EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 200,000 Max Cl/Cd: 63.59 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e328-il-200000-n5.txt Download as CSV file: xf-e328-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3819 0.08881 0.08542 -0.0314 1.0000 0.0219
-9.000 -0.3869 0.08420 0.08086 -0.0341 1.0000 0.0218
-8.750 -0.3987 0.07866 0.07536 -0.0382 1.0000 0.0215
-8.500 -0.4140 0.07413 0.07083 -0.0400 1.0000 0.0212
-8.250 -0.4624 0.06532 0.06186 -0.0376 1.0000 0.0125
-8.000 -0.4713 0.06301 0.05953 -0.0350 1.0000 0.0124
-7.750 -0.4724 0.06010 0.05656 -0.0340 0.9935 0.0122
-7.500 -0.4638 0.05533 0.05161 -0.0355 0.9660 0.0120
-7.250 -0.4418 0.05093 0.04696 -0.0386 0.9243 0.0115
-7.000 -0.4177 0.04481 0.04039 -0.0418 0.8889 0.0113
-6.500 -0.3848 0.03540 0.02996 -0.0406 0.8221 0.0107
-6.250 -0.3719 0.03174 0.02577 -0.0382 0.7962 0.0106
-6.000 -0.3563 0.02900 0.02255 -0.0360 0.7734 0.0109
-5.750 -0.3380 0.02682 0.01992 -0.0341 0.7529 0.0113
-5.500 -0.3175 0.02444 0.01691 -0.0322 0.7347 0.0124
-5.250 -0.2949 0.02281 0.01487 -0.0309 0.7172 0.0128
-5.000 -0.2715 0.02162 0.01345 -0.0301 0.7004 0.0131
-4.750 -0.2466 0.02041 0.01200 -0.0293 0.6850 0.0133
-4.500 -0.2214 0.01936 0.01075 -0.0285 0.6701 0.0136
-4.250 -0.1963 0.01848 0.00968 -0.0278 0.6563 0.0139
-4.000 -0.1718 0.01768 0.00873 -0.0269 0.6429 0.0144
-3.750 -0.1481 0.01696 0.00789 -0.0260 0.6303 0.0151
-3.500 -0.1252 0.01635 0.00716 -0.0249 0.6182 0.0158
-3.250 -0.1031 0.01582 0.00656 -0.0238 0.6068 0.0168
-3.000 -0.0805 0.01542 0.00607 -0.0227 0.5955 0.0182
-2.750 -0.0575 0.01505 0.00565 -0.0217 0.5846 0.0224
-2.500 -0.0348 0.01470 0.00523 -0.0207 0.5749 0.0278
-2.250 -0.0127 0.01431 0.00483 -0.0195 0.5649 0.0408
-2.000 0.0091 0.01390 0.00452 -0.0184 0.5553 0.0730
-1.750 0.0273 0.01325 0.00423 -0.0168 0.5467 0.1757
-1.500 0.0182 0.01127 0.00474 -0.0090 0.5401 0.7746
-1.250 0.0386 0.01169 0.00505 -0.0065 0.5320 0.8274
-1.000 0.0610 0.01213 0.00539 -0.0043 0.5236 0.8536
-0.750 0.0868 0.01268 0.00582 -0.0026 0.5155 0.8736
-0.500 0.1164 0.01316 0.00618 -0.0017 0.5070 0.8891
-0.250 0.1521 0.01356 0.00643 -0.0025 0.4993 0.8991
0.000 0.1737 0.01354 0.00630 -0.0012 0.4920 0.9038
0.250 0.2020 0.01356 0.00618 -0.0014 0.4848 0.9052
0.500 0.2296 0.01356 0.00609 -0.0014 0.4777 0.9068
0.750 0.2561 0.01358 0.00600 -0.0012 0.4711 0.9087
1.000 0.2815 0.01359 0.00591 -0.0008 0.4653 0.9108
1.250 0.3052 0.01358 0.00584 -0.0002 0.4587 0.9133
1.500 0.3259 0.01358 0.00575 0.0011 0.4531 0.9164
1.750 0.3484 0.01357 0.00568 0.0020 0.4475 0.9186
2.000 0.3763 0.01361 0.00567 0.0019 0.4415 0.9198
2.250 0.4036 0.01368 0.00566 0.0018 0.4363 0.9212
2.500 0.4305 0.01372 0.00568 0.0019 0.4305 0.9227
2.750 0.4564 0.01377 0.00569 0.0021 0.4251 0.9243
3.000 0.4814 0.01385 0.00570 0.0024 0.4205 0.9260
3.250 0.5060 0.01390 0.00576 0.0029 0.4151 0.9283
3.500 0.5287 0.01395 0.00579 0.0037 0.4100 0.9310
3.750 0.5511 0.01402 0.00581 0.0046 0.4057 0.9333
4.000 0.5787 0.01410 0.00592 0.0044 0.4006 0.9344
4.250 0.6059 0.01420 0.00602 0.0043 0.3953 0.9358
4.500 0.6325 0.01432 0.00611 0.0043 0.3908 0.9373
4.750 0.6590 0.01443 0.00624 0.0043 0.3859 0.9391
5.000 0.6848 0.01454 0.00640 0.0044 0.3809 0.9413
5.250 0.7091 0.01466 0.00651 0.0049 0.3764 0.9438
5.500 0.7320 0.01478 0.00664 0.0056 0.3720 0.9464
5.750 0.7576 0.01490 0.00683 0.0057 0.3667 0.9483
6.000 0.7852 0.01506 0.00701 0.0054 0.3618 0.9498
6.250 0.8124 0.01523 0.00720 0.0052 0.3571 0.9515
6.500 0.8390 0.01538 0.00745 0.0050 0.3516 0.9536
6.750 0.8646 0.01555 0.00764 0.0051 0.3465 0.9560
7.000 0.8890 0.01573 0.00786 0.0054 0.3415 0.9591
7.250 0.9141 0.01590 0.00813 0.0056 0.3355 0.9619
7.500 0.9423 0.01612 0.00837 0.0050 0.3300 0.9638
7.750 0.9699 0.01633 0.00868 0.0046 0.3236 0.9660
8.000 0.9963 0.01654 0.00897 0.0043 0.3171 0.9686
8.250 1.0212 0.01677 0.00926 0.0044 0.3111 0.9719
8.500 1.0472 0.01700 0.00960 0.0042 0.3038 0.9748
8.750 1.0750 0.01728 0.00995 0.0035 0.2966 0.9772
9.000 1.1020 0.01756 0.01032 0.0030 0.2881 0.9803
9.250 1.1274 0.01786 0.01071 0.0028 0.2800 0.9843
9.500 1.1548 0.01822 0.01114 0.0020 0.2707 0.9874
9.750 1.1822 0.01859 0.01162 0.0012 0.2607 0.9913
10.000 1.2075 0.01901 0.01213 0.0007 0.2503 0.9966
10.250 1.2181 0.01940 0.01253 0.0031 0.2414 1.0000
10.500 1.2228 0.01971 0.01292 0.0067 0.2330 1.0000
10.750 1.2296 0.02017 0.01341 0.0097 0.2236 1.0000
11.000 1.2356 0.02074 0.01399 0.0127 0.2137 1.0000
11.250 1.2441 0.02138 0.01468 0.0150 0.2027 1.0000
11.500 1.2509 0.02218 0.01551 0.0172 0.1913 1.0000
11.750 1.2564 0.02313 0.01648 0.0194 0.1804 1.0000
12.000 1.2596 0.02431 0.01769 0.0214 0.1695 1.0000
12.500 1.2626 0.02731 0.02074 0.0246 0.1489 1.0000
12.750 1.2625 0.02917 0.02265 0.0257 0.1393 1.0000
13.000 1.2601 0.03139 0.02490 0.0264 0.1309 1.0000
13.250 1.2569 0.03386 0.02741 0.0269 0.1223 1.0000
13.500 1.2542 0.03644 0.03005 0.0270 0.1149 1.0000
13.750 1.2474 0.03956 0.03320 0.0270 0.1083 1.0000
14.000 1.2441 0.04245 0.03618 0.0267 0.1019 1.0000
14.250 1.2353 0.04601 0.03978 0.0262 0.0963 1.0000
14.500 1.2306 0.04922 0.04309 0.0257 0.0907 1.0000
14.750 1.2213 0.05304 0.04696 0.0249 0.0856 1.0000
15.000 1.2149 0.05662 0.05062 0.0240 0.0812 1.0000
15.250 1.2078 0.06041 0.05450 0.0230 0.0769 1.0000
15.750 1.1934 0.06840 0.06263 0.0206 0.0691 1.0000
16.000 1.1852 0.07270 0.06698 0.0191 0.0652 1.0000
16.250 1.1767 0.07713 0.07147 0.0175 0.0621 1.0000
16.500 1.1721 0.08110 0.07554 0.0160 0.0583 1.0000
16.750 1.1641 0.08568 0.08018 0.0142 0.0551 1.0000
17.000 1.1561 0.09033 0.08488 0.0123 0.0524 1.0000
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Polar data table (+)
Polar graphs
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