0.00296 -0.0125 0.9493 0.2063
-4.250 -0.4356 0.00801 0.00283 -0.0120 0.9401 0.2098
-4.000 -0.4087 0.00792 0.00272 -0.0114 0.9294 0.2123
-3.750 -0.3823 0.00777 0.00257 -0.0108 0.9153 0.2168
-3.500 -0.3562 0.00764 0.00243 -0.0100 0.8910 0.2214
-3.250 -0.3314 0.00763 0.00227 -0.0089 0.8375 0.2252
-3.000 -0.3088 0.00781 0.00215 -0.0074 0.7599 0.2280
-2.750 -0.2858 0.00795 0.00207 -0.0062 0.6926 0.2323
-2.500 -0.2618 0.00807 0.00201 -0.0052 0.6322 0.2375
-2.250 -0.2370 0.00821 0.00196 -0.0044 0.5757 0.2421
-2.000 -0.2114 0.00834 0.00192 -0.0037 0.5249 0.2456
-1.750 -0.1860 0.00840 0.00187 -0.0031 0.4824 0.2520
-1.250 -0.1333 0.00853 0.00180 -0.0021 0.4161 0.2641
-1.000 -0.1069 0.00856 0.00178 -0.0017 0.3891 0.2719
-0.750 -0.0802 0.00862 0.00176 -0.0012 0.3643 0.2789
-0.500 -0.0537 0.00863 0.00174 -0.0008 0.3437 0.2893
-0.250 -0.0269 0.00865 0.00173 -0.0004 0.3270 0.3002
0.000 0.0000 0.00866 0.00173 0.0000 0.3124 0.3124
0.250 0.0269 0.00865 0.00173 0.0004 0.3002 0.3270
0.500 0.0537 0.00863 0.00174 0.0008 0.2891 0.3438
0.750 0.0802 0.00862 0.00176 0.0012 0.2789 0.3641
1.000 0.1069 0.00856 0.00178 0.0017 0.2719 0.3893
1.250 0.1333 0.00853 0.00180 0.0021 0.2642 0.4161
1.500 0.1598 0.00847 0.00183 0.0026 0.2580 0.4469
1.750 0.1860 0.00840 0.00187 0.0031 0.2520 0.4824
2.000 0.2114 0.00834 0.00192 0.0037 0.2458 0.5244
2.250 0.2370 0.00821 0.00196 0.0044 0.2421 0.5755
2.500 0.2618 0.00807 0.00201 0.0052 0.2375 0.6322
2.750 0.2858 0.00795 0.00207 0.0062 0.2324 0.6926
3.000 0.3088 0.00781 0.00215 0.0074 0.2280 0.7597
3.250 0.3314 0.00763 0.00226 0.0089 0.2252 0.8370
3.500 0.3562 0.00764 0.00243 0.0100 0.2214 0.8913
3.750 0.3823 0.00776 0.00257 0.0108 0.2168 0.9153
4.000 0.4087 0.00792 0.00272 0.0114 0.2123 0.9294
4.250 0.4356 0.00801 0.00283 0.0120 0.2097 0.9402
4.500 0.4630 0.00813 0.00296 0.0124 0.2063 0.9491
4.750 0.4910 0.00828 0.00309 0.0127 0.2021 0.9565
5.000 0.5199 0.00849 0.00327 0.0128 0.1970 0.9629
5.250 0.5474 0.00859 0.00339 0.0131 0.1948 0.9687
5.500 0.5829 0.00874 0.00354 0.0118 0.1912 0.9713
5.750 0.6188 0.00893 0.00369 0.0103 0.1863 0.9740
6.000 0.6536 0.00916 0.00389 0.0090 0.1816 0.9766
6.250 0.6847 0.00927 0.00402 0.0085 0.1786 0.9799
6.500 0.7217 0.00944 0.00417 0.0068 0.1745 0.9821
6.750 0.7656 0.00970 0.00439 0.0035 0.1684 0.9840
7.000 0.8102 0.00987 0.00457 0.0002 0.1648 0.9866
7.250 0.8519 0.01005 0.00474 -0.0026 0.1598 0.9899
7.500 0.8891 0.01032 0.00495 -0.0044 0.1538 0.9931
7.750 0.9312 0.01043 0.00509 -0.0073 0.1503 0.9948
8.000 0.9694 0.01058 0.00523 -0.0094 0.1458 0.9967
8.250 1.0042 0.01083 0.00543 -0.0108 0.1397 0.9985
8.500 1.0384 0.01096 0.00560 -0.0121 0.1365 0.9998
8.750 1.0616 0.01113 0.00577 -0.0111 0.1322 1.0000
9.000 1.0817 0.01141 0.00600 -0.0096 0.1265 1.0000
9.250 1.1031 0.01157 0.00619 -0.0083 0.1228 1.0000
9.500 1.1233 0.01180 0.00641 -0.0068 0.1179 1.0000
9.750 1.1424 0.01210 0.00669 -0.0051 0.1126 1.0000
10.000 1.1625 0.01229 0.00691 -0.0036 0.1096 1.0000
10.250 1.1814 0.01256 0.00718 -0.0018 0.1054 1.0000
10.500 1.1989 0.01290 0.00750 0.0001 0.1005 1.0000
10.750 1.2177 0.01313 0.00776 0.0019 0.0971 1.0000
11.000 1.2346 0.01346 0.00807 0.0039 0.0925 1.0000
11.250 1.2511 0.01380 0.00841 0.0060 0.0882 1.0000
11.500 1.2677 0.01412 0.00874 0.0081 0.0838 1.0000
11.750 1.2823 0.01456 0.00915 0.0105 0.0785 1.0000
12.000 1.2990 0.01487 0.00949 0.0125 0.0749 1.0000
12.250 1.3134 0.01534 0.00993 0.0148 0.0700 1.0000
12.500 1.3293 0.01574 0.01034 0.0169 0.0663 1.0000
12.750 1.3437 0.01623 0.01082 0.0192 0.0620 1.0000
13.000 1.3581 0.01671 0.01132 0.0214 0.0584 1.0000
13.250 1.3723 0.01720 0.01182 0.0236 0.0550 1.0000
13.500 1.3837 0.01781 0.01242 0.0261 0.0512 1.0000
13.750 1.3946 0.01828 0.01293 0.0289 0.0486 1.0000
14.000 1.4014 0.01893 0.01358 0.0321 0.0454 1.0000
14.250 1.4103 0.01956 0.01423 0.0348 0.0424 1.0000
14.500 1.4184 0.02028 0.01499 0.0374 0.0399 1.0000
14.750 1.4243 0.02116 0.01588 0.0401 0.0370 1.0000
15.000 1.4312 0.02203 0.01679 0.0425 0.0346 1.0000
15.250 1.4337 0.02320 0.01799 0.0450 0.0321 1.0000
15.500 1.4384 0.02432 0.01916 0.0470 0.0299 1.0000
15.750 1.4385 0.02583 0.02072 0.0490 0.0280 1.0000
16.000 1.4386 0.02751 0.02246 0.0505 0.0264 1.0000
16.250 1.4380 0.02944 0.02447 0.0515 0.0252 1.0000
16.500 1.4317 0.03218 0.02728 0.0518 0.0239 1.0000
16.750 1.4223 0.03569 0.03089 0.0511 0.0229 1.0000
17.000 1.4138 0.03962 0.03495 0.0496 0.0223 1.0000
17.250 1.3999 0.04466 0.04013 0.0470 0.0219 1.0000
17.500 1.3779 0.05112 0.04675 0.0435 0.0218 1.0000
17.750 1.3445 0.05925 0.05506 0.0392 0.0217 1.0000
18.000 1.3043 0.06819 0.06418 0.0348 0.0219 1.0000
18.250 1.2609 0.07753 0.07368 0.0302 0.0221 1.0000
18.500 1.2205 0.08669 0.08299 0.0257 0.0223 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E474 (14.09%) (e474-il)