EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 500,000 Max Cl/Cd: 86.71 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e328-il-500000-n5.txt Download as CSV file: xf-e328-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 328 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2945 0.09697 0.09484 -0.0288 1.0000 0.0098
-10.500 -0.2952 0.09298 0.09086 -0.0299 1.0000 0.0098
-10.000 -0.3942 0.09332 0.09106 -0.0287 1.0000 0.0097
-9.500 -0.4056 0.08366 0.08146 -0.0321 1.0000 0.0072
-9.250 -0.4083 0.07983 0.07766 -0.0345 1.0000 0.0071
-9.000 -0.4194 0.07455 0.07240 -0.0387 1.0000 0.0070
-8.750 -0.4262 0.06888 0.06668 -0.0437 0.9643 0.0068
-8.250 -0.4083 0.05648 0.05351 -0.0567 0.8077 0.0063
-7.750 -0.4487 0.04275 0.03901 -0.0481 0.7600 0.0051
-7.500 -0.4566 0.03697 0.03280 -0.0438 0.7411 0.0051
-7.250 -0.4462 0.03505 0.03065 -0.0418 0.7218 0.0050
-7.000 -0.4626 0.02416 0.01865 -0.0345 0.7115 0.0050
-6.750 -0.4471 0.02136 0.01527 -0.0322 0.6952 0.0051
-6.500 -0.4277 0.01952 0.01305 -0.0307 0.6803 0.0052
-6.250 -0.4061 0.01830 0.01159 -0.0297 0.6656 0.0054
-6.000 -0.3829 0.01775 0.01091 -0.0289 0.6505 0.0057
-5.750 -0.3593 0.01695 0.00992 -0.0281 0.6366 0.0058
-5.500 -0.3352 0.01631 0.00911 -0.0274 0.6238 0.0061
-5.250 -0.3111 0.01562 0.00827 -0.0266 0.6118 0.0062
-5.000 -0.2869 0.01504 0.00756 -0.0259 0.5997 0.0064
-4.750 -0.2629 0.01449 0.00688 -0.0251 0.5881 0.0066
-4.500 -0.2389 0.01406 0.00634 -0.0243 0.5768 0.0070
-4.250 -0.2145 0.01372 0.00589 -0.0236 0.5660 0.0072
-4.000 -0.1911 0.01328 0.00541 -0.0228 0.5565 0.0078
-3.500 -0.1429 0.01267 0.00467 -0.0213 0.5365 0.0087
-3.250 -0.1189 0.01237 0.00429 -0.0205 0.5275 0.0091
-3.000 -0.0946 0.01211 0.00396 -0.0198 0.5184 0.0094
-2.750 -0.0704 0.01182 0.00362 -0.0190 0.5106 0.0103
-2.500 -0.0457 0.01162 0.00336 -0.0184 0.5020 0.0115
-2.250 -0.0209 0.01142 0.00312 -0.0177 0.4942 0.0145
-2.000 0.0039 0.01124 0.00293 -0.0171 0.4858 0.0212
-1.750 0.0287 0.01105 0.00277 -0.0165 0.4790 0.0377
-1.500 0.0526 0.01079 0.00265 -0.0158 0.4718 0.0753
-1.250 0.0753 0.01044 0.00252 -0.0150 0.4651 0.1489
-1.000 0.0684 0.00801 0.00211 -0.0092 0.4603 0.6882
-0.750 0.0890 0.00805 0.00242 -0.0071 0.4535 0.8040
-0.500 0.1152 0.00817 0.00248 -0.0065 0.4475 0.8230
-0.250 0.1411 0.00834 0.00260 -0.0058 0.4413 0.8379
0.000 0.1663 0.00855 0.00277 -0.0048 0.4355 0.8508
0.250 0.1925 0.00868 0.00286 -0.0042 0.4294 0.8590
0.500 0.2184 0.00883 0.00296 -0.0036 0.4235 0.8658
0.750 0.2459 0.00889 0.00294 -0.0035 0.4184 0.8681
1.000 0.2738 0.00892 0.00291 -0.0036 0.4128 0.8694
1.250 0.3013 0.00897 0.00289 -0.0037 0.4072 0.8709
1.500 0.3291 0.00902 0.00288 -0.0037 0.4024 0.8719
1.750 0.3568 0.00906 0.00288 -0.0037 0.3975 0.8728
2.000 0.3843 0.00913 0.00290 -0.0037 0.3923 0.8738
2.250 0.4117 0.00920 0.00293 -0.0037 0.3877 0.8748
2.500 0.4392 0.00926 0.00297 -0.0037 0.3832 0.8761
2.750 0.4666 0.00933 0.00301 -0.0037 0.3784 0.8773
3.000 0.4936 0.00943 0.00307 -0.0037 0.3738 0.8785
3.250 0.5213 0.00949 0.00312 -0.0038 0.3696 0.8796
3.500 0.5487 0.00956 0.00318 -0.0038 0.3650 0.8809
3.750 0.5757 0.00967 0.00325 -0.0038 0.3604 0.8821
4.000 0.6030 0.00975 0.00333 -0.0038 0.3564 0.8834
4.250 0.6305 0.00983 0.00341 -0.0039 0.3521 0.8847
4.500 0.6575 0.00994 0.00350 -0.0039 0.3474 0.8862
4.750 0.6841 0.01007 0.00360 -0.0039 0.3433 0.8876
5.000 0.7111 0.01014 0.00372 -0.0039 0.3390 0.8887
5.250 0.7377 0.01025 0.00383 -0.0038 0.3342 0.8899
5.500 0.7637 0.01038 0.00396 -0.0036 0.3297 0.8911
5.750 0.7903 0.01049 0.00410 -0.0035 0.3253 0.8925
6.000 0.8168 0.01061 0.00424 -0.0035 0.3203 0.8939
6.250 0.8425 0.01076 0.00439 -0.0033 0.3152 0.8954
6.500 0.8687 0.01089 0.00456 -0.0032 0.3102 0.8970
6.750 0.8947 0.01102 0.00472 -0.0031 0.3042 0.8986
7.000 0.9199 0.01121 0.00489 -0.0029 0.2986 0.9004
7.250 0.9461 0.01134 0.00508 -0.0028 0.2928 0.9023
7.500 0.9707 0.01152 0.00527 -0.0025 0.2863 0.9040
7.750 0.9953 0.01169 0.00548 -0.0021 0.2798 0.9058
8.000 1.0193 0.01188 0.00570 -0.0017 0.2723 0.9077
8.250 1.0433 0.01209 0.00593 -0.0012 0.2647 0.9098
8.500 1.0663 0.01234 0.00619 -0.0007 0.2564 0.9121
8.750 1.0899 0.01257 0.00646 -0.0002 0.2475 0.9145
9.000 1.1124 0.01285 0.00675 0.0003 0.2386 0.9170
9.250 1.1333 0.01317 0.00707 0.0012 0.2279 0.9196
9.500 1.1541 0.01347 0.00740 0.0021 0.2176 0.9224
9.750 1.1735 0.01382 0.00777 0.0032 0.2068 0.9258
10.000 1.1917 0.01423 0.00818 0.0045 0.1951 0.9298
10.250 1.2080 0.01470 0.00864 0.0060 0.1816 0.9344
10.500 1.2220 0.01519 0.00913 0.0080 0.1687 0.9403
11.000 1.2454 0.01631 0.01025 0.0125 0.1443 0.9576
11.250 1.2619 0.01706 0.01099 0.0133 0.1310 0.9694
11.500 1.2826 0.01792 0.01185 0.0129 0.1180 0.9868
11.750 1.2920 0.01882 0.01273 0.0147 0.1075 1.0000
12.000 1.3001 0.01971 0.01364 0.0165 0.0988 1.0000
12.250 1.3063 0.02077 0.01470 0.0184 0.0910 1.0000
12.500 1.3096 0.02208 0.01602 0.0202 0.0834 1.0000
12.750 1.3134 0.02349 0.01746 0.0216 0.0764 1.0000
13.000 1.3154 0.02517 0.01917 0.0228 0.0705 1.0000
13.250 1.3167 0.02706 0.02109 0.0237 0.0649 1.0000
13.500 1.3175 0.02915 0.02324 0.0242 0.0604 1.0000
13.750 1.3175 0.03145 0.02560 0.0246 0.0561 1.0000
14.000 1.3149 0.03412 0.02831 0.0247 0.0521 1.0000
14.250 1.3138 0.03673 0.03100 0.0247 0.0488 1.0000
14.500 1.3079 0.03992 0.03424 0.0244 0.0451 1.0000
14.750 1.3048 0.04291 0.03731 0.0241 0.0427 1.0000
15.000 1.3002 0.04612 0.04059 0.0236 0.0403 1.0000
15.250 1.2918 0.04980 0.04433 0.0230 0.0375 1.0000
15.500 1.2857 0.05334 0.04795 0.0222 0.0358 1.0000
15.750 1.2801 0.05692 0.05161 0.0214 0.0336 1.0000
16.000 1.2718 0.06093 0.05568 0.0203 0.0314 1.0000
16.250 1.2647 0.06491 0.05974 0.0191 0.0302 1.0000
16.500 1.2595 0.06872 0.06365 0.0179 0.0289 1.0000
16.750 1.2527 0.07286 0.06785 0.0165 0.0269 1.0000
17.000 1.2461 0.07704 0.07212 0.0151 0.0258 1.0000
17.250 1.2377 0.08156 0.07670 0.0134 0.0244 1.0000
17.500 1.2323 0.08572 0.08094 0.0118 0.0225 1.0000
17.750 1.2276 0.08987 0.08518 0.0101 0.0221 1.0000
18.000 1.2207 0.09439 0.08976 0.0082 0.0206 1.0000
18.250 1.2125 0.09919 0.09463 0.0062 0.0195 1.0000
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Polar data table (+)
Polar graphs
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