EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.1 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e328-il-1000000.txt Download as CSV file: xf-e328-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3964 0.08359 0.08206 -0.0309 1.0000 0.0082
-9.000 -0.4043 0.07839 0.07688 -0.0347 1.0000 0.0082
-8.750 -0.4215 0.07269 0.07119 -0.0389 1.0000 0.0083
-8.500 -0.4409 0.06876 0.06723 -0.0390 1.0000 0.0082
-8.250 -0.4459 0.06392 0.06232 -0.0415 0.9835 0.0082
-8.000 -0.4083 0.05569 0.05383 -0.0539 0.9307 0.0085
-7.750 -0.3951 0.05108 0.04871 -0.0564 0.8387 0.0087
-7.500 -0.3995 0.04747 0.04479 -0.0531 0.7975 0.0091
-7.250 -0.3963 0.04488 0.04197 -0.0507 0.7685 0.0090
-7.000 -0.3916 0.03854 0.03521 -0.0464 0.7493 0.0097
-6.750 -0.3876 0.03488 0.03119 -0.0430 0.7301 0.0098
-6.500 -0.3907 0.03052 0.02652 -0.0395 0.7135 0.0101
-6.250 -0.3765 0.02899 0.02480 -0.0377 0.6954 0.0102
-6.000 -0.3603 0.02775 0.02341 -0.0363 0.6792 0.0104
-5.750 -0.3573 0.01906 0.01360 -0.0297 0.6700 0.0074
-5.500 -0.3368 0.01676 0.01105 -0.0283 0.6558 0.0068
-5.250 -0.3135 0.01510 0.00909 -0.0272 0.6424 0.0066
-5.000 -0.2890 0.01396 0.00774 -0.0263 0.6292 0.0066
-4.750 -0.2644 0.01317 0.00678 -0.0255 0.6166 0.0069
-4.500 -0.2393 0.01270 0.00616 -0.0248 0.6039 0.0074
-4.250 -0.2169 0.01192 0.00528 -0.0237 0.5918 0.0077
-4.000 -0.1926 0.01156 0.00487 -0.0230 0.5802 0.0081
-3.750 -0.1684 0.01120 0.00445 -0.0223 0.5696 0.0084
-3.500 -0.1439 0.01092 0.00411 -0.0215 0.5590 0.0088
-3.250 -0.1195 0.01063 0.00375 -0.0208 0.5482 0.0090
-3.000 -0.0946 0.01039 0.00345 -0.0201 0.5382 0.0093
-2.750 -0.0698 0.01017 0.00316 -0.0195 0.5287 0.0097
-2.500 -0.0454 0.00988 0.00283 -0.0188 0.5196 0.0107
-2.250 -0.0199 0.00971 0.00262 -0.0182 0.5108 0.0120
-2.000 0.0053 0.00952 0.00238 -0.0176 0.5017 0.0141
-1.750 0.0293 0.00920 0.00216 -0.0168 0.4937 0.0408
-1.500 0.0539 0.00898 0.00205 -0.0162 0.4856 0.0809
-1.000 0.0833 0.00695 0.00160 -0.0120 0.4721 0.5647
-0.750 0.0963 0.00628 0.00171 -0.0089 0.4656 0.8046
-0.500 0.1223 0.00644 0.00188 -0.0081 0.4584 0.8309
-0.250 0.1489 0.00660 0.00197 -0.0076 0.4513 0.8419
0.000 0.1762 0.00673 0.00209 -0.0072 0.4452 0.8502
0.250 0.2022 0.00690 0.00223 -0.0066 0.4384 0.8598
0.500 0.2291 0.00706 0.00236 -0.0061 0.4325 0.8663
0.750 0.2561 0.00719 0.00245 -0.0058 0.4266 0.8722
1.000 0.2825 0.00729 0.00250 -0.0053 0.4204 0.8759
1.250 0.3108 0.00731 0.00250 -0.0054 0.4153 0.8771
1.500 0.3388 0.00736 0.00249 -0.0055 0.4096 0.8782
1.750 0.3666 0.00743 0.00250 -0.0056 0.4042 0.8792
2.000 0.3950 0.00745 0.00251 -0.0058 0.3996 0.8804
2.250 0.4229 0.00751 0.00253 -0.0059 0.3943 0.8816
2.500 0.4506 0.00760 0.00256 -0.0060 0.3892 0.8827
2.750 0.4791 0.00762 0.00258 -0.0062 0.3850 0.8837
3.000 0.5072 0.00768 0.00261 -0.0064 0.3803 0.8847
3.250 0.5347 0.00778 0.00266 -0.0064 0.3754 0.8857
3.500 0.5629 0.00784 0.00271 -0.0066 0.3714 0.8867
3.750 0.5910 0.00788 0.00275 -0.0068 0.3669 0.8877
4.000 0.6183 0.00794 0.00278 -0.0068 0.3623 0.8888
4.250 0.6455 0.00802 0.00285 -0.0069 0.3577 0.8899
4.500 0.6734 0.00807 0.00290 -0.0070 0.3538 0.8909
4.750 0.7008 0.00814 0.00298 -0.0070 0.3493 0.8920
5.000 0.7275 0.00827 0.00308 -0.0070 0.3443 0.8931
5.250 0.7553 0.00833 0.00316 -0.0071 0.3406 0.8943
5.500 0.7827 0.00841 0.00325 -0.0072 0.3359 0.8956
5.750 0.8093 0.00853 0.00336 -0.0072 0.3307 0.8970
6.000 0.8365 0.00863 0.00347 -0.0072 0.3262 0.8985
6.250 0.8639 0.00871 0.00357 -0.0073 0.3214 0.8998
6.500 0.8905 0.00885 0.00369 -0.0073 0.3161 0.9010
6.750 0.9175 0.00896 0.00381 -0.0074 0.3112 0.9022
7.000 0.9445 0.00905 0.00393 -0.0075 0.3057 0.9035
7.250 0.9699 0.00920 0.00406 -0.0073 0.2994 0.9051
7.500 0.9965 0.00929 0.00419 -0.0072 0.2940 0.9066
7.750 1.0220 0.00944 0.00435 -0.0071 0.2872 0.9082
8.000 1.0478 0.00958 0.00451 -0.0069 0.2810 0.9099
8.250 1.0732 0.00974 0.00468 -0.0067 0.2739 0.9117
8.500 1.0982 0.00992 0.00488 -0.0065 0.2664 0.9137
8.750 1.1228 0.01013 0.00508 -0.0062 0.2579 0.9158
9.000 1.1477 0.01033 0.00529 -0.0060 0.2497 0.9177
9.250 1.1708 0.01058 0.00553 -0.0054 0.2397 0.9201
9.500 1.1931 0.01084 0.00579 -0.0048 0.2288 0.9225
9.750 1.2152 0.01112 0.00606 -0.0041 0.2174 0.9252
10.000 1.2366 0.01145 0.00637 -0.0033 0.2056 0.9282
10.250 1.2564 0.01186 0.00674 -0.0023 0.1910 0.9314
10.500 1.2749 0.01227 0.00713 -0.0011 0.1771 0.9350
10.750 1.2915 0.01271 0.00754 0.0005 0.1638 0.9395
11.000 1.3071 0.01318 0.00799 0.0022 0.1509 0.9448
11.250 1.3192 0.01371 0.00849 0.0045 0.1366 0.9517
11.500 1.3259 0.01428 0.00902 0.0079 0.1224 0.9637
11.750 1.3430 0.01493 0.00966 0.0088 0.1103 0.9784
12.000 1.3634 0.01586 0.01052 0.0085 0.0939 1.0000
12.250 1.3735 0.01659 0.01122 0.0105 0.0855 1.0000
12.500 1.3822 0.01738 0.01200 0.0126 0.0772 1.0000
12.750 1.3863 0.01841 0.01300 0.0150 0.0675 1.0000
13.000 1.3915 0.01946 0.01405 0.0171 0.0617 1.0000
13.250 1.3926 0.02083 0.01541 0.0192 0.0545 1.0000
13.500 1.3984 0.02206 0.01668 0.0206 0.0510 1.0000
13.750 1.3975 0.02388 0.01850 0.0221 0.0454 1.0000
14.000 1.4014 0.02554 0.02021 0.0229 0.0424 1.0000
14.250 1.3985 0.02786 0.02256 0.0237 0.0379 1.0000
14.500 1.4007 0.02993 0.02470 0.0241 0.0363 1.0000
14.750 1.3985 0.03249 0.02730 0.0243 0.0327 1.0000
15.000 1.3935 0.03545 0.03031 0.0244 0.0302 1.0000
15.250 1.3904 0.03830 0.03322 0.0242 0.0276 1.0000
15.500 1.3860 0.04137 0.03636 0.0240 0.0263 1.0000
15.750 1.3777 0.04493 0.03998 0.0235 0.0244 1.0000
16.000 1.3725 0.04822 0.04335 0.0230 0.0230 1.0000
16.250 1.3669 0.05164 0.04685 0.0223 0.0222 1.0000
16.500 1.3576 0.05561 0.05089 0.0214 0.0208 1.0000
16.750 1.3477 0.05980 0.05514 0.0203 0.0195 1.0000
17.000 1.3420 0.06355 0.05898 0.0192 0.0185 1.0000
17.250 1.3343 0.06765 0.06314 0.0179 0.0173 1.0000
17.500 1.3255 0.07196 0.06751 0.0165 0.0164 1.0000
17.750 1.3169 0.07638 0.07201 0.0150 0.0158 1.0000
18.000 1.3101 0.08062 0.07633 0.0134 0.0151 1.0000
18.250 1.3040 0.08482 0.08062 0.0117 0.0144 1.0000
18.500 1.2969 0.08926 0.08513 0.0100 0.0139 1.0000
18.750 1.2867 0.09423 0.09016 0.0079 0.0126 1.0000
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