EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.25 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e473-il-1000000.txt Download as CSV file: xf-e473-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.2376 0.08494 0.08108 -0.0236 1.0000 0.0341
-18.250 -1.2660 0.07782 0.07386 -0.0268 1.0000 0.0347
-18.000 -1.2964 0.07069 0.06662 -0.0299 1.0000 0.0350
-17.750 -1.3297 0.06338 0.05918 -0.0329 1.0000 0.0352
-17.500 -1.3599 0.05648 0.05213 -0.0358 1.0000 0.0353
-17.250 -1.3903 0.04952 0.04504 -0.0387 1.0000 0.0360
-17.000 -1.4125 0.04358 0.03896 -0.0413 1.0000 0.0367
-16.750 -1.4275 0.03862 0.03388 -0.0435 1.0000 0.0379
-16.500 -1.4384 0.03442 0.02957 -0.0451 1.0000 0.0392
-16.250 -1.4489 0.03070 0.02576 -0.0460 1.0000 0.0411
-16.000 -1.4526 0.02810 0.02307 -0.0459 1.0000 0.0430
-15.750 -1.4533 0.02608 0.02099 -0.0451 1.0000 0.0451
-15.500 -1.4563 0.02420 0.01906 -0.0435 1.0000 0.0477
-15.250 -1.4537 0.02289 0.01771 -0.0416 1.0000 0.0503
-15.000 -1.4517 0.02171 0.01649 -0.0392 1.0000 0.0532
-14.750 -1.4485 0.02070 0.01547 -0.0365 1.0000 0.0565
-14.500 -1.4420 0.01995 0.01468 -0.0338 1.0000 0.0592
-14.250 -1.4396 0.01910 0.01384 -0.0304 1.0000 0.0636
-14.000 -1.4323 0.01856 0.01325 -0.0273 1.0000 0.0665
-13.750 -1.4302 0.01792 0.01262 -0.0231 1.0000 0.0706
-13.500 -1.4243 0.01742 0.01211 -0.0195 1.0000 0.0746
-13.250 -1.4136 0.01685 0.01154 -0.0167 1.0000 0.0789
-13.000 -1.4014 0.01632 0.01101 -0.0141 1.0000 0.0838
-12.750 -1.3881 0.01581 0.01050 -0.0117 1.0000 0.0891
-12.500 -1.3734 0.01533 0.01004 -0.0095 1.0000 0.0942
-12.250 -1.3574 0.01490 0.00961 -0.0074 1.0000 0.0992
-12.000 -1.3413 0.01445 0.00918 -0.0053 1.0000 0.1049
-11.750 -1.3234 0.01409 0.00880 -0.0035 1.0000 0.1098
-11.500 -1.3062 0.01367 0.00841 -0.0016 1.0000 0.1157
-11.250 -1.2865 0.01338 0.00810 -0.0001 1.0000 0.1201
-11.000 -1.2684 0.01298 0.00773 0.0017 1.0000 0.1261
-10.750 -1.2483 0.01269 0.00744 0.0032 1.0000 0.1313
-10.500 -1.2284 0.01238 0.00713 0.0048 1.0000 0.1367
-10.250 -1.2083 0.01208 0.00685 0.0063 1.0000 0.1419
-9.750 -1.1669 0.01154 0.00635 0.0092 1.0000 0.1540
-9.500 -1.1449 0.01136 0.00615 0.0105 1.0000 0.1590
-9.250 -1.1240 0.01110 0.00591 0.0119 1.0000 0.1644
-9.000 -1.1024 0.01089 0.00572 0.0132 1.0000 0.1693
-8.750 -1.0798 0.01075 0.00555 0.0144 1.0000 0.1730
-8.500 -1.0583 0.01054 0.00535 0.0157 1.0000 0.1774
-8.250 -1.0218 0.01036 0.00520 0.0140 0.9984 0.1831
-8.000 -0.9837 0.01026 0.00509 0.0120 0.9964 0.1874
-7.750 -0.9463 0.01007 0.00492 0.0101 0.9943 0.1930
-7.500 -0.9069 0.00994 0.00481 0.0078 0.9927 0.1980
-7.250 -0.8715 0.00980 0.00466 0.0064 0.9895 0.2017
-7.000 -0.8349 0.00962 0.00448 0.0047 0.9864 0.2057
-6.750 -0.7967 0.00943 0.00433 0.0027 0.9837 0.2105
-6.500 -0.7556 0.00929 0.00420 0.0001 0.9815 0.2145
-6.250 -0.7247 0.00915 0.00404 -0.0002 0.9748 0.2173
-5.500 -0.6225 0.00853 0.00347 -0.0033 0.9387 0.2287
-5.250 -0.5452 0.00835 0.00319 -0.0135 0.8947 0.2329
-5.000 -0.5173 0.00848 0.00300 -0.0131 0.8048 0.2360
-4.750 -0.4969 0.00860 0.00289 -0.0112 0.7321 0.2396
-4.500 -0.4742 0.00870 0.00280 -0.0099 0.6741 0.2425
-4.250 -0.4500 0.00880 0.00273 -0.0089 0.6241 0.2454
-4.000 -0.4249 0.00889 0.00266 -0.0081 0.5805 0.2479
-3.750 -0.3991 0.00898 0.00260 -0.0074 0.5419 0.2497
-3.500 -0.3742 0.00897 0.00249 -0.0067 0.5078 0.2533
-3.250 -0.3487 0.00899 0.00241 -0.0060 0.4753 0.2569
-3.000 -0.3225 0.00901 0.00236 -0.0054 0.4482 0.2602
-2.750 -0.2960 0.00906 0.00231 -0.0049 0.4251 0.2631
-2.500 -0.2692 0.00910 0.00227 -0.0044 0.4054 0.2653
-2.000 -0.2162 0.00907 0.00215 -0.0034 0.3741 0.2726
-1.750 -0.1894 0.00907 0.00212 -0.0030 0.3614 0.2764
-1.500 -0.1624 0.00909 0.00210 -0.0025 0.3497 0.2798
-1.250 -0.1351 0.00912 0.00207 -0.0021 0.3394 0.2824
-1.000 -0.1083 0.00910 0.00204 -0.0017 0.3311 0.2867
-0.750 -0.0814 0.00908 0.00202 -0.0012 0.3236 0.2916
-0.500 -0.0544 0.00910 0.00202 -0.0008 0.3167 0.2960
-0.250 -0.0268 0.00910 0.00201 -0.0005 0.3113 0.2996
0.000 0.0000 0.00909 0.00200 0.0000 0.3053 0.3052
0.250 0.0268 0.00910 0.00201 0.0005 0.2996 0.3112
0.500 0.0544 0.00910 0.00202 0.0008 0.2960 0.3166
0.750 0.0814 0.00908 0.00202 0.0012 0.2916 0.3237
1.000 0.1082 0.00910 0.00204 0.0017 0.2866 0.3312
1.250 0.1351 0.00912 0.00207 0.0021 0.2824 0.3393
1.500 0.1624 0.00909 0.00210 0.0025 0.2797 0.3496
1.750 0.1894 0.00907 0.00212 0.0030 0.2764 0.3614
2.000 0.2162 0.00907 0.00215 0.0034 0.2726 0.3740
2.500 0.2692 0.00910 0.00227 0.0044 0.2654 0.4055
2.750 0.2960 0.00906 0.00231 0.0049 0.2631 0.4250
3.000 0.3225 0.00901 0.00236 0.0054 0.2602 0.4488
3.250 0.3487 0.00899 0.00241 0.0060 0.2570 0.4760
3.500 0.3742 0.00897 0.00249 0.0067 0.2533 0.5080
3.750 0.3991 0.00898 0.00260 0.0074 0.2497 0.5420
4.000 0.4249 0.00889 0.00266 0.0081 0.2479 0.5806
4.250 0.4500 0.00880 0.00273 0.0089 0.2454 0.6240
4.500 0.4742 0.00870 0.00280 0.0099 0.2425 0.6740
4.750 0.4968 0.00860 0.00289 0.0113 0.2396 0.7330
5.000 0.5174 0.00848 0.00300 0.0131 0.2360 0.8042
5.250 0.5452 0.00835 0.00319 0.0135 0.2329 0.8947
5.500 0.6225 0.00853 0.00347 0.0033 0.2287 0.9387
6.250 0.7247 0.00914 0.00404 0.0002 0.2172 0.9747
6.500 0.7556 0.00929 0.00420 -0.0001 0.2146 0.9815
6.750 0.7968 0.00943 0.00433 -0.0027 0.2105 0.9837
7.000 0.8350 0.00962 0.00448 -0.0048 0.2057 0.9864
7.250 0.8718 0.00980 0.00466 -0.0065 0.2017 0.9896
7.500 0.9069 0.00994 0.00481 -0.0078 0.1980 0.9927
7.750 0.9464 0.01007 0.00492 -0.0101 0.1930 0.9944
8.000 0.9838 0.01026 0.00509 -0.0120 0.1874 0.9964
8.250 1.0225 0.01036 0.00520 -0.0142 0.1830 0.9985
8.500 1.0582 0.01054 0.00535 -0.0157 0.1776 1.0000
8.750 1.0798 0.01075 0.00555 -0.0144 0.1730 1.0000
9.000 1.1023 0.01089 0.00571 -0.0132 0.1693 1.0000
9.250 1.1239 0.01110 0.00591 -0.0119 0.1645 1.0000
9.500 1.1449 0.01135 0.00615 -0.0104 0.1589 1.0000
9.750 1.1669 0.01155 0.00634 -0.0092 0.1537 1.0000
10.000 1.1867 0.01187 0.00662 -0.0076 0.1467 1.0000
10.250 1.2083 0.01208 0.00685 -0.0063 0.1421 1.0000
10.500 1.2284 0.01238 0.00713 -0.0048 0.1365 1.0000
10.750 1.2483 0.01269 0.00744 -0.0032 0.1311 1.0000
11.000 1.2684 0.01298 0.00773 -0.0017 0.1262 1.0000
11.250 1.2865 0.01338 0.00810 0.0001 0.1200 1.0000
11.500 1.3062 0.01367 0.00841 0.0016 0.1156 1.0000
11.750 1.3235 0.01409 0.00880 0.0035 0.1099 1.0000
12.000 1.3414 0.01445 0.00917 0.0053 0.1051 1.0000
12.250 1.3574 0.01490 0.00960 0.0074 0.0992 1.0000
12.500 1.3735 0.01533 0.01004 0.0094 0.0943 1.0000
12.750 1.3879 0.01582 0.01051 0.0117 0.0887 1.0000
13.000 1.4017 0.01631 0.01100 0.0141 0.0841 1.0000
13.250 1.4137 0.01685 0.01154 0.0167 0.0788 1.0000
13.500 1.4247 0.01741 0.01210 0.0194 0.0749 1.0000
13.750 1.4305 0.01793 0.01262 0.0231 0.0705 1.0000
14.000 1.4327 0.01856 0.01325 0.0272 0.0665 1.0000
14.250 1.4391 0.01914 0.01387 0.0304 0.0628 1.0000
14.500 1.4433 0.01992 0.01465 0.0337 0.0595 1.0000
14.750 1.4492 0.02070 0.01546 0.0364 0.0565 1.0000
15.000 1.4531 0.02166 0.01645 0.0391 0.0534 1.0000
15.250 1.4547 0.02287 0.01769 0.0415 0.0503 1.0000
15.500 1.4569 0.02420 0.01907 0.0434 0.0475 1.0000
15.750 1.4546 0.02605 0.02095 0.0449 0.0450 1.0000
16.000 1.4541 0.02805 0.02303 0.0457 0.0430 1.0000
16.250 1.4502 0.03067 0.02572 0.0458 0.0410 1.0000
16.500 1.4407 0.03429 0.02943 0.0449 0.0392 1.0000
16.750 1.4295 0.03853 0.03378 0.0433 0.0378 1.0000
17.000 1.4155 0.04337 0.03875 0.0412 0.0368 1.0000
17.250 1.3928 0.04940 0.04491 0.0385 0.0359 1.0000
17.500 1.3645 0.05612 0.05178 0.0356 0.0355 1.0000
17.750 1.3317 0.06336 0.05915 0.0326 0.0351 1.0000
18.000 1.2977 0.07076 0.06668 0.0295 0.0347 1.0000
18.250 1.2672 0.07795 0.07399 0.0264 0.0345 1.0000
18.500 1.2406 0.08482 0.08096 0.0233 0.0341 1.0000
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