EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 500,000 Max Cl/Cd: 69.19 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e325-il-500000-n5.txt Download as CSV file: xf-e325-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6160 0.08030 0.07810 -0.0135 1.0000 0.0045
-10.250 -0.6455 0.07251 0.07022 -0.0171 1.0000 0.0045
-10.000 -0.7075 0.06159 0.05907 -0.0159 1.0000 0.0041
-9.750 -0.7334 0.05689 0.05422 -0.0124 1.0000 0.0041
-9.500 -0.7543 0.05297 0.05013 -0.0078 1.0000 0.0042
-9.250 -0.7914 0.04470 0.04147 -0.0004 1.0000 0.0041
-9.000 -0.8100 0.03831 0.03466 0.0054 1.0000 0.0042
-8.750 -0.7987 0.03756 0.03383 0.0074 1.0000 0.0043
-8.500 -0.8058 0.03228 0.02805 0.0125 1.0000 0.0044
-8.250 -0.8000 0.02910 0.02450 0.0159 1.0000 0.0045
-8.000 -0.7875 0.02707 0.02220 0.0184 1.0000 0.0046
-7.750 -0.7733 0.02473 0.01953 0.0207 1.0000 0.0047
-7.500 -0.7199 0.02190 0.01619 0.0149 0.8979 0.0049
-7.250 -0.6977 0.02072 0.01456 0.0161 0.8296 0.0051
-7.000 -0.6766 0.01984 0.01338 0.0174 0.7892 0.0052
-6.750 -0.6538 0.01899 0.01226 0.0185 0.7593 0.0055
-6.500 -0.6305 0.01832 0.01134 0.0194 0.7329 0.0057
-6.250 -0.6068 0.01759 0.01040 0.0202 0.7095 0.0058
-6.000 -0.5837 0.01671 0.00937 0.0210 0.6896 0.0061
-5.750 -0.5610 0.01604 0.00858 0.0220 0.6712 0.0062
-5.500 -0.5385 0.01544 0.00788 0.0230 0.6541 0.0063
-5.250 -0.5163 0.01492 0.00724 0.0240 0.6375 0.0064
-5.000 -0.4941 0.01444 0.00667 0.0251 0.6224 0.0066
-4.500 -0.4493 0.01364 0.00571 0.0273 0.5951 0.0070
-4.250 -0.4268 0.01327 0.00524 0.0284 0.5816 0.0075
-4.000 -0.4040 0.01295 0.00483 0.0294 0.5694 0.0081
-3.750 -0.3809 0.01267 0.00448 0.0303 0.5577 0.0084
-3.500 -0.3577 0.01240 0.00414 0.0313 0.5464 0.0098
-3.250 -0.3344 0.01214 0.00384 0.0322 0.5353 0.0124
-3.000 -0.3114 0.01189 0.00357 0.0332 0.5246 0.0194
-2.750 -0.2890 0.01160 0.00333 0.0342 0.5142 0.0382
-2.500 -0.2672 0.01127 0.00313 0.0353 0.5050 0.0741
-2.250 -0.2475 0.01084 0.00292 0.0367 0.4956 0.1394
-2.000 -0.2389 0.00975 0.00258 0.0401 0.4875 0.3313
-1.750 -0.2634 0.00758 0.00208 0.0504 0.4825 0.7133
-1.500 -0.2424 0.00765 0.00238 0.0524 0.4741 0.8049
-1.250 -0.2175 0.00784 0.00251 0.0534 0.4654 0.8275
-1.000 -0.1916 0.00805 0.00268 0.0542 0.4567 0.8430
-0.750 -0.1657 0.00821 0.00274 0.0549 0.4483 0.8515
-0.500 -0.1379 0.00842 0.00291 0.0552 0.4404 0.8601
-0.250 -0.1113 0.00862 0.00303 0.0558 0.4325 0.8673
0.000 -0.0826 0.00870 0.00306 0.0557 0.4245 0.8699
0.500 -0.0277 0.00875 0.00296 0.0558 0.4102 0.8726
0.750 -0.0006 0.00878 0.00290 0.0559 0.4029 0.8740
1.000 0.0266 0.00879 0.00286 0.0559 0.3963 0.8754
1.250 0.0535 0.00881 0.00283 0.0560 0.3899 0.8769
1.500 0.0804 0.00884 0.00279 0.0561 0.3838 0.8782
1.750 0.1074 0.00886 0.00276 0.0562 0.3771 0.8793
2.000 0.1344 0.00890 0.00274 0.0562 0.3711 0.8804
2.250 0.1624 0.00893 0.00276 0.0561 0.3658 0.8813
2.500 0.1902 0.00899 0.00278 0.0561 0.3596 0.8822
2.750 0.2178 0.00905 0.00281 0.0560 0.3540 0.8831
3.000 0.2456 0.00910 0.00285 0.0559 0.3487 0.8840
3.250 0.2731 0.00917 0.00289 0.0558 0.3429 0.8849
3.500 0.3005 0.00924 0.00295 0.0558 0.3377 0.8859
3.750 0.3280 0.00930 0.00300 0.0557 0.3323 0.8869
4.000 0.3551 0.00938 0.00308 0.0557 0.3269 0.8881
4.250 0.3822 0.00946 0.00315 0.0557 0.3217 0.8894
4.500 0.4094 0.00954 0.00323 0.0557 0.3161 0.8907
4.750 0.4360 0.00964 0.00331 0.0558 0.3104 0.8920
5.000 0.4631 0.00972 0.00341 0.0557 0.3046 0.8931
5.250 0.4898 0.00981 0.00350 0.0557 0.2985 0.8943
5.500 0.5163 0.00993 0.00361 0.0558 0.2928 0.8955
5.750 0.5434 0.01001 0.00373 0.0557 0.2867 0.8965
6.000 0.5700 0.01014 0.00386 0.0558 0.2803 0.8975
6.250 0.5969 0.01026 0.00401 0.0557 0.2742 0.8985
6.500 0.6233 0.01039 0.00417 0.0558 0.2672 0.8997
6.750 0.6496 0.01054 0.00434 0.0559 0.2606 0.9009
7.000 0.6755 0.01070 0.00451 0.0560 0.2527 0.9024
7.250 0.7013 0.01086 0.00471 0.0561 0.2449 0.9040
7.500 0.7264 0.01107 0.00491 0.0563 0.2354 0.9056
7.750 0.7518 0.01126 0.00513 0.0565 0.2257 0.9072
8.000 0.7766 0.01148 0.00536 0.0567 0.2168 0.9088
8.250 0.8008 0.01174 0.00561 0.0570 0.2065 0.9104
8.500 0.8251 0.01199 0.00588 0.0573 0.1953 0.9120
8.750 0.8489 0.01227 0.00619 0.0576 0.1838 0.9135
9.000 0.8717 0.01261 0.00653 0.0581 0.1705 0.9153
9.250 0.8934 0.01301 0.00691 0.0587 0.1559 0.9173
9.500 0.9138 0.01348 0.00736 0.0595 0.1400 0.9196
9.750 0.9334 0.01398 0.00782 0.0604 0.1255 0.9222
10.000 0.9519 0.01451 0.00833 0.0614 0.1117 0.9252
10.250 0.9690 0.01510 0.00889 0.0626 0.0973 0.9283
10.500 0.9854 0.01571 0.00950 0.0639 0.0841 0.9315
10.750 1.0006 0.01634 0.01013 0.0653 0.0732 0.9353
11.000 1.0143 0.01698 0.01078 0.0669 0.0643 0.9399
11.250 1.0281 0.01761 0.01144 0.0685 0.0571 0.9446
11.500 1.0394 0.01829 0.01217 0.0703 0.0509 0.9507
11.750 1.0494 0.01914 0.01306 0.0720 0.0451 0.9585
12.000 1.0665 0.02010 0.01409 0.0719 0.0395 0.9651
12.250 1.0833 0.02128 0.01533 0.0712 0.0347 0.9725
12.500 1.1012 0.02281 0.01691 0.0694 0.0300 0.9793
12.750 1.1175 0.02465 0.01883 0.0671 0.0258 0.9862
13.000 1.1324 0.02688 0.02113 0.0642 0.0217 0.9931
13.250 1.1388 0.02917 0.02350 0.0630 0.0204 1.0000
13.500 1.1320 0.03171 0.02607 0.0635 0.0175 1.0000
13.750 1.1296 0.03416 0.02863 0.0636 0.0175 1.0000
14.000 1.1249 0.03703 0.03157 0.0634 0.0165 1.0000
14.250 1.1193 0.04009 0.03470 0.0630 0.0147 1.0000
14.500 1.1139 0.04326 0.03797 0.0624 0.0145 1.0000
14.750 1.1047 0.04689 0.04165 0.0615 0.0129 1.0000
15.000 1.0980 0.05036 0.04522 0.0607 0.0132 1.0000
15.250 1.0888 0.05412 0.04902 0.0597 0.0111 1.0000
15.500 1.0795 0.05803 0.05301 0.0585 0.0104 1.0000
15.750 1.0730 0.06175 0.05682 0.0573 0.0102 1.0000
16.000 1.0652 0.06577 0.06095 0.0559 0.0101 1.0000
16.250 1.0582 0.06977 0.06504 0.0544 0.0099 1.0000
16.500 1.0501 0.07404 0.06941 0.0528 0.0102 1.0000
16.750 1.0435 0.07815 0.07360 0.0512 0.0094 1.0000
17.000 1.0343 0.08270 0.07820 0.0494 0.0084 1.0000
17.250 1.0265 0.08716 0.08275 0.0475 0.0084 1.0000
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Polar data table (+)
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