EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.74 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e473-il-1000000-n5.txt Download as CSV file: xf-e473-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.2013 0.08685 0.08275 -0.0220 1.0000 0.0235
-18.000 -1.2227 0.08062 0.07642 -0.0247 1.0000 0.0238
-17.750 -1.2473 0.07413 0.06983 -0.0275 1.0000 0.0241
-17.500 -1.2763 0.06726 0.06284 -0.0304 1.0000 0.0243
-17.250 -1.3058 0.06043 0.05587 -0.0332 1.0000 0.0244
-16.750 -1.3597 0.04727 0.04242 -0.0388 1.0000 0.0248
-16.500 -1.3789 0.04164 0.03667 -0.0413 1.0000 0.0253
-16.250 -1.3927 0.03684 0.03175 -0.0434 1.0000 0.0261
-16.000 -1.4007 0.03307 0.02787 -0.0447 1.0000 0.0271
-15.750 -1.4045 0.03015 0.02486 -0.0452 1.0000 0.0284
-15.500 -1.4091 0.02756 0.02220 -0.0449 1.0000 0.0300
-15.250 -1.4099 0.02564 0.02022 -0.0439 1.0000 0.0317
-14.750 -1.4069 0.02281 0.01729 -0.0402 1.0000 0.0354
-14.500 -1.4021 0.02182 0.01626 -0.0379 1.0000 0.0372
-14.250 -1.3987 0.02087 0.01527 -0.0351 1.0000 0.0398
-14.000 -1.3938 0.02008 0.01446 -0.0321 1.0000 0.0423
-13.750 -1.3875 0.01944 0.01379 -0.0290 1.0000 0.0447
-13.500 -1.3854 0.01876 0.01310 -0.0251 1.0000 0.0480
-13.250 -1.3807 0.01826 0.01259 -0.0212 1.0000 0.0508
-13.000 -1.3741 0.01765 0.01197 -0.0178 1.0000 0.0545
-12.750 -1.3627 0.01710 0.01141 -0.0151 1.0000 0.0589
-12.500 -1.3508 0.01653 0.01086 -0.0125 1.0000 0.0631
-12.250 -1.3362 0.01607 0.01039 -0.0102 1.0000 0.0672
-12.000 -1.3222 0.01554 0.00988 -0.0079 1.0000 0.0722
-11.750 -1.3057 0.01513 0.00946 -0.0059 1.0000 0.0766
-11.500 -1.2899 0.01465 0.00901 -0.0038 1.0000 0.0817
-11.000 -1.2546 0.01386 0.00823 -0.0001 1.0000 0.0912
-10.750 -1.2356 0.01352 0.00789 0.0016 1.0000 0.0960
-10.500 -1.2174 0.01311 0.00751 0.0034 1.0000 0.1020
-10.250 -1.1976 0.01280 0.00720 0.0049 1.0000 0.1070
-10.000 -1.1787 0.01242 0.00686 0.0066 1.0000 0.1138
-9.750 -1.1565 0.01206 0.00654 0.0077 0.9997 0.1226
-9.500 -1.1150 0.01170 0.00623 0.0047 0.9971 0.1317
-9.250 -1.0706 0.01137 0.00593 0.0012 0.9939 0.1385
-9.000 -1.0301 0.01108 0.00565 -0.0015 0.9899 0.1445
-8.750 -0.9938 0.01079 0.00537 -0.0032 0.9855 0.1500
-8.500 -0.9581 0.01052 0.00513 -0.0048 0.9824 0.1562
-8.250 -0.9289 0.01031 0.00492 -0.0050 0.9783 0.1605
-8.000 -0.9042 0.01006 0.00471 -0.0042 0.9722 0.1664
-7.750 -0.8790 0.00987 0.00452 -0.0035 0.9639 0.1709
-7.500 -0.8505 0.00968 0.00432 -0.0034 0.9504 0.1748
-7.250 -0.7781 0.00931 0.00397 -0.0128 0.9229 0.1823
-7.000 -0.7328 0.00929 0.00369 -0.0162 0.8409 0.1870
-6.750 -0.7117 0.00939 0.00355 -0.0145 0.7717 0.1899
-6.250 -0.6671 0.00950 0.00330 -0.0119 0.6558 0.1978
-6.000 -0.6425 0.00953 0.00318 -0.0110 0.6112 0.2007
-5.750 -0.6172 0.00956 0.00307 -0.0103 0.5746 0.2031
-5.500 -0.5921 0.00953 0.00296 -0.0096 0.5419 0.2070
-5.250 -0.5665 0.00952 0.00286 -0.0089 0.5117 0.2105
-5.000 -0.5406 0.00952 0.00277 -0.0083 0.4823 0.2139
-4.750 -0.5144 0.00954 0.00268 -0.0078 0.4547 0.2167
-4.500 -0.4879 0.00954 0.00260 -0.0073 0.4322 0.2186
-4.250 -0.4616 0.00951 0.00251 -0.0067 0.4139 0.2222
-4.000 -0.4351 0.00948 0.00244 -0.0063 0.3976 0.2257
-3.750 -0.4084 0.00946 0.00237 -0.0058 0.3832 0.2285
-3.500 -0.3814 0.00946 0.00231 -0.0054 0.3696 0.2310
-3.250 -0.3544 0.00946 0.00225 -0.0050 0.3560 0.2331
-3.000 -0.3274 0.00944 0.00219 -0.0045 0.3453 0.2361
-2.750 -0.3006 0.00942 0.00214 -0.0041 0.3350 0.2395
-2.500 -0.2734 0.00938 0.00210 -0.0037 0.3277 0.2423
-2.250 -0.2462 0.00938 0.00206 -0.0033 0.3197 0.2452
-2.000 -0.2188 0.00937 0.00202 -0.0030 0.3137 0.2480
-1.750 -0.1913 0.00937 0.00199 -0.0026 0.3075 0.2500
-1.250 -0.1370 0.00932 0.00193 -0.0018 0.2958 0.2568
-1.000 -0.1096 0.00931 0.00192 -0.0014 0.2906 0.2605
-0.750 -0.0823 0.00932 0.00190 -0.0011 0.2857 0.2637
-0.500 -0.0547 0.00933 0.00189 -0.0007 0.2820 0.2661
-0.250 -0.0273 0.00931 0.00188 -0.0004 0.2784 0.2697
0.000 0.0000 0.00930 0.00188 0.0000 0.2742 0.2741
0.250 0.0273 0.00931 0.00188 0.0004 0.2697 0.2784
0.500 0.0547 0.00933 0.00189 0.0007 0.2661 0.2819
0.750 0.0823 0.00932 0.00190 0.0011 0.2637 0.2858
1.000 0.1096 0.00931 0.00191 0.0014 0.2603 0.2906
1.250 0.1370 0.00933 0.00193 0.0018 0.2567 0.2957
1.750 0.1913 0.00937 0.00199 0.0026 0.2501 0.3074
2.000 0.2188 0.00937 0.00202 0.0030 0.2480 0.3137
2.250 0.2462 0.00938 0.00206 0.0033 0.2452 0.3198
2.500 0.2734 0.00938 0.00210 0.0037 0.2423 0.3276
3.000 0.3274 0.00943 0.00219 0.0045 0.2362 0.3459
3.250 0.3543 0.00946 0.00225 0.0050 0.2332 0.3567
3.500 0.3815 0.00946 0.00231 0.0054 0.2310 0.3697
3.750 0.4084 0.00946 0.00237 0.0058 0.2286 0.3833
4.000 0.4351 0.00948 0.00244 0.0063 0.2257 0.3978
4.250 0.4617 0.00951 0.00251 0.0067 0.2223 0.4138
4.500 0.4879 0.00954 0.00260 0.0073 0.2186 0.4321
4.750 0.5144 0.00954 0.00268 0.0078 0.2166 0.4554
5.000 0.5406 0.00952 0.00277 0.0083 0.2140 0.4820
5.250 0.5665 0.00952 0.00286 0.0089 0.2107 0.5118
5.500 0.5921 0.00953 0.00296 0.0095 0.2070 0.5420
5.750 0.6172 0.00956 0.00307 0.0103 0.2030 0.5745
6.000 0.6425 0.00953 0.00318 0.0110 0.2007 0.6111
6.250 0.6671 0.00950 0.00330 0.0119 0.1977 0.6553
6.500 0.6903 0.00945 0.00342 0.0130 0.1940 0.7096
6.750 0.7116 0.00938 0.00355 0.0146 0.1899 0.7730
7.000 0.7328 0.00929 0.00369 0.0162 0.1869 0.8409
7.250 0.7786 0.00932 0.00397 0.0127 0.1822 0.9234
7.500 0.8504 0.00968 0.00432 0.0035 0.1747 0.9503
7.750 0.8791 0.00987 0.00452 0.0035 0.1710 0.9638
8.000 0.9043 0.01007 0.00471 0.0042 0.1663 0.9722
8.250 0.9288 0.01031 0.00492 0.0050 0.1609 0.9786
8.500 0.9582 0.01052 0.00513 0.0048 0.1561 0.9824
8.750 0.9936 0.01079 0.00537 0.0032 0.1500 0.9854
9.000 1.0305 0.01108 0.00565 0.0014 0.1445 0.9900
9.250 1.0703 0.01137 0.00593 -0.0011 0.1387 0.9938
9.500 1.1152 0.01170 0.00623 -0.0048 0.1315 0.9972
9.750 1.1565 0.01208 0.00655 -0.0077 0.1221 0.9998
10.000 1.1789 0.01241 0.00685 -0.0067 0.1145 1.0000
10.250 1.1977 0.01279 0.00720 -0.0050 0.1073 1.0000
10.500 1.2173 0.01311 0.00751 -0.0034 0.1018 1.0000
10.750 1.2355 0.01352 0.00789 -0.0016 0.0957 1.0000
11.000 1.2546 0.01385 0.00823 0.0001 0.0913 1.0000
11.250 1.2716 0.01430 0.00864 0.0020 0.0856 1.0000
11.500 1.2898 0.01466 0.00901 0.0038 0.0815 1.0000
11.750 1.3058 0.01512 0.00946 0.0059 0.0767 1.0000
12.000 1.3225 0.01553 0.00987 0.0078 0.0725 1.0000
12.250 1.3363 0.01606 0.01039 0.0102 0.0673 1.0000
12.500 1.3510 0.01653 0.01085 0.0124 0.0632 1.0000
13.000 1.3749 0.01762 0.01195 0.0176 0.0550 1.0000
13.250 1.3809 0.01827 0.01259 0.0212 0.0507 1.0000
13.500 1.3866 0.01873 0.01308 0.0249 0.0485 1.0000
13.750 1.3885 0.01942 0.01377 0.0289 0.0449 1.0000
14.000 1.3946 0.02006 0.01444 0.0320 0.0425 1.0000
14.250 1.3968 0.02097 0.01536 0.0353 0.0389 1.0000
14.500 1.4034 0.02178 0.01622 0.0377 0.0375 1.0000
14.750 1.4077 0.02280 0.01728 0.0401 0.0354 1.0000
15.000 1.4093 0.02411 0.01863 0.0422 0.0335 1.0000
15.250 1.4112 0.02560 0.02018 0.0437 0.0318 1.0000
15.500 1.4100 0.02755 0.02219 0.0448 0.0299 1.0000
15.750 1.4066 0.03004 0.02475 0.0451 0.0284 1.0000
16.000 1.4023 0.03302 0.02781 0.0446 0.0271 1.0000
16.250 1.3949 0.03672 0.03163 0.0433 0.0261 1.0000
16.500 1.3808 0.04157 0.03659 0.0411 0.0252 1.0000
16.750 1.3609 0.04729 0.04244 0.0385 0.0246 1.0000
17.250 1.3089 0.06025 0.05568 0.0330 0.0242 1.0000
17.500 1.2797 0.06705 0.06262 0.0302 0.0242 1.0000
17.750 1.2499 0.07404 0.06974 0.0273 0.0240 1.0000
18.000 1.2254 0.08051 0.07631 0.0245 0.0237 1.0000
18.250 1.2044 0.08671 0.08262 0.0218 0.0235 1.0000
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Polar data table (+)
Polar graphs
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