EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 100,000 Max Cl/Cd: 35.85 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e473-il-100000-n5.txt Download as CSV file: xf-e473-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8230 0.10689 0.10055 -0.0141 1.0000 0.1206
-15.000 -0.7937 0.10904 0.10268 -0.0124 1.0000 0.1215
-14.750 -0.9270 0.08260 0.07618 -0.0263 1.0000 0.1337
-14.500 -0.8690 0.08908 0.08268 -0.0219 1.0000 0.1346
-14.250 -0.8320 0.09226 0.08585 -0.0195 1.0000 0.1357
-14.000 -1.0811 0.05188 0.04501 -0.0426 1.0000 0.1449
-13.750 -1.0919 0.04831 0.04137 -0.0436 1.0000 0.1480
-13.500 -1.0943 0.04599 0.03902 -0.0437 1.0000 0.1513
-13.250 -1.1081 0.04282 0.03571 -0.0436 1.0000 0.1547
-13.000 -1.1259 0.03976 0.03242 -0.0424 1.0000 0.1582
-12.750 -1.1274 0.03827 0.03087 -0.0405 1.0000 0.1616
-12.500 -1.1227 0.03743 0.03003 -0.0385 1.0000 0.1651
-12.250 -1.1247 0.03622 0.02871 -0.0356 1.0000 0.1689
-12.000 -1.1330 0.03476 0.02703 -0.0318 1.0000 0.1729
-11.750 -1.1245 0.03418 0.02646 -0.0293 1.0000 0.1763
-11.500 -1.1139 0.03369 0.02593 -0.0270 1.0000 0.1803
-11.250 -1.1077 0.03278 0.02487 -0.0243 1.0000 0.1848
-11.000 -1.1007 0.03182 0.02374 -0.0217 1.0000 0.1892
-10.750 -1.0839 0.03154 0.02348 -0.0200 1.0000 0.1927
-10.500 -1.0706 0.03099 0.02285 -0.0180 1.0000 0.1971
-10.250 -1.0619 0.03002 0.02163 -0.0154 1.0000 0.2021
-10.000 -1.0443 0.02961 0.02122 -0.0138 1.0000 0.2056
-9.750 -1.0264 0.02926 0.02086 -0.0122 1.0000 0.2095
-9.500 -1.0115 0.02864 0.02010 -0.0102 1.0000 0.2140
-9.250 -0.9982 0.02784 0.01907 -0.0081 1.0000 0.2187
-9.000 -0.9775 0.02754 0.01883 -0.0068 1.0000 0.2220
-8.750 -0.9586 0.02713 0.01839 -0.0053 1.0000 0.2259
-8.500 -0.9420 0.02654 0.01764 -0.0035 1.0000 0.2305
-8.250 -0.9252 0.02592 0.01686 -0.0017 1.0000 0.2349
-8.000 -0.9040 0.02558 0.01657 -0.0005 1.0000 0.2381
-7.750 -0.8843 0.02518 0.01613 0.0010 1.0000 0.2421
-7.500 -0.8660 0.02466 0.01549 0.0026 1.0000 0.2467
-7.250 -0.8476 0.02412 0.01480 0.0042 1.0000 0.2509
-7.000 -0.8261 0.02377 0.01451 0.0054 1.0000 0.2542
-6.750 -0.8057 0.02339 0.01412 0.0068 1.0000 0.2580
-6.500 -0.7861 0.02296 0.01359 0.0083 1.0000 0.2624
-6.250 -0.7672 0.02249 0.01297 0.0098 1.0000 0.2668
-6.000 -0.7457 0.02212 0.01269 0.0110 1.0000 0.2699
-5.750 -0.7249 0.02178 0.01236 0.0123 1.0000 0.2735
-5.500 -0.7048 0.02143 0.01198 0.0137 1.0000 0.2776
-5.250 -0.6853 0.02107 0.01151 0.0152 1.0000 0.2821
-5.000 -0.6651 0.02073 0.01120 0.0165 1.0000 0.2856
-4.750 -0.6201 0.02043 0.01094 0.0130 0.9887 0.2902
-4.500 -0.5778 0.02008 0.01056 0.0101 0.9737 0.2957
-4.000 -0.5050 0.01928 0.00978 0.0070 0.9292 0.3052
-3.750 -0.4629 0.01891 0.00940 0.0045 0.9023 0.3106
-3.500 -0.4142 0.01855 0.00892 0.0007 0.8667 0.3172
-3.250 -0.3605 0.01818 0.00853 -0.0039 0.8150 0.3228
-3.000 -0.3171 0.01799 0.00813 -0.0064 0.7520 0.3287
-2.750 -0.2858 0.01794 0.00777 -0.0066 0.6934 0.3346
-2.500 -0.2583 0.01789 0.00757 -0.0061 0.6413 0.3393
-2.250 -0.2321 0.01787 0.00738 -0.0055 0.5976 0.3448
-2.000 -0.2059 0.01786 0.00716 -0.0049 0.5609 0.3507
-1.500 -0.1543 0.01779 0.00690 -0.0037 0.5045 0.3624
-1.250 -0.1284 0.01780 0.00676 -0.0031 0.4822 0.3697
-1.000 -0.1029 0.01775 0.00670 -0.0024 0.4631 0.3760
-0.750 -0.0771 0.01774 0.00662 -0.0018 0.4469 0.3836
-0.500 -0.0513 0.01772 0.00657 -0.0012 0.4335 0.3914
-0.250 -0.0258 0.01772 0.00654 -0.0006 0.4218 0.4005
0.000 0.0000 0.01770 0.00654 0.0000 0.4104 0.4104
0.250 0.0258 0.01772 0.00654 0.0006 0.4005 0.4218
0.500 0.0513 0.01772 0.00657 0.0012 0.3914 0.4334
0.750 0.0771 0.01774 0.00662 0.0018 0.3836 0.4470
1.000 0.1029 0.01775 0.00670 0.0024 0.3760 0.4632
1.250 0.1284 0.01780 0.00676 0.0031 0.3697 0.4821
1.500 0.1543 0.01779 0.00690 0.0037 0.3624 0.5044
2.000 0.2059 0.01786 0.00716 0.0049 0.3507 0.5608
2.250 0.2321 0.01787 0.00738 0.0055 0.3448 0.5976
2.500 0.2583 0.01789 0.00757 0.0061 0.3394 0.6413
3.000 0.3171 0.01799 0.00813 0.0064 0.3287 0.7520
3.250 0.3606 0.01818 0.00853 0.0039 0.3228 0.8154
3.500 0.4142 0.01855 0.00892 -0.0007 0.3172 0.8667
3.750 0.4629 0.01891 0.00940 -0.0045 0.3106 0.9023
4.000 0.5051 0.01928 0.00978 -0.0070 0.3053 0.9293
4.500 0.5779 0.02008 0.01056 -0.0101 0.2957 0.9737
4.750 0.6202 0.02043 0.01094 -0.0130 0.2902 0.9889
5.000 0.6650 0.02073 0.01120 -0.0165 0.2856 1.0000
5.250 0.6853 0.02107 0.01151 -0.0152 0.2821 1.0000
5.500 0.7047 0.02143 0.01197 -0.0137 0.2776 1.0000
5.750 0.7249 0.02178 0.01236 -0.0123 0.2735 1.0000
6.000 0.7457 0.02212 0.01268 -0.0110 0.2699 1.0000
6.250 0.7672 0.02249 0.01296 -0.0098 0.2668 1.0000
6.500 0.7860 0.02295 0.01359 -0.0083 0.2624 1.0000
6.750 0.8056 0.02338 0.01411 -0.0068 0.2580 1.0000
7.000 0.8261 0.02376 0.01450 -0.0054 0.2542 1.0000
7.250 0.8476 0.02412 0.01480 -0.0042 0.2509 1.0000
7.500 0.8660 0.02466 0.01549 -0.0026 0.2467 1.0000
7.750 0.8842 0.02518 0.01613 -0.0010 0.2421 1.0000
8.000 0.9040 0.02558 0.01657 0.0005 0.2381 1.0000
8.250 0.9251 0.02592 0.01686 0.0017 0.2349 1.0000
8.500 0.9420 0.02654 0.01764 0.0035 0.2306 1.0000
8.750 0.9587 0.02713 0.01839 0.0053 0.2260 1.0000
9.000 0.9775 0.02755 0.01884 0.0068 0.2220 1.0000
9.250 0.9982 0.02784 0.01908 0.0081 0.2187 1.0000
9.500 1.0115 0.02864 0.02010 0.0102 0.2140 1.0000
9.750 1.0264 0.02925 0.02085 0.0122 0.2095 1.0000
10.000 1.0444 0.02961 0.02121 0.0138 0.2056 1.0000
10.250 1.0620 0.03002 0.02162 0.0154 0.2021 1.0000
10.500 1.0707 0.03099 0.02285 0.0179 0.1971 1.0000
10.750 1.0841 0.03154 0.02348 0.0200 0.1928 1.0000
11.000 1.1009 0.03182 0.02374 0.0217 0.1892 1.0000
11.250 1.1080 0.03278 0.02487 0.0243 0.1848 1.0000
11.500 1.1141 0.03368 0.02592 0.0270 0.1802 1.0000
11.750 1.1248 0.03418 0.02646 0.0292 0.1763 1.0000
12.000 1.1336 0.03475 0.02702 0.0317 0.1729 1.0000
12.250 1.1252 0.03622 0.02871 0.0356 0.1689 1.0000
12.500 1.1233 0.03741 0.03000 0.0384 0.1650 1.0000
12.750 1.1282 0.03825 0.03085 0.0404 0.1615 1.0000
13.000 1.1267 0.03974 0.03241 0.0423 0.1582 1.0000
13.250 1.1091 0.04279 0.03568 0.0435 0.1547 1.0000
13.500 1.0957 0.04592 0.03895 0.0436 0.1513 1.0000
13.750 1.0938 0.04820 0.04126 0.0435 0.1479 1.0000
14.000 1.0824 0.05183 0.04495 0.0425 0.1448 1.0000
14.500 0.8723 0.08875 0.08235 0.0219 0.1346 1.0000
14.750 0.9299 0.08234 0.07591 0.0263 0.1337 1.0000
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