EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 500,000 Max Cl/Cd: 78.73 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e473-il-500000-n5.txt Download as CSV file: xf-e473-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1459 0.08767 0.08315 -0.0222 1.0000 0.0414
-17.500 -1.1620 0.08215 0.07755 -0.0245 1.0000 0.0422
-17.250 -1.1807 0.07640 0.07172 -0.0270 1.0000 0.0435
-17.000 -1.2006 0.07069 0.06590 -0.0293 1.0000 0.0441
-16.750 -1.2275 0.06417 0.05928 -0.0320 1.0000 0.0451
-16.500 -1.2526 0.05791 0.05289 -0.0346 1.0000 0.0456
-16.250 -1.2777 0.05160 0.04646 -0.0372 1.0000 0.0464
-16.000 -1.2975 0.04593 0.04066 -0.0397 1.0000 0.0473
-15.750 -1.3136 0.04080 0.03540 -0.0419 1.0000 0.0489
-15.500 -1.3231 0.03669 0.03117 -0.0436 1.0000 0.0504
-15.250 -1.3326 0.03297 0.02735 -0.0446 1.0000 0.0526
-15.000 -1.3380 0.03012 0.02442 -0.0447 1.0000 0.0551
-14.750 -1.3390 0.02803 0.02224 -0.0440 1.0000 0.0574
-14.500 -1.3410 0.02616 0.02032 -0.0426 1.0000 0.0604
-14.250 -1.3402 0.02471 0.01882 -0.0407 1.0000 0.0636
-14.000 -1.3367 0.02358 0.01764 -0.0385 1.0000 0.0671
-13.750 -1.3341 0.02251 0.01654 -0.0358 1.0000 0.0703
-13.500 -1.3285 0.02169 0.01568 -0.0330 1.0000 0.0743
-13.250 -1.3231 0.02094 0.01490 -0.0300 1.0000 0.0777
-13.000 -1.3184 0.02025 0.01419 -0.0266 1.0000 0.0817
-12.750 -1.3113 0.01973 0.01363 -0.0233 1.0000 0.0855
-12.500 -1.3044 0.01912 0.01301 -0.0199 1.0000 0.0894
-12.250 -1.2925 0.01855 0.01243 -0.0174 1.0000 0.0944
-12.000 -1.2796 0.01802 0.01189 -0.0150 1.0000 0.0991
-11.750 -1.2655 0.01751 0.01137 -0.0127 1.0000 0.1042
-11.500 -1.2498 0.01707 0.01090 -0.0107 1.0000 0.1091
-11.250 -1.2345 0.01657 0.01043 -0.0086 1.0000 0.1150
-11.000 -1.2176 0.01615 0.01000 -0.0067 1.0000 0.1215
-10.750 -1.2009 0.01570 0.00958 -0.0048 1.0000 0.1287
-10.500 -1.1825 0.01533 0.00920 -0.0030 1.0000 0.1347
-10.250 -1.1642 0.01495 0.00883 -0.0013 1.0000 0.1407
-10.000 -1.1442 0.01467 0.00852 0.0002 1.0000 0.1453
-9.750 -1.1250 0.01433 0.00819 0.0019 1.0000 0.1500
-9.500 -1.1049 0.01404 0.00789 0.0034 1.0000 0.1550
-9.250 -1.0838 0.01380 0.00762 0.0047 1.0000 0.1593
-9.000 -1.0638 0.01351 0.00734 0.0063 1.0000 0.1639
-8.750 -1.0428 0.01327 0.00710 0.0077 1.0000 0.1692
-8.500 -1.0211 0.01307 0.00687 0.0090 1.0000 0.1735
-8.250 -0.9921 0.01281 0.00663 0.0087 0.9988 0.1784
-8.000 -0.9476 0.01260 0.00642 0.0053 0.9944 0.1842
-7.750 -0.9092 0.01240 0.00619 0.0032 0.9904 0.1885
-7.500 -0.8742 0.01214 0.00596 0.0017 0.9856 0.1933
-7.250 -0.8374 0.01194 0.00575 0.0000 0.9817 0.1980
-7.000 -0.8086 0.01176 0.00554 0.0000 0.9748 0.2016
-6.750 -0.7792 0.01155 0.00533 -0.0002 0.9657 0.2052
-6.500 -0.7532 0.01133 0.00512 0.0004 0.9516 0.2089
-6.250 -0.7172 0.01111 0.00490 -0.0011 0.9336 0.2131
-6.000 -0.6498 0.01087 0.00460 -0.0091 0.9087 0.2179
-5.750 -0.5890 0.01069 0.00423 -0.0158 0.8320 0.2229
-5.500 -0.5656 0.01081 0.00407 -0.0145 0.7545 0.2262
-5.250 -0.5437 0.01093 0.00394 -0.0130 0.6919 0.2291
-5.000 -0.5203 0.01101 0.00381 -0.0118 0.6420 0.2320
-4.750 -0.4963 0.01106 0.00369 -0.0108 0.5998 0.2347
-4.500 -0.4722 0.01106 0.00356 -0.0099 0.5626 0.2376
-4.250 -0.4475 0.01107 0.00346 -0.0091 0.5286 0.2406
-4.000 -0.4223 0.01109 0.00336 -0.0083 0.4965 0.2437
-3.750 -0.3967 0.01112 0.00327 -0.0077 0.4681 0.2470
-3.500 -0.3706 0.01114 0.00318 -0.0071 0.4444 0.2495
-3.250 -0.3449 0.01112 0.00308 -0.0065 0.4251 0.2522
-3.000 -0.3190 0.01109 0.00300 -0.0059 0.4081 0.2555
-2.750 -0.2927 0.01107 0.00293 -0.0054 0.3931 0.2590
-2.500 -0.2663 0.01107 0.00287 -0.0048 0.3793 0.2623
-2.250 -0.2397 0.01108 0.00281 -0.0044 0.3665 0.2651
-2.000 -0.2133 0.01107 0.00276 -0.0038 0.3548 0.2680
-1.750 -0.1869 0.01103 0.00271 -0.0033 0.3459 0.2718
-1.500 -0.1604 0.01102 0.00267 -0.0028 0.3373 0.2758
-1.250 -0.1336 0.01101 0.00264 -0.0024 0.3304 0.2794
-1.000 -0.1067 0.01102 0.00261 -0.0019 0.3233 0.2826
-0.750 -0.0803 0.01101 0.00258 -0.0014 0.3167 0.2867
-0.500 -0.0535 0.01098 0.00257 -0.0009 0.3108 0.2915
-0.250 -0.0268 0.01099 0.00256 -0.0005 0.3048 0.2960
0.000 0.0000 0.01102 0.00256 0.0000 0.3000 0.3000
0.250 0.0268 0.01099 0.00256 0.0005 0.2960 0.3048
0.500 0.0535 0.01098 0.00257 0.0009 0.2915 0.3107
0.750 0.0803 0.01101 0.00258 0.0014 0.2867 0.3168
1.000 0.1066 0.01102 0.00261 0.0019 0.2826 0.3233
1.250 0.1336 0.01101 0.00264 0.0024 0.2794 0.3304
1.500 0.1604 0.01102 0.00267 0.0028 0.2758 0.3372
1.750 0.1869 0.01103 0.00271 0.0033 0.2717 0.3459
2.000 0.2133 0.01107 0.00275 0.0038 0.2680 0.3548
2.250 0.2397 0.01108 0.00281 0.0044 0.2651 0.3665
2.500 0.2663 0.01107 0.00287 0.0048 0.2623 0.3794
2.750 0.2927 0.01107 0.00293 0.0054 0.2591 0.3931
3.000 0.3190 0.01109 0.00300 0.0059 0.2555 0.4081
3.250 0.3449 0.01112 0.00308 0.0065 0.2522 0.4251
3.500 0.3706 0.01114 0.00318 0.0071 0.2494 0.4444
3.750 0.3967 0.01112 0.00327 0.0077 0.2470 0.4682
4.000 0.4223 0.01109 0.00336 0.0083 0.2439 0.4963
4.250 0.4475 0.01107 0.00346 0.0091 0.2405 0.5282
4.500 0.4722 0.01106 0.00356 0.0099 0.2376 0.5625
4.750 0.4963 0.01106 0.00369 0.0108 0.2346 0.5998
5.000 0.5203 0.01101 0.00381 0.0118 0.2320 0.6419
5.250 0.5436 0.01093 0.00393 0.0130 0.2290 0.6934
5.500 0.5656 0.01081 0.00407 0.0145 0.2262 0.7549
5.750 0.5890 0.01069 0.00423 0.0158 0.2229 0.8309
6.000 0.6500 0.01087 0.00460 0.0091 0.2179 0.9087
6.250 0.7172 0.01111 0.00490 0.0011 0.2132 0.9336
6.500 0.7532 0.01133 0.00512 -0.0004 0.2089 0.9518
6.750 0.7792 0.01154 0.00533 0.0002 0.2053 0.9660
7.000 0.8087 0.01176 0.00554 0.0000 0.2016 0.9749
7.250 0.8377 0.01194 0.00575 0.0000 0.1980 0.9817
7.500 0.8748 0.01214 0.00596 -0.0019 0.1933 0.9858
7.750 0.9091 0.01240 0.00618 -0.0032 0.1885 0.9904
8.000 0.9476 0.01260 0.00641 -0.0053 0.1843 0.9944
8.250 0.9921 0.01281 0.00663 -0.0087 0.1784 0.9988
8.500 1.0211 0.01307 0.00687 -0.0090 0.1735 1.0000
8.750 1.0428 0.01326 0.00710 -0.0077 0.1692 1.0000
9.000 1.0637 0.01351 0.00734 -0.0063 0.1641 1.0000
9.250 1.0838 0.01380 0.00762 -0.0047 0.1593 1.0000
9.500 1.1049 0.01404 0.00789 -0.0034 0.1550 1.0000
9.750 1.1250 0.01433 0.00818 -0.0019 0.1500 1.0000
10.000 1.1442 0.01467 0.00852 -0.0002 0.1452 1.0000
10.250 1.1642 0.01495 0.00883 0.0013 0.1406 1.0000
10.500 1.1826 0.01533 0.00919 0.0030 0.1348 1.0000
10.750 1.2009 0.01570 0.00957 0.0047 0.1288 1.0000
11.000 1.2175 0.01616 0.01000 0.0067 0.1213 1.0000
11.250 1.2346 0.01657 0.01043 0.0086 0.1149 1.0000
11.500 1.2497 0.01708 0.01091 0.0107 0.1088 1.0000
11.750 1.2657 0.01751 0.01137 0.0127 0.1042 1.0000
12.000 1.2797 0.01802 0.01189 0.0150 0.0991 1.0000
12.250 1.2928 0.01855 0.01243 0.0174 0.0946 1.0000
12.500 1.3048 0.01910 0.01300 0.0199 0.0896 1.0000
12.750 1.3116 0.01973 0.01363 0.0232 0.0853 1.0000
13.000 1.3188 0.02025 0.01419 0.0265 0.0817 1.0000
13.250 1.3237 0.02093 0.01490 0.0299 0.0777 1.0000
13.500 1.3291 0.02168 0.01567 0.0329 0.0744 1.0000
13.750 1.3351 0.02249 0.01652 0.0356 0.0707 1.0000
14.250 1.3413 0.02468 0.01879 0.0406 0.0638 1.0000
14.500 1.3418 0.02615 0.02031 0.0425 0.0603 1.0000
14.750 1.3404 0.02797 0.02219 0.0439 0.0576 1.0000
15.000 1.3385 0.03014 0.02444 0.0446 0.0546 1.0000
15.250 1.3319 0.03312 0.02749 0.0444 0.0520 1.0000
15.500 1.3252 0.03657 0.03105 0.0434 0.0506 1.0000
15.750 1.3153 0.04073 0.03533 0.0418 0.0487 1.0000
16.000 1.3002 0.04575 0.04048 0.0396 0.0474 1.0000
16.250 1.2793 0.05158 0.04644 0.0370 0.0463 1.0000
16.500 1.2553 0.05775 0.05273 0.0344 0.0456 1.0000
16.750 1.2305 0.06400 0.05910 0.0318 0.0451 1.0000
17.000 1.2035 0.07055 0.06576 0.0291 0.0441 1.0000
17.250 1.1831 0.07632 0.07163 0.0267 0.0432 1.0000
17.500 1.1651 0.08199 0.07739 0.0243 0.0423 1.0000
17.750 1.1478 0.08769 0.08317 0.0218 0.0410 1.0000
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