EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 500,000 Max Cl/Cd: 75.36 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e326-il-500000-n5.txt Download as CSV file: xf-e326-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4309 0.08243 0.08038 -0.0163 1.0000 0.0072
-10.000 -0.4408 0.07640 0.07437 -0.0192 1.0000 0.0071
-9.750 -0.4596 0.06821 0.06618 -0.0250 1.0000 0.0070
-9.500 -0.4867 0.06089 0.05879 -0.0288 1.0000 0.0070
-9.250 -0.5102 0.05575 0.05357 -0.0294 1.0000 0.0069
-9.000 -0.5325 0.05152 0.04926 -0.0282 1.0000 0.0069
-8.750 -0.5533 0.04791 0.04557 -0.0254 1.0000 0.0068
-8.500 -0.5613 0.04296 0.04043 -0.0248 0.9213 0.0066
-8.000 -0.6518 0.03845 0.03492 -0.0097 0.9360 0.0051
-7.750 -0.6345 0.03322 0.02905 -0.0098 0.8542 0.0050
-7.500 -0.6331 0.02919 0.02442 -0.0055 0.8110 0.0049
-7.250 -0.6225 0.02662 0.02139 -0.0025 0.7788 0.0048
-7.000 -0.6087 0.02374 0.01799 0.0001 0.7539 0.0048
-6.750 -0.5898 0.02159 0.01540 0.0019 0.7312 0.0047
-6.500 -0.5679 0.02000 0.01346 0.0031 0.7112 0.0047
-6.250 -0.5444 0.01876 0.01193 0.0040 0.6923 0.0047
-6.000 -0.5203 0.01771 0.01066 0.0048 0.6749 0.0047
-5.750 -0.4961 0.01676 0.00951 0.0056 0.6581 0.0048
-5.500 -0.4724 0.01605 0.00864 0.0064 0.6426 0.0048
-5.250 -0.4491 0.01535 0.00779 0.0074 0.6285 0.0049
-5.000 -0.4261 0.01480 0.00712 0.0083 0.6144 0.0050
-4.750 -0.4033 0.01431 0.00652 0.0093 0.6006 0.0051
-4.500 -0.3804 0.01385 0.00596 0.0103 0.5881 0.0053
-4.250 -0.3582 0.01336 0.00539 0.0114 0.5766 0.0055
-4.000 -0.3352 0.01301 0.00497 0.0124 0.5650 0.0058
-3.500 -0.2880 0.01246 0.00427 0.0141 0.5423 0.0069
-3.250 -0.2643 0.01220 0.00394 0.0150 0.5326 0.0080
-2.750 -0.2164 0.01176 0.00341 0.0165 0.5120 0.0131
-2.500 -0.1927 0.01153 0.00318 0.0174 0.5029 0.0218
-2.250 -0.1701 0.01122 0.00298 0.0183 0.4941 0.0512
-2.000 -0.1486 0.01084 0.00281 0.0194 0.4860 0.1070
-1.750 -0.1298 0.01031 0.00260 0.0210 0.4773 0.2062
-1.500 -0.1370 0.00841 0.00210 0.0272 0.4717 0.5676
-1.250 -0.1322 0.00773 0.00233 0.0325 0.4650 0.7996
-1.000 -0.1073 0.00790 0.00246 0.0335 0.4577 0.8255
-0.750 -0.0815 0.00806 0.00255 0.0342 0.4496 0.8392
-0.500 -0.0556 0.00825 0.00266 0.0349 0.4423 0.8506
-0.250 -0.0281 0.00846 0.00285 0.0354 0.4347 0.8592
0.000 -0.0033 0.00861 0.00291 0.0362 0.4283 0.8675
0.250 0.0251 0.00868 0.00293 0.0362 0.4215 0.8699
0.500 0.0528 0.00873 0.00289 0.0362 0.4144 0.8710
0.750 0.0807 0.00875 0.00286 0.0362 0.4082 0.8722
1.000 0.1083 0.00879 0.00284 0.0362 0.4020 0.8734
1.250 0.1359 0.00883 0.00282 0.0362 0.3960 0.8745
1.500 0.1635 0.00886 0.00280 0.0362 0.3898 0.8756
1.750 0.1908 0.00892 0.00280 0.0362 0.3842 0.8770
2.000 0.2183 0.00896 0.00280 0.0362 0.3790 0.8783
2.250 0.2457 0.00900 0.00280 0.0361 0.3731 0.8795
2.500 0.2728 0.00907 0.00281 0.0362 0.3678 0.8807
2.750 0.3004 0.00910 0.00283 0.0361 0.3630 0.8818
3.000 0.3277 0.00916 0.00286 0.0361 0.3574 0.8829
3.250 0.3550 0.00924 0.00291 0.0361 0.3523 0.8839
3.500 0.3827 0.00930 0.00297 0.0360 0.3476 0.8850
3.750 0.4101 0.00937 0.00304 0.0360 0.3423 0.8859
4.000 0.4371 0.00947 0.00311 0.0360 0.3373 0.8869
4.250 0.4647 0.00954 0.00319 0.0359 0.3326 0.8879
4.500 0.4918 0.00962 0.00327 0.0359 0.3273 0.8890
4.750 0.5186 0.00974 0.00338 0.0359 0.3222 0.8902
5.000 0.5459 0.00981 0.00348 0.0359 0.3173 0.8914
5.250 0.5727 0.00992 0.00358 0.0359 0.3116 0.8927
5.500 0.5993 0.01004 0.00370 0.0359 0.3064 0.8940
5.750 0.6262 0.01014 0.00383 0.0359 0.3007 0.8956
6.000 0.6524 0.01028 0.00395 0.0360 0.2946 0.8971
6.250 0.6791 0.01039 0.00410 0.0360 0.2887 0.8984
6.500 0.7054 0.01052 0.00424 0.0360 0.2821 0.8995
6.750 0.7314 0.01066 0.00441 0.0361 0.2760 0.9007
7.000 0.7575 0.01081 0.00459 0.0363 0.2689 0.9020
7.250 0.7829 0.01098 0.00478 0.0364 0.2621 0.9034
7.500 0.8085 0.01115 0.00498 0.0366 0.2542 0.9049
7.750 0.8336 0.01135 0.00520 0.0368 0.2462 0.9065
8.000 0.8581 0.01157 0.00543 0.0371 0.2366 0.9082
8.250 0.8828 0.01178 0.00567 0.0374 0.2275 0.9101
8.500 0.9068 0.01204 0.00593 0.0377 0.2180 0.9121
8.750 0.9299 0.01234 0.00623 0.0382 0.2069 0.9141
9.000 0.9524 0.01265 0.00655 0.0388 0.1946 0.9161
9.250 0.9743 0.01299 0.00690 0.0394 0.1819 0.9183
9.500 0.9952 0.01338 0.00730 0.0402 0.1687 0.9207
9.750 1.0147 0.01385 0.00773 0.0412 0.1541 0.9235
10.000 1.0332 0.01435 0.00821 0.0422 0.1399 0.9266
10.500 1.0661 0.01548 0.00930 0.0449 0.1123 0.9334
10.750 1.0798 0.01612 0.00993 0.0467 0.0987 0.9380
11.250 1.1052 0.01732 0.01118 0.0504 0.0795 0.9494
11.750 1.1323 0.01894 0.01285 0.0527 0.0633 0.9667
12.000 1.1503 0.02002 0.01396 0.0523 0.0552 0.9756
12.250 1.1699 0.02118 0.01518 0.0511 0.0485 0.9850
12.500 1.1887 0.02258 0.01663 0.0495 0.0432 0.9990
12.750 1.1894 0.02403 0.01811 0.0511 0.0393 1.0000
13.000 1.1889 0.02577 0.01991 0.0522 0.0361 1.0000
13.250 1.1900 0.02766 0.02186 0.0528 0.0332 1.0000
13.500 1.1884 0.03001 0.02426 0.0531 0.0306 1.0000
13.750 1.1880 0.03241 0.02675 0.0530 0.0286 1.0000
14.000 1.1859 0.03510 0.02951 0.0528 0.0264 1.0000
14.250 1.1819 0.03807 0.03254 0.0523 0.0248 1.0000
14.500 1.1767 0.04124 0.03580 0.0518 0.0231 1.0000
14.750 1.1720 0.04443 0.03907 0.0511 0.0218 1.0000
15.000 1.1654 0.04788 0.04261 0.0503 0.0206 1.0000
15.250 1.1576 0.05154 0.04632 0.0494 0.0194 1.0000
15.500 1.1484 0.05542 0.05030 0.0483 0.0187 1.0000
15.750 1.1423 0.05909 0.05406 0.0472 0.0180 1.0000
16.000 1.1361 0.06287 0.05793 0.0459 0.0173 1.0000
16.250 1.1283 0.06695 0.06209 0.0445 0.0163 1.0000
16.500 1.1205 0.07116 0.06637 0.0429 0.0157 1.0000
16.750 1.1117 0.07558 0.07087 0.0412 0.0151 1.0000
17.000 1.1040 0.07993 0.07530 0.0395 0.0146 1.0000
17.250 1.0988 0.08400 0.07946 0.0379 0.0139 1.0000
17.500 1.0924 0.08833 0.08388 0.0361 0.0133 1.0000
17.750 1.0855 0.09280 0.08843 0.0341 0.0127 1.0000
18.000 1.0778 0.09747 0.09319 0.0321 0.0123 1.0000
18.250 1.0696 0.10234 0.09813 0.0299 0.0118 1.0000
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Polar data table (+)
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