EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.64 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e593-il-1000000-n5.txt Download as CSV file: xf-e593-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 593 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4273 0.12708 0.12366 0.0190 0.4624 0.0049
-9.000 -0.6683 0.02771 0.02333 -0.0379 0.4650 0.0036
-8.750 -0.6501 0.02468 0.01997 -0.0382 0.4637 0.0036
-8.500 -0.6290 0.02260 0.01762 -0.0382 0.4623 0.0036
-8.250 -0.6062 0.02098 0.01577 -0.0380 0.4605 0.0036
-8.000 -0.5825 0.01958 0.01415 -0.0377 0.4586 0.0037
-7.750 -0.5578 0.01847 0.01285 -0.0374 0.4566 0.0037
-7.500 -0.5326 0.01746 0.01166 -0.0371 0.4545 0.0037
-7.250 -0.5069 0.01658 0.01062 -0.0368 0.4526 0.0037
-7.000 -0.4807 0.01581 0.00968 -0.0365 0.4507 0.0037
-6.750 -0.4542 0.01512 0.00887 -0.0362 0.4492 0.0037
-6.500 -0.4274 0.01449 0.00812 -0.0360 0.4481 0.0037
-6.250 -0.4004 0.01392 0.00745 -0.0357 0.4468 0.0038
-6.000 -0.3731 0.01340 0.00684 -0.0354 0.4453 0.0038
-5.750 -0.3457 0.01292 0.00627 -0.0352 0.4437 0.0038
-5.500 -0.3183 0.01236 0.00560 -0.0349 0.4420 0.0039
-5.250 -0.2907 0.01191 0.00506 -0.0347 0.4401 0.0040
-5.000 -0.2629 0.01153 0.00460 -0.0344 0.4384 0.0042
-4.750 -0.2350 0.01121 0.00421 -0.0342 0.4368 0.0044
-4.500 -0.2069 0.01094 0.00388 -0.0340 0.4352 0.0046
-4.250 -0.1788 0.01070 0.00358 -0.0339 0.4338 0.0049
-4.000 -0.1505 0.01047 0.00332 -0.0337 0.4329 0.0053
-3.750 -0.1222 0.01023 0.00305 -0.0335 0.4317 0.0061
-3.500 -0.0939 0.01001 0.00281 -0.0333 0.4304 0.0075
-3.250 -0.0657 0.00979 0.00259 -0.0332 0.4289 0.0106
-3.000 -0.0374 0.00959 0.00240 -0.0330 0.4273 0.0163
-2.750 -0.0091 0.00942 0.00224 -0.0329 0.4257 0.0216
-2.500 0.0193 0.00928 0.00210 -0.0328 0.4243 0.0276
-2.250 0.0477 0.00915 0.00198 -0.0327 0.4229 0.0346
-2.000 0.0760 0.00899 0.00188 -0.0326 0.4215 0.0471
-1.750 0.1044 0.00889 0.00180 -0.0325 0.4200 0.0576
-1.500 0.1329 0.00880 0.00173 -0.0324 0.4187 0.0677
-1.250 0.1615 0.00871 0.00167 -0.0324 0.4177 0.0764
-1.000 0.1901 0.00864 0.00161 -0.0323 0.4165 0.0840
-0.750 0.2188 0.00856 0.00156 -0.0323 0.4151 0.0938
-0.500 0.2474 0.00849 0.00152 -0.0322 0.4137 0.1040
-0.250 0.2760 0.00845 0.00149 -0.0322 0.4123 0.1135
0.000 0.3047 0.00840 0.00146 -0.0321 0.4110 0.1237
0.250 0.3333 0.00835 0.00144 -0.0321 0.4096 0.1369
0.500 0.3618 0.00831 0.00142 -0.0321 0.4083 0.1527
0.750 0.3904 0.00827 0.00142 -0.0321 0.4068 0.1707
1.000 0.4188 0.00822 0.00143 -0.0320 0.4051 0.1975
1.250 0.4473 0.00816 0.00145 -0.0320 0.4037 0.2277
1.750 0.5039 0.00794 0.00151 -0.0321 0.4015 0.3310
2.000 0.5236 0.00664 0.00160 -0.0307 0.4004 0.8193
2.500 0.6049 0.00640 0.00167 -0.0357 0.3970 1.0000
2.750 0.6323 0.00646 0.00170 -0.0354 0.3954 1.0000
3.000 0.6598 0.00653 0.00175 -0.0352 0.3938 1.0000
3.250 0.6873 0.00660 0.00179 -0.0350 0.3921 1.0000
3.500 0.7148 0.00669 0.00185 -0.0348 0.3901 1.0000
3.750 0.7425 0.00675 0.00191 -0.0347 0.3886 1.0000
4.000 0.7703 0.00680 0.00198 -0.0345 0.3865 1.0000
4.250 0.7980 0.00686 0.00204 -0.0344 0.3838 1.0000
4.500 0.8258 0.00693 0.00210 -0.0343 0.3809 1.0000
4.750 0.8535 0.00701 0.00216 -0.0342 0.3780 1.0000
5.000 0.8812 0.00711 0.00225 -0.0342 0.3752 1.0000
5.250 0.9091 0.00717 0.00234 -0.0341 0.3727 1.0000
5.500 0.9370 0.00725 0.00242 -0.0341 0.3693 1.0000
5.750 0.9647 0.00734 0.00251 -0.0340 0.3652 1.0000
6.000 0.9924 0.00745 0.00261 -0.0340 0.3611 1.0000
6.250 1.0202 0.00753 0.00272 -0.0340 0.3574 1.0000
6.500 1.0479 0.00764 0.00284 -0.0340 0.3528 1.0000
6.750 1.0754 0.00778 0.00297 -0.0339 0.3476 1.0000
7.000 1.1031 0.00788 0.00311 -0.0339 0.3420 1.0000
7.250 1.1302 0.00806 0.00326 -0.0339 0.3333 1.0000
7.500 1.1575 0.00823 0.00343 -0.0339 0.3231 1.0000
7.750 1.1844 0.00845 0.00364 -0.0339 0.3116 1.0000
8.000 1.2107 0.00876 0.00389 -0.0339 0.2958 1.0000
8.250 1.2361 0.00921 0.00425 -0.0338 0.2742 1.0000
8.500 1.2607 0.00976 0.00470 -0.0336 0.2506 1.0000
8.750 1.2847 0.01037 0.00521 -0.0335 0.2262 1.0000
9.000 1.3082 0.01102 0.00577 -0.0333 0.2035 1.0000
9.250 1.3316 0.01166 0.00632 -0.0331 0.1832 1.0000
9.500 1.3545 0.01231 0.00690 -0.0328 0.1653 1.0000
9.750 1.3770 0.01299 0.00750 -0.0326 0.1473 1.0000
10.000 1.3988 0.01369 0.00814 -0.0323 0.1311 1.0000
10.250 1.4201 0.01442 0.00882 -0.0319 0.1167 1.0000
10.500 1.4406 0.01517 0.00952 -0.0315 0.1039 1.0000
10.750 1.4589 0.01609 0.01037 -0.0310 0.0892 1.0000
11.250 1.4937 0.01787 0.01210 -0.0297 0.0691 1.0000
11.500 1.5092 0.01881 0.01305 -0.0290 0.0617 1.0000
11.750 1.5211 0.01994 0.01418 -0.0280 0.0551 1.0000
12.000 1.5296 0.02122 0.01549 -0.0269 0.0503 1.0000
12.250 1.5161 0.02422 0.01859 -0.0259 0.0464 1.0000
12.500 1.5142 0.02745 0.02191 -0.0269 0.0447 1.0000
12.750 1.5057 0.03114 0.02565 -0.0275 0.0414 1.0000
13.000 1.4994 0.03440 0.02896 -0.0276 0.0395 1.0000
13.250 1.4917 0.03772 0.03234 -0.0277 0.0366 1.0000
13.500 1.4800 0.04141 0.03606 -0.0277 0.0332 1.0000
13.750 1.4732 0.04465 0.03934 -0.0279 0.0306 1.0000
14.000 1.4618 0.04838 0.04308 -0.0281 0.0267 1.0000
14.250 1.4597 0.05116 0.04591 -0.0282 0.0258 1.0000
14.500 1.4532 0.05457 0.04935 -0.0286 0.0231 1.0000
14.750 1.4485 0.05791 0.05271 -0.0291 0.0199 1.0000
15.000 1.4500 0.06066 0.05553 -0.0295 0.0197 1.0000
15.250 1.4496 0.06365 0.05856 -0.0300 0.0185 1.0000
15.500 1.4473 0.06698 0.06193 -0.0307 0.0166 1.0000
15.750 1.4461 0.07019 0.06517 -0.0314 0.0148 1.0000
16.000 1.4459 0.07336 0.06840 -0.0322 0.0143 1.0000
16.250 1.4431 0.07689 0.07195 -0.0330 0.0118 1.0000
16.500 1.4436 0.08010 0.07523 -0.0339 0.0116 1.0000
16.750 1.4434 0.08340 0.07857 -0.0348 0.0105 1.0000
17.000 1.4425 0.08686 0.08209 -0.0358 0.0096 1.0000
17.250 1.4409 0.09049 0.08577 -0.0370 0.0089 1.0000
17.500 1.4405 0.09399 0.08932 -0.0381 0.0080 1.0000
17.750 1.4386 0.09776 0.09316 -0.0394 0.0074 1.0000
18.000 1.4377 0.10144 0.09689 -0.0407 0.0070 1.0000
18.250 1.4359 0.10534 0.10087 -0.0422 0.0067 1.0000
18.500 1.4352 0.10905 0.10464 -0.0437 0.0061 1.0000
18.750 1.4330 0.11311 0.10878 -0.0453 0.0059 1.0000
19.000 1.4313 0.11708 0.11281 -0.0470 0.0054 1.0000
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