E64 (8.45%) (e64-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 50,000 Max Cl/Cd: 42.52 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e64-il-50000-n5.txt Download as CSV file: xf-e64-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3901 0.09545 0.08856 -0.0346 1.0000 0.0524
-7.750 -0.3961 0.09240 0.08562 -0.0344 1.0000 0.0500
-7.250 -0.4171 0.08493 0.07840 -0.0381 1.0000 0.0446
-7.000 -0.4173 0.08179 0.07533 -0.0378 1.0000 0.0438
-6.750 -0.4180 0.07834 0.07193 -0.0385 1.0000 0.0430
-6.500 -0.4178 0.07457 0.06821 -0.0399 1.0000 0.0423
-6.250 -0.4158 0.07048 0.06413 -0.0418 1.0000 0.0414
-6.000 -0.4117 0.06600 0.05962 -0.0442 1.0000 0.0405
-5.750 -0.4045 0.06115 0.05466 -0.0470 1.0000 0.0396
-5.500 -0.3933 0.05602 0.04933 -0.0502 1.0000 0.0388
-5.250 -0.3775 0.05095 0.04395 -0.0534 1.0000 0.0382
-5.000 -0.3579 0.04639 0.03901 -0.0562 1.0000 0.0386
-4.750 -0.3350 0.04239 0.03454 -0.0586 1.0000 0.0397
-4.500 -0.3095 0.03867 0.03027 -0.0605 1.0000 0.0409
-4.250 -0.2823 0.03544 0.02641 -0.0620 1.0000 0.0420
-4.000 -0.2545 0.03264 0.02303 -0.0628 1.0000 0.0427
-3.750 -0.2268 0.03034 0.02019 -0.0632 1.0000 0.0437
-3.500 -0.1998 0.02854 0.01792 -0.0630 1.0000 0.0452
-3.250 -0.1747 0.02693 0.01619 -0.0628 1.0000 0.0479
-3.000 -0.1506 0.02591 0.01499 -0.0624 1.0000 0.0543
-2.750 -0.1262 0.02490 0.01381 -0.0620 1.0000 0.0622
-2.500 -0.1000 0.02391 0.01269 -0.0619 1.0000 0.0766
-2.250 -0.0711 0.02273 0.01179 -0.0628 1.0000 0.1378
-2.000 -0.0413 0.02137 0.01136 -0.0643 1.0000 0.3180
-1.750 -0.0137 0.02070 0.01135 -0.0646 0.9976 0.4996
-1.500 0.0127 0.02029 0.01145 -0.0637 0.9910 0.6688
-1.250 0.0346 0.01985 0.01136 -0.0612 0.9828 0.8777
-1.000 0.0763 0.01997 0.01105 -0.0646 0.9734 1.0000
-0.750 0.1125 0.02027 0.01093 -0.0669 0.9649 1.0000
-0.500 0.1505 0.02062 0.01093 -0.0695 0.9572 1.0000
-0.250 0.1875 0.02094 0.01096 -0.0718 0.9488 1.0000
0.000 0.2219 0.02123 0.01100 -0.0736 0.9395 1.0000
0.250 0.2604 0.02155 0.01111 -0.0760 0.9314 1.0000
0.500 0.2945 0.02181 0.01122 -0.0776 0.9214 1.0000
0.750 0.3278 0.02207 0.01135 -0.0790 0.9112 1.0000
1.000 0.3646 0.02231 0.01148 -0.0810 0.9021 1.0000
1.250 0.4000 0.02252 0.01163 -0.0826 0.8921 1.0000
1.500 0.4318 0.02274 0.01180 -0.0835 0.8806 1.0000
1.750 0.4652 0.02291 0.01196 -0.0847 0.8695 1.0000
2.000 0.5017 0.02301 0.01207 -0.0862 0.8592 1.0000
2.250 0.5383 0.02306 0.01216 -0.0877 0.8485 1.0000
2.500 0.5704 0.02314 0.01229 -0.0883 0.8358 1.0000
2.750 0.6032 0.02319 0.01241 -0.0890 0.8228 1.0000
3.000 0.6363 0.02320 0.01251 -0.0896 0.8095 1.0000
3.250 0.6693 0.02316 0.01260 -0.0900 0.7955 1.0000
3.500 0.7023 0.02307 0.01263 -0.0903 0.7806 1.0000
3.750 0.7356 0.02292 0.01262 -0.0906 0.7648 1.0000
4.000 0.7695 0.02273 0.01261 -0.0907 0.7481 1.0000
4.250 0.7974 0.02271 0.01273 -0.0900 0.7275 1.0000
4.500 0.8293 0.02253 0.01270 -0.0897 0.7064 1.0000
4.750 0.8575 0.02248 0.01284 -0.0889 0.6817 1.0000
5.000 0.8863 0.02243 0.01292 -0.0881 0.6546 1.0000
5.250 0.9138 0.02245 0.01305 -0.0871 0.6239 1.0000
5.500 0.9409 0.02253 0.01319 -0.0859 0.5897 1.0000
5.750 0.9641 0.02280 0.01356 -0.0843 0.5507 1.0000
6.000 0.9860 0.02319 0.01394 -0.0826 0.5082 1.0000
6.250 1.0058 0.02374 0.01444 -0.0806 0.4624 1.0000
6.500 1.0234 0.02448 0.01507 -0.0785 0.4148 1.0000
6.750 1.0389 0.02539 0.01589 -0.0763 0.3659 1.0000
7.000 1.0527 0.02648 0.01688 -0.0740 0.3178 1.0000
7.250 1.0649 0.02775 0.01799 -0.0717 0.2704 1.0000
7.500 1.0763 0.02919 0.01927 -0.0695 0.2256 1.0000
7.750 1.0865 0.03081 0.02074 -0.0673 0.1834 1.0000
8.000 1.0944 0.03264 0.02232 -0.0651 0.1396 1.0000
8.250 1.1011 0.03457 0.02398 -0.0630 0.1003 1.0000
8.500 1.1084 0.03671 0.02599 -0.0607 0.0767 1.0000
8.750 1.1169 0.03895 0.02827 -0.0585 0.0634 1.0000
9.000 1.1256 0.04124 0.03059 -0.0564 0.0564 1.0000
9.250 1.1404 0.04341 0.03305 -0.0547 0.0504 1.0000
9.500 1.1503 0.04567 0.03531 -0.0531 0.0461 1.0000
9.750 1.1680 0.04806 0.03809 -0.0518 0.0422 1.0000
10.000 1.1835 0.05070 0.04102 -0.0505 0.0396 1.0000
10.250 1.1967 0.05354 0.04413 -0.0493 0.0380 1.0000
10.500 1.2066 0.05659 0.04743 -0.0479 0.0369 1.0000
10.750 1.2136 0.06000 0.05107 -0.0465 0.0360 1.0000
11.000 1.2154 0.06382 0.05521 -0.0450 0.0355 1.0000
11.250 1.2094 0.06765 0.05944 -0.0432 0.0352 1.0000
11.500 1.1994 0.07176 0.06391 -0.0418 0.0351 1.0000
11.750 1.1860 0.07621 0.06868 -0.0411 0.0350 1.0000
12.000 1.1702 0.08109 0.07385 -0.0412 0.0350 1.0000
12.250 1.1525 0.08649 0.07952 -0.0422 0.0350 1.0000
12.500 1.1338 0.09248 0.08574 -0.0443 0.0351 1.0000
12.750 1.1143 0.09914 0.09259 -0.0475 0.0352 1.0000
13.000 1.0951 0.10646 0.10006 -0.0516 0.0354 1.0000
13.250 1.0738 0.11500 0.10875 -0.0571 0.0357 1.0000
13.500 1.0278 0.13282 0.12677 -0.0704 0.0375 1.0000
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Polar data table (+)
Polar graphs
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