EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 332 AIRFOIL (e332-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.77 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e332-il-1000000-n5.txt Download as CSV file: xf-e332-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 332 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3896 0.09179 0.08938 -0.0220 0.7441 0.0057
-9.250 -0.3946 0.08718 0.08471 -0.0239 0.7213 0.0058
-7.750 -0.4269 0.06449 0.06169 -0.0325 0.6346 0.0057
-5.250 -0.3681 0.02277 0.01774 -0.0132 0.5449 0.0037
-5.000 -0.3544 0.01849 0.01287 -0.0101 0.5367 0.0035
-4.750 -0.3322 0.01662 0.01067 -0.0087 0.5277 0.0035
-4.500 -0.3083 0.01517 0.00892 -0.0077 0.5191 0.0034
-4.250 -0.2836 0.01394 0.00745 -0.0068 0.5093 0.0034
-4.000 -0.2583 0.01318 0.00652 -0.0061 0.5009 0.0034
-3.750 -0.2333 0.01241 0.00560 -0.0054 0.4919 0.0034
-3.500 -0.2079 0.01188 0.00496 -0.0047 0.4845 0.0034
-3.000 -0.1577 0.01097 0.00385 -0.0033 0.4680 0.0034
-2.750 -0.1324 0.01065 0.00345 -0.0027 0.4603 0.0034
-2.500 -0.1068 0.01034 0.00308 -0.0021 0.4537 0.0035
-2.250 -0.0811 0.01011 0.00279 -0.0016 0.4468 0.0036
-2.000 -0.0550 0.00990 0.00253 -0.0011 0.4405 0.0036
-1.750 -0.0291 0.00969 0.00226 -0.0006 0.4335 0.0039
-1.500 -0.0029 0.00953 0.00206 -0.0002 0.4271 0.0042
-1.250 0.0237 0.00942 0.00191 0.0002 0.4206 0.0051
-1.000 0.0503 0.00934 0.00179 0.0005 0.4150 0.0059
-0.750 0.0770 0.00922 0.00168 0.0008 0.4094 0.0104
-0.500 0.1033 0.00911 0.00160 0.0012 0.4032 0.0247
-0.250 0.1292 0.00895 0.00154 0.0016 0.3978 0.0577
0.000 0.1501 0.00831 0.00147 0.0027 0.3930 0.2456
0.250 0.1397 0.00614 0.00141 0.0104 0.3898 0.8690
0.500 0.1652 0.00625 0.00151 0.0112 0.3847 0.8954
0.750 0.1917 0.00634 0.00158 0.0117 0.3795 0.9069
1.000 0.2168 0.00648 0.00168 0.0126 0.3744 0.9195
1.250 0.2430 0.00661 0.00178 0.0132 0.3698 0.9269
1.500 0.2686 0.00671 0.00185 0.0139 0.3650 0.9333
1.750 0.2963 0.00678 0.00188 0.0140 0.3599 0.9351
2.000 0.3242 0.00685 0.00189 0.0140 0.3553 0.9361
2.250 0.3523 0.00690 0.00191 0.0139 0.3506 0.9370
2.500 0.3801 0.00696 0.00193 0.0139 0.3458 0.9379
2.750 0.4078 0.00703 0.00196 0.0139 0.3413 0.9388
3.000 0.4356 0.00708 0.00200 0.0138 0.3367 0.9399
3.250 0.4632 0.00715 0.00204 0.0138 0.3321 0.9410
3.500 0.4905 0.00724 0.00209 0.0139 0.3273 0.9421
3.750 0.5182 0.00730 0.00213 0.0138 0.3230 0.9430
4.000 0.5456 0.00737 0.00219 0.0138 0.3183 0.9440
4.250 0.5727 0.00747 0.00226 0.0138 0.3132 0.9450
4.500 0.6002 0.00754 0.00232 0.0138 0.3090 0.9459
4.750 0.6275 0.00763 0.00239 0.0138 0.3039 0.9468
5.000 0.6547 0.00774 0.00248 0.0138 0.2986 0.9477
5.250 0.6823 0.00782 0.00258 0.0137 0.2939 0.9487
5.500 0.7094 0.00793 0.00268 0.0138 0.2882 0.9498
5.750 0.7363 0.00805 0.00279 0.0138 0.2826 0.9508
6.000 0.7633 0.00816 0.00291 0.0138 0.2769 0.9519
6.500 0.8166 0.00842 0.00316 0.0139 0.2644 0.9542
6.750 0.8427 0.00859 0.00332 0.0140 0.2569 0.9555
7.000 0.8691 0.00872 0.00346 0.0141 0.2502 0.9568
7.250 0.8947 0.00891 0.00362 0.0143 0.2414 0.9582
7.500 0.9202 0.00910 0.00380 0.0145 0.2320 0.9596
7.750 0.9454 0.00929 0.00399 0.0147 0.2234 0.9610
8.000 0.9706 0.00955 0.00421 0.0149 0.2110 0.9624
8.250 0.9958 0.00982 0.00446 0.0151 0.2001 0.9640
8.500 1.0205 0.01012 0.00473 0.0153 0.1884 0.9658
8.750 1.0443 0.01046 0.00504 0.0156 0.1744 0.9678
9.250 1.0901 0.01120 0.00571 0.0166 0.1479 0.9723
9.500 1.1123 0.01160 0.00608 0.0172 0.1360 0.9748
9.750 1.1368 0.01209 0.00652 0.0171 0.1208 0.9765
10.000 1.1605 0.01267 0.00703 0.0171 0.1044 0.9785
10.250 1.1843 0.01320 0.00753 0.0171 0.0923 0.9808
10.500 1.2061 0.01384 0.00810 0.0173 0.0787 0.9837
10.750 1.2283 0.01443 0.00868 0.0175 0.0682 0.9864
11.000 1.2525 0.01518 0.00937 0.0170 0.0565 0.9880
11.250 1.2764 0.01588 0.01005 0.0165 0.0476 0.9899
11.500 1.2967 0.01686 0.01096 0.0163 0.0352 0.9926
11.750 1.3199 0.01747 0.01161 0.0161 0.0322 0.9957
12.000 1.3361 0.01828 0.01243 0.0168 0.0271 1.0000
12.250 1.3282 0.01906 0.01320 0.0221 0.0220 1.0000
12.500 1.3368 0.01964 0.01385 0.0245 0.0225 1.0000
12.750 1.3402 0.02063 0.01488 0.0269 0.0196 1.0000
13.000 1.3366 0.02228 0.01652 0.0292 0.0143 1.0000
13.250 1.3408 0.02371 0.01802 0.0304 0.0134 1.0000
13.500 1.3417 0.02562 0.01997 0.0312 0.0111 1.0000
13.750 1.3403 0.02797 0.02236 0.0316 0.0089 1.0000
14.000 1.3450 0.02991 0.02439 0.0317 0.0090 1.0000
14.250 1.3467 0.03224 0.02679 0.0315 0.0084 1.0000
14.500 1.3458 0.03492 0.02955 0.0313 0.0076 1.0000
14.750 1.3434 0.03784 0.03256 0.0309 0.0070 1.0000
15.000 1.3382 0.04111 0.03591 0.0303 0.0061 1.0000
15.250 1.3356 0.04413 0.03902 0.0298 0.0061 1.0000
15.500 1.3306 0.04748 0.04245 0.0291 0.0057 1.0000
15.750 1.3223 0.05123 0.04628 0.0283 0.0051 1.0000
16.000 1.3192 0.05442 0.04957 0.0275 0.0055 1.0000
16.250 1.3057 0.05901 0.05422 0.0262 0.0043 1.0000
16.500 1.2995 0.06281 0.05811 0.0251 0.0044 1.0000
16.750 1.2908 0.06705 0.06243 0.0238 0.0038 1.0000
17.000 1.2836 0.07114 0.06661 0.0225 0.0038 1.0000
17.250 1.2770 0.07523 0.07078 0.0211 0.0037 1.0000
17.500 1.2705 0.07943 0.07506 0.0196 0.0037 1.0000
17.750 1.2631 0.08378 0.07950 0.0180 0.0037 1.0000
18.000 1.2520 0.08873 0.08452 0.0161 0.0031 1.0000
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Polar data table (+)
Polar graphs
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