EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 332 AIRFOIL (e332-il) Reynolds number: 50,000 Max Cl/Cd: 27.7 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e332-il-50000-n5.txt Download as CSV file: xf-e332-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4142 0.10553 0.09914 -0.0110 1.0000 0.1103
-8.750 -0.4353 0.10306 0.09682 -0.0171 1.0000 0.1139
-8.500 -0.4410 0.09893 0.09280 -0.0194 1.0000 0.1153
-8.250 -0.4210 0.09467 0.08857 -0.0173 1.0000 0.1177
-8.000 -0.4176 0.09105 0.08503 -0.0180 1.0000 0.1201
-7.500 -0.4591 0.08629 0.08036 -0.0218 1.0000 0.1302
-7.000 -0.4345 0.07291 0.06664 -0.0246 1.0000 0.0556
-6.750 -0.4284 0.06940 0.06320 -0.0237 1.0000 0.0528
-6.500 -0.4277 0.06572 0.05946 -0.0227 1.0000 0.0495
-6.250 -0.4280 0.06208 0.05546 -0.0211 1.0000 0.0440
-6.000 -0.4236 0.05913 0.05253 -0.0193 1.0000 0.0430
-5.750 -0.4213 0.05647 0.04983 -0.0170 1.0000 0.0421
-5.500 -0.4218 0.05417 0.04746 -0.0141 1.0000 0.0413
-5.250 -0.3944 0.05011 0.04307 -0.0165 0.9738 0.0398
-5.000 -0.3634 0.04608 0.03858 -0.0187 0.9464 0.0386
-4.750 -0.3311 0.04245 0.03442 -0.0203 0.9218 0.0376
-4.500 -0.2965 0.03913 0.03053 -0.0216 0.9003 0.0369
-4.250 -0.2640 0.03647 0.02740 -0.0224 0.8776 0.0379
-4.000 -0.2310 0.03427 0.02470 -0.0230 0.8567 0.0398
-3.750 -0.2001 0.03226 0.02218 -0.0227 0.8353 0.0423
-3.500 -0.1683 0.03044 0.01985 -0.0224 0.8153 0.0436
-3.250 -0.1344 0.02855 0.01757 -0.0222 0.7968 0.0454
-3.000 -0.1016 0.02717 0.01603 -0.0225 0.7784 0.0499
-2.750 -0.0645 0.02605 0.01452 -0.0230 0.7604 0.0569
-2.500 -0.0328 0.02491 0.01329 -0.0230 0.7435 0.0668
-2.000 0.1747 0.02049 0.01114 -0.0455 0.7073 1.0000
-1.750 0.1967 0.02053 0.01078 -0.0445 0.6918 1.0000
-1.500 0.2189 0.02058 0.01049 -0.0435 0.6773 1.0000
-1.250 0.2412 0.02065 0.01027 -0.0426 0.6636 1.0000
-1.000 0.2637 0.02074 0.01009 -0.0417 0.6508 1.0000
-0.750 0.2864 0.02085 0.00992 -0.0409 0.6388 1.0000
-0.500 0.3091 0.02096 0.00980 -0.0400 0.6278 1.0000
-0.250 0.3319 0.02111 0.00977 -0.0392 0.6160 1.0000
0.000 0.3547 0.02127 0.00976 -0.0385 0.6053 1.0000
0.250 0.3777 0.02142 0.00971 -0.0376 0.5962 1.0000
0.500 0.4003 0.02163 0.00982 -0.0369 0.5856 1.0000
0.750 0.4230 0.02185 0.00992 -0.0361 0.5762 1.0000
1.000 0.4461 0.02206 0.01000 -0.0353 0.5677 1.0000
1.250 0.4689 0.02236 0.01023 -0.0347 0.5584 1.0000
1.750 0.5141 0.02294 0.01066 -0.0331 0.5417 1.0000
2.000 0.5367 0.02321 0.01083 -0.0322 0.5347 1.0000
2.250 0.5585 0.02360 0.01124 -0.0315 0.5260 1.0000
2.500 0.5808 0.02391 0.01148 -0.0306 0.5193 1.0000
2.750 0.6022 0.02436 0.01197 -0.0298 0.5111 1.0000
3.000 0.6245 0.02467 0.01219 -0.0288 0.5052 1.0000
3.250 0.6449 0.02520 0.01281 -0.0279 0.4967 1.0000
3.500 0.6672 0.02551 0.01306 -0.0269 0.4909 1.0000
3.750 0.6867 0.02615 0.01383 -0.0260 0.4829 1.0000
4.000 0.7085 0.02651 0.01415 -0.0249 0.4769 1.0000
4.250 0.7275 0.02717 0.01491 -0.0239 0.4694 1.0000
4.500 0.7483 0.02762 0.01539 -0.0228 0.4632 1.0000
4.750 0.7674 0.02824 0.01613 -0.0217 0.4564 1.0000
5.000 0.7865 0.02883 0.01681 -0.0205 0.4496 1.0000
5.250 0.8070 0.02931 0.01731 -0.0193 0.4440 1.0000
5.500 0.8230 0.03016 0.01832 -0.0180 0.4363 1.0000
5.750 0.8448 0.03050 0.01870 -0.0168 0.4312 1.0000
6.000 0.8578 0.03157 0.01998 -0.0152 0.4232 1.0000
6.250 0.8781 0.03198 0.02044 -0.0139 0.4175 1.0000
6.500 0.8910 0.03302 0.02166 -0.0123 0.4102 1.0000
6.750 0.9089 0.03360 0.02236 -0.0108 0.4038 1.0000
7.000 0.9229 0.03448 0.02339 -0.0091 0.3970 1.0000
7.250 0.9371 0.03530 0.02435 -0.0074 0.3899 1.0000
7.500 0.9533 0.03596 0.02512 -0.0057 0.3836 1.0000
7.750 0.9624 0.03710 0.02647 -0.0036 0.3758 1.0000
8.000 0.9815 0.03749 0.02694 -0.0021 0.3698 1.0000
8.250 0.9846 0.03897 0.02863 0.0004 0.3614 1.0000
8.500 1.0045 0.03926 0.02901 0.0018 0.3552 1.0000
8.750 1.0030 0.04096 0.03091 0.0047 0.3466 1.0000
9.000 1.0190 0.04142 0.03151 0.0064 0.3398 1.0000
9.250 1.0175 0.04304 0.03331 0.0092 0.3315 1.0000
9.500 1.0238 0.04413 0.03453 0.0114 0.3241 1.0000
9.750 1.0282 0.04526 0.03579 0.0138 0.3162 1.0000
10.000 1.0146 0.04773 0.03838 0.0167 0.3083 1.0000
10.250 1.0347 0.04760 0.03837 0.0183 0.3007 1.0000
10.500 0.9624 0.05535 0.04608 0.0209 0.2922 1.0000
10.750 1.0263 0.05093 0.04190 0.0230 0.2855 1.0000
11.000 0.9368 0.06297 0.05381 0.0209 0.2742 1.0000
11.250 0.9032 0.07038 0.06120 0.0187 0.2627 1.0000
11.500 0.9456 0.06673 0.05778 0.0218 0.2580 1.0000
11.750 0.9055 0.07547 0.06647 0.0188 0.2458 1.0000
12.250 0.9166 0.07930 0.07055 0.0193 0.2303 1.0000
12.500 0.8845 0.08771 0.07888 0.0161 0.2190 1.0000
13.000 0.8939 0.09207 0.08348 0.0161 0.2037 1.0000
13.500 0.9050 0.09616 0.08779 0.0160 0.1891 1.0000
13.750 0.8669 0.10678 0.09833 0.0114 0.1786 1.0000
14.000 0.8590 0.11176 0.10335 0.0097 0.1712 1.0000
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Polar data table (+)
Polar graphs
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