EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 500,000 Max Cl/Cd: 78.15 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e473-il-500000.txt Download as CSV file: xf-e473-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 473 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1656 0.09102 0.08685 -0.0218 1.0000 0.0530
-18.000 -1.1837 0.08519 0.08097 -0.0243 1.0000 0.0547
-17.750 -1.2011 0.07956 0.07527 -0.0268 1.0000 0.0567
-17.500 -1.2163 0.07439 0.06999 -0.0289 1.0000 0.0582
-17.250 -1.2423 0.06795 0.06349 -0.0317 1.0000 0.0596
-17.000 -1.2691 0.06155 0.05699 -0.0343 1.0000 0.0607
-16.750 -1.2952 0.05521 0.05056 -0.0369 1.0000 0.0620
-16.500 -1.3176 0.04934 0.04457 -0.0394 1.0000 0.0636
-16.250 -1.3339 0.04424 0.03935 -0.0415 1.0000 0.0654
-16.000 -1.3470 0.03962 0.03460 -0.0434 1.0000 0.0674
-15.750 -1.3613 0.03512 0.03002 -0.0451 1.0000 0.0698
-15.500 -1.3684 0.03184 0.02666 -0.0457 1.0000 0.0727
-15.000 -1.3747 0.02716 0.02182 -0.0446 1.0000 0.0792
-14.750 -1.3746 0.02551 0.02011 -0.0431 1.0000 0.0829
-14.500 -1.3707 0.02427 0.01881 -0.0413 1.0000 0.0867
-14.250 -1.3706 0.02298 0.01749 -0.0387 1.0000 0.0907
-14.000 -1.3642 0.02211 0.01658 -0.0364 1.0000 0.0952
-13.750 -1.3593 0.02125 0.01569 -0.0335 1.0000 0.0991
-13.500 -1.3541 0.02049 0.01492 -0.0305 1.0000 0.1039
-13.250 -1.3440 0.01999 0.01436 -0.0278 1.0000 0.1080
-13.000 -1.3414 0.01931 0.01368 -0.0239 1.0000 0.1126
-12.750 -1.3324 0.01882 0.01317 -0.0208 1.0000 0.1173
-12.500 -1.3192 0.01834 0.01264 -0.0184 1.0000 0.1219
-12.250 -1.3071 0.01779 0.01211 -0.0159 1.0000 0.1272
-12.000 -1.2901 0.01743 0.01169 -0.0140 1.0000 0.1323
-11.750 -1.2762 0.01693 0.01120 -0.0117 1.0000 0.1374
-11.500 -1.2593 0.01655 0.01080 -0.0098 1.0000 0.1427
-11.250 -1.2410 0.01621 0.01042 -0.0081 1.0000 0.1476
-11.000 -1.2243 0.01581 0.01005 -0.0061 1.0000 0.1536
-10.750 -1.2037 0.01559 0.00977 -0.0047 1.0000 0.1592
-10.500 -1.1862 0.01521 0.00942 -0.0029 1.0000 0.1650
-10.250 -1.1662 0.01496 0.00916 -0.0014 1.0000 0.1702
-10.000 -1.1450 0.01475 0.00888 0.0000 1.0000 0.1744
-9.750 -1.1262 0.01442 0.00858 0.0017 1.0000 0.1792
-9.500 -1.1053 0.01421 0.00835 0.0031 1.0000 0.1838
-9.250 -1.0830 0.01407 0.00813 0.0043 1.0000 0.1878
-9.000 -1.0634 0.01375 0.00785 0.0059 1.0000 0.1922
-8.750 -1.0421 0.01357 0.00768 0.0073 1.0000 0.1967
-8.500 -1.0199 0.01345 0.00749 0.0086 1.0000 0.2008
-8.250 -0.9984 0.01325 0.00726 0.0099 1.0000 0.2045
-8.000 -0.9776 0.01302 0.00707 0.0113 1.0000 0.2085
-7.750 -0.9558 0.01288 0.00692 0.0127 1.0000 0.2124
-7.500 -0.9335 0.01277 0.00677 0.0139 1.0000 0.2160
-7.250 -0.9117 0.01263 0.00658 0.0152 1.0000 0.2192
-7.000 -0.8910 0.01240 0.00639 0.0167 1.0000 0.2231
-6.750 -0.8694 0.01227 0.00627 0.0180 1.0000 0.2264
-6.500 -0.8335 0.01220 0.00618 0.0165 0.9978 0.2306
-6.250 -0.7895 0.01215 0.00606 0.0133 0.9940 0.2343
-6.000 -0.7488 0.01185 0.00584 0.0107 0.9897 0.2391
-5.750 -0.7079 0.01171 0.00571 0.0082 0.9848 0.2433
-5.500 -0.6631 0.01159 0.00557 0.0049 0.9810 0.2474
-5.250 -0.6270 0.01141 0.00535 0.0035 0.9719 0.2505
-5.000 -0.5928 0.01104 0.00505 0.0023 0.9608 0.2548
-4.750 -0.5605 0.01081 0.00485 0.0018 0.9447 0.2585
-4.500 -0.5182 0.01060 0.00462 -0.0008 0.9268 0.2626
-4.250 -0.4452 0.01035 0.00429 -0.0099 0.8933 0.2669
-4.000 -0.3990 0.01020 0.00393 -0.0133 0.8089 0.2718
-3.750 -0.3766 0.01036 0.00381 -0.0118 0.7336 0.2753
-3.500 -0.3545 0.01051 0.00370 -0.0103 0.6723 0.2786
-3.250 -0.3313 0.01064 0.00360 -0.0090 0.6193 0.2815
-3.000 -0.3075 0.01071 0.00349 -0.0080 0.5729 0.2845
-2.750 -0.2839 0.01070 0.00336 -0.0070 0.5329 0.2887
-2.500 -0.2593 0.01075 0.00329 -0.0061 0.4970 0.2925
-2.250 -0.2339 0.01081 0.00323 -0.0054 0.4661 0.2963
-2.000 -0.2082 0.01089 0.00316 -0.0047 0.4406 0.2995
-1.750 -0.1829 0.01085 0.00308 -0.0040 0.4199 0.3039
-1.500 -0.1573 0.01085 0.00303 -0.0034 0.4027 0.3086
-1.000 -0.1044 0.01092 0.00297 -0.0023 0.3757 0.3172
-0.750 -0.0788 0.01086 0.00292 -0.0017 0.3653 0.3227
-0.500 -0.0527 0.01087 0.00291 -0.0011 0.3557 0.3286
-0.250 -0.0259 0.01090 0.00290 -0.0006 0.3479 0.3342
0.000 0.0000 0.01086 0.00289 0.0000 0.3408 0.3408
0.250 0.0259 0.01090 0.00290 0.0006 0.3342 0.3479
0.500 0.0527 0.01087 0.00291 0.0011 0.3286 0.3556
0.750 0.0788 0.01086 0.00292 0.0017 0.3227 0.3654
1.000 0.1044 0.01092 0.00297 0.0023 0.3172 0.3758
1.500 0.1573 0.01085 0.00303 0.0034 0.3086 0.4026
1.750 0.1828 0.01085 0.00307 0.0040 0.3039 0.4200
2.000 0.2082 0.01089 0.00316 0.0047 0.2995 0.4406
2.250 0.2339 0.01081 0.00323 0.0054 0.2962 0.4661
2.500 0.2592 0.01075 0.00329 0.0061 0.2925 0.4971
2.750 0.2839 0.01070 0.00337 0.0070 0.2887 0.5328
3.000 0.3075 0.01071 0.00349 0.0080 0.2845 0.5729
3.250 0.3313 0.01064 0.00360 0.0090 0.2815 0.6192
3.500 0.3545 0.01051 0.00370 0.0103 0.2786 0.6722
3.750 0.3766 0.01036 0.00381 0.0118 0.2753 0.7337
4.000 0.3990 0.01021 0.00393 0.0133 0.2719 0.8086
4.250 0.4447 0.01035 0.00429 0.0100 0.2669 0.8929
4.500 0.5182 0.01060 0.00462 0.0008 0.2626 0.9268
4.750 0.5606 0.01081 0.00484 -0.0018 0.2584 0.9447
5.000 0.5928 0.01104 0.00505 -0.0024 0.2548 0.9608
5.250 0.6275 0.01140 0.00535 -0.0035 0.2506 0.9721
5.500 0.6632 0.01159 0.00557 -0.0049 0.2474 0.9810
5.750 0.7080 0.01171 0.00571 -0.0082 0.2432 0.9849
6.000 0.7489 0.01185 0.00584 -0.0107 0.2390 0.9898
6.250 0.7895 0.01215 0.00606 -0.0133 0.2342 0.9940
6.500 0.8337 0.01221 0.00618 -0.0165 0.2307 0.9979
6.750 0.8693 0.01227 0.00627 -0.0180 0.2265 1.0000
7.000 0.8909 0.01239 0.00638 -0.0167 0.2230 1.0000
7.250 0.9116 0.01263 0.00657 -0.0152 0.2192 1.0000
7.500 0.9335 0.01277 0.00676 -0.0139 0.2160 1.0000
7.750 0.9557 0.01288 0.00692 -0.0126 0.2124 1.0000
8.000 0.9775 0.01302 0.00706 -0.0113 0.2085 1.0000
8.250 0.9983 0.01325 0.00726 -0.0099 0.2046 1.0000
8.500 1.0199 0.01345 0.00749 -0.0085 0.2008 1.0000
8.750 1.0421 0.01357 0.00767 -0.0073 0.1966 1.0000
9.000 1.0633 0.01375 0.00785 -0.0059 0.1923 1.0000
9.250 1.0830 0.01407 0.00813 -0.0043 0.1877 1.0000
9.500 1.1053 0.01421 0.00835 -0.0031 0.1838 1.0000
9.750 1.1262 0.01441 0.00858 -0.0017 0.1792 1.0000
10.000 1.1450 0.01475 0.00887 0.0000 0.1744 1.0000
10.250 1.1662 0.01496 0.00916 0.0014 0.1702 1.0000
10.500 1.1862 0.01521 0.00942 0.0029 0.1650 1.0000
10.750 1.2037 0.01559 0.00977 0.0047 0.1592 1.0000
11.000 1.2243 0.01581 0.01005 0.0061 0.1535 1.0000
11.250 1.2411 0.01621 0.01042 0.0081 0.1476 1.0000
11.500 1.2594 0.01654 0.01080 0.0098 0.1426 1.0000
11.750 1.2763 0.01692 0.01120 0.0117 0.1374 1.0000
12.000 1.2903 0.01743 0.01169 0.0140 0.1323 1.0000
12.250 1.3072 0.01779 0.01210 0.0159 0.1273 1.0000
12.500 1.3195 0.01833 0.01264 0.0184 0.1220 1.0000
12.750 1.3327 0.01882 0.01316 0.0207 0.1173 1.0000
13.000 1.3418 0.01931 0.01368 0.0238 0.1126 1.0000
13.250 1.3445 0.01999 0.01435 0.0277 0.1080 1.0000
13.500 1.3546 0.02049 0.01492 0.0304 0.1038 1.0000
13.750 1.3602 0.02123 0.01568 0.0334 0.0993 1.0000
14.000 1.3649 0.02210 0.01657 0.0362 0.0950 1.0000
14.250 1.3712 0.02297 0.01749 0.0386 0.0908 1.0000
14.500 1.3713 0.02427 0.01881 0.0412 0.0866 1.0000
14.750 1.3756 0.02548 0.02009 0.0430 0.0829 1.0000
15.000 1.3754 0.02716 0.02182 0.0445 0.0789 1.0000
15.250 1.3698 0.02954 0.02425 0.0454 0.0755 1.0000
15.500 1.3698 0.03179 0.02660 0.0456 0.0728 1.0000
15.750 1.3627 0.03507 0.02996 0.0449 0.0697 1.0000
16.000 1.3486 0.03956 0.03454 0.0433 0.0674 1.0000
16.250 1.3356 0.04419 0.03930 0.0413 0.0654 1.0000
16.500 1.3197 0.04925 0.04448 0.0392 0.0636 1.0000
16.750 1.2974 0.05514 0.05047 0.0367 0.0619 1.0000
17.000 1.2715 0.06145 0.05689 0.0341 0.0606 1.0000
17.250 1.2434 0.06805 0.06357 0.0313 0.0593 1.0000
17.500 1.2189 0.07427 0.06988 0.0287 0.0582 1.0000
17.750 1.2036 0.07949 0.07520 0.0265 0.0565 1.0000
18.000 1.1862 0.08512 0.08090 0.0241 0.0546 1.0000
18.250 1.1673 0.09108 0.08690 0.0214 0.0529 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 473 AIRFOIL (e473-il)