EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 332 AIRFOIL (e332-il) Reynolds number: 100,000 Max Cl/Cd: 40.72 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e332-il-100000.txt Download as CSV file: xf-e332-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4296 0.10628 0.10170 -0.0162 1.0000 0.0699
-9.000 -0.4416 0.10277 0.09826 -0.0219 1.0000 0.0702
-8.750 -0.4542 0.09986 0.09537 -0.0243 1.0000 0.0703
-8.500 -0.4115 0.09358 0.08915 -0.0166 1.0000 0.0738
-8.250 -0.4077 0.09023 0.08585 -0.0175 1.0000 0.0755
-8.000 -0.4091 0.08662 0.08231 -0.0194 1.0000 0.0777
-7.750 -0.4158 0.08311 0.07885 -0.0214 1.0000 0.0796
-7.500 -0.4281 0.08004 0.07581 -0.0226 1.0000 0.0819
-7.250 -0.4442 0.07807 0.07371 -0.0242 1.0000 0.0839
-7.000 -0.4611 0.07768 0.07298 -0.0232 1.0000 0.0847
-6.750 -0.4379 0.06984 0.06558 -0.0229 1.0000 0.0872
-6.500 -0.4298 0.06676 0.06255 -0.0215 1.0000 0.0904
-6.250 -0.4280 0.06415 0.05993 -0.0203 1.0000 0.0946
-6.000 -0.4487 0.06579 0.06104 -0.0166 1.0000 0.0996
-5.750 -0.4494 0.06057 0.05620 -0.0143 1.0000 0.1011
-5.500 -0.4274 0.05680 0.05257 -0.0161 0.9897 0.1057
-5.250 -0.3904 0.05232 0.04781 -0.0217 0.9689 0.1185
-5.000 -0.3533 0.04823 0.04354 -0.0261 0.9494 0.1340
-4.750 -0.3179 0.04466 0.03979 -0.0294 0.9288 0.1517
-4.500 -0.2898 0.04175 0.03664 -0.0310 0.9053 0.1791
-4.250 -0.2674 0.03906 0.03396 -0.0307 0.8813 0.2143
-3.500 -0.1667 0.02941 0.02156 -0.0252 0.8204 0.0679
-3.250 -0.1401 0.02677 0.01826 -0.0230 0.8021 0.0588
-3.000 -0.1128 0.02559 0.01669 -0.0214 0.7840 0.0563
-2.750 -0.0851 0.02381 0.01462 -0.0204 0.7674 0.0557
-2.500 -0.0565 0.02248 0.01301 -0.0194 0.7515 0.0565
-2.250 -0.0290 0.02097 0.01151 -0.0188 0.7362 0.0626
-2.000 0.1953 0.01631 0.00952 -0.0488 0.7114 1.0000
-1.750 0.2168 0.01634 0.00924 -0.0477 0.6964 1.0000
-1.500 0.2387 0.01640 0.00902 -0.0467 0.6826 1.0000
-1.250 0.2606 0.01647 0.00883 -0.0457 0.6698 1.0000
-1.000 0.2828 0.01655 0.00866 -0.0447 0.6581 1.0000
-0.750 0.3054 0.01665 0.00859 -0.0439 0.6456 1.0000
-0.500 0.3281 0.01677 0.00855 -0.0432 0.6340 1.0000
-0.250 0.3509 0.01690 0.00851 -0.0423 0.6239 1.0000
0.000 0.3738 0.01704 0.00849 -0.0415 0.6139 1.0000
0.250 0.3970 0.01722 0.00857 -0.0409 0.6037 1.0000
0.500 0.4201 0.01738 0.00857 -0.0400 0.5953 1.0000
0.750 0.4433 0.01757 0.00870 -0.0393 0.5854 1.0000
1.000 0.4665 0.01779 0.00883 -0.0387 0.5769 1.0000
1.250 0.4898 0.01799 0.00893 -0.0379 0.5687 1.0000
1.500 0.5130 0.01825 0.00916 -0.0373 0.5600 1.0000
1.750 0.5365 0.01846 0.00927 -0.0365 0.5528 1.0000
2.000 0.5595 0.01878 0.00959 -0.0359 0.5444 1.0000
2.250 0.5830 0.01900 0.00972 -0.0351 0.5375 1.0000
2.500 0.6057 0.01936 0.01013 -0.0345 0.5295 1.0000
2.750 0.6290 0.01962 0.01032 -0.0337 0.5228 1.0000
3.000 0.6514 0.02003 0.01077 -0.0330 0.5154 1.0000
3.250 0.6744 0.02032 0.01104 -0.0322 0.5086 1.0000
3.500 0.6967 0.02075 0.01151 -0.0315 0.5018 1.0000
3.750 0.7189 0.02112 0.01191 -0.0307 0.4947 1.0000
4.000 0.7417 0.02149 0.01225 -0.0298 0.4888 1.0000
4.250 0.7626 0.02201 0.01288 -0.0290 0.4813 1.0000
4.500 0.7863 0.02228 0.01309 -0.0281 0.4760 1.0000
4.750 0.8055 0.02295 0.01395 -0.0271 0.4680 1.0000
5.000 0.8285 0.02323 0.01420 -0.0262 0.4622 1.0000
5.250 0.8476 0.02392 0.01504 -0.0251 0.4550 1.0000
5.500 0.8694 0.02428 0.01544 -0.0241 0.4486 1.0000
5.750 0.8894 0.02487 0.01612 -0.0230 0.4420 1.0000
6.000 0.9094 0.02535 0.01669 -0.0219 0.4348 1.0000
6.250 0.9313 0.02574 0.01711 -0.0208 0.4291 1.0000
6.500 0.9482 0.02644 0.01798 -0.0194 0.4210 1.0000
6.750 0.9736 0.02653 0.01799 -0.0186 0.4157 1.0000
7.000 0.9861 0.02749 0.01923 -0.0167 0.4067 1.0000
7.250 1.0122 0.02746 0.01914 -0.0160 0.4011 1.0000
7.500 1.0235 0.02842 0.02037 -0.0139 0.3919 1.0000
7.750 1.0505 0.02830 0.02016 -0.0132 0.3860 1.0000
8.000 1.0604 0.02923 0.02138 -0.0108 0.3765 1.0000
8.250 1.0831 0.02933 0.02150 -0.0097 0.3695 1.0000
8.500 1.0979 0.02981 0.02214 -0.0077 0.3604 1.0000
8.750 1.1145 0.03022 0.02267 -0.0060 0.3520 1.0000
9.000 1.1388 0.02998 0.02241 -0.0049 0.3435 1.0000
9.250 1.1484 0.03067 0.02333 -0.0023 0.3338 1.0000
9.500 1.1698 0.03055 0.02324 -0.0009 0.3246 1.0000
9.750 1.1904 0.03038 0.02310 0.0006 0.3147 1.0000
10.000 1.1994 0.03089 0.02381 0.0034 0.3040 1.0000
10.250 1.2144 0.03098 0.02398 0.0055 0.2932 1.0000
10.500 1.2326 0.03083 0.02384 0.0073 0.2821 1.0000
10.750 1.2498 0.03069 0.02370 0.0092 0.2700 1.0000
11.000 1.2582 0.03097 0.02409 0.0121 0.2577 1.0000
11.250 1.2632 0.03139 0.02462 0.0153 0.2451 1.0000
11.500 1.2671 0.03189 0.02520 0.0185 0.2323 1.0000
11.750 1.2688 0.03254 0.02591 0.0218 0.2196 1.0000
12.000 1.2678 0.03340 0.02681 0.0252 0.2075 1.0000
12.250 1.2622 0.03439 0.02781 0.0290 0.1964 1.0000
12.500 1.2582 0.03560 0.02899 0.0321 0.1855 1.0000
12.750 1.2544 0.03706 0.03037 0.0345 0.1743 1.0000
13.000 1.2449 0.03911 0.03254 0.0364 0.1644 1.0000
13.250 1.2358 0.04160 0.03511 0.0376 0.1550 1.0000
13.500 1.2309 0.04400 0.03748 0.0384 0.1456 1.0000
13.750 1.2286 0.04628 0.03966 0.0390 0.1355 1.0000
14.000 1.2155 0.04981 0.04339 0.0388 0.1287 1.0000
14.250 1.2121 0.05259 0.04614 0.0390 0.1206 1.0000
14.500 1.2079 0.05545 0.04898 0.0389 0.1127 1.0000
14.750 1.1973 0.05933 0.05302 0.0383 0.1069 1.0000
15.000 1.2011 0.06154 0.05507 0.0386 0.0983 1.0000
15.250 1.1849 0.06630 0.06011 0.0371 0.0951 1.0000
15.500 1.1924 0.06820 0.06182 0.0377 0.0868 1.0000
15.750 1.1738 0.07352 0.06744 0.0357 0.0846 1.0000
16.000 1.1583 0.07871 0.07286 0.0337 0.0817 1.0000
16.250 1.1671 0.08058 0.07456 0.0342 0.0748 1.0000
16.500 1.1465 0.08678 0.08103 0.0313 0.0734 1.0000
16.750 1.1253 0.09348 0.08798 0.0281 0.0721 1.0000
17.000 1.1022 0.10087 0.09559 0.0244 0.0714 1.0000
17.250 1.0718 0.11007 0.10501 0.0196 0.0723 1.0000
17.500 1.0328 0.12159 0.11670 0.0131 0.0740 1.0000
17.750 0.9929 0.13429 0.12949 0.0063 0.0757 1.0000
18.000 0.8385 0.18850 0.18322 -0.0203 0.0991 1.0000
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Polar data table (+)
Polar graphs
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