EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 331 AIRFOIL (e331-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.07 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e331-il-1000000.txt Download as CSV file: xf-e331-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 331 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4701 0.08432 0.08281 -0.0112 1.0000 0.0067
-8.750 -0.4767 0.07907 0.07759 -0.0160 1.0000 0.0067
-8.500 -0.4856 0.07472 0.07322 -0.0185 1.0000 0.0067
-8.250 -0.4982 0.07073 0.06920 -0.0187 1.0000 0.0067
-8.000 -0.5089 0.06752 0.06595 -0.0171 1.0000 0.0067
-7.750 -0.5134 0.06375 0.06212 -0.0162 1.0000 0.0067
-7.500 -0.4951 0.05759 0.05556 -0.0207 0.8692 0.0067
-7.250 -0.4965 0.05441 0.05206 -0.0182 0.8089 0.0067
-7.000 -0.5070 0.04986 0.04726 -0.0154 0.7775 0.0069
-6.750 -0.5014 0.04716 0.04435 -0.0135 0.7507 0.0070
-6.500 -0.4930 0.04455 0.04155 -0.0117 0.7287 0.0071
-6.000 -0.4709 0.03935 0.03594 -0.0079 0.6905 0.0073
-5.750 -0.4581 0.03660 0.03297 -0.0059 0.6749 0.0076
-5.500 -0.4442 0.03370 0.02983 -0.0036 0.6605 0.0079
-5.250 -0.4292 0.03050 0.02635 -0.0010 0.6471 0.0083
-5.000 -0.4112 0.02629 0.02154 0.0032 0.6354 0.0091
-4.750 -0.3996 0.02254 0.01748 0.0057 0.6233 0.0095
-4.500 -0.3785 0.02133 0.01612 0.0068 0.6096 0.0097
-4.250 -0.3565 0.02004 0.01462 0.0080 0.5967 0.0102
-4.000 -0.3319 0.01416 0.00778 0.0116 0.5876 0.0069
-3.750 -0.3063 0.01307 0.00654 0.0122 0.5756 0.0071
-3.500 -0.2807 0.01263 0.00606 0.0127 0.5632 0.0076
-3.000 -0.2299 0.01150 0.00474 0.0140 0.5408 0.0079
-2.750 -0.2049 0.01106 0.00421 0.0147 0.5304 0.0082
-2.250 -0.1534 0.01056 0.00358 0.0159 0.5093 0.0090
-2.000 -0.1293 0.01012 0.00307 0.0168 0.5001 0.0092
-1.750 -0.1048 0.00975 0.00264 0.0176 0.4908 0.0095
-1.500 -0.0794 0.00949 0.00233 0.0183 0.4821 0.0099
-1.000 -0.0296 0.00891 0.00180 0.0198 0.4650 0.0463
-0.750 -0.0062 0.00856 0.00169 0.0206 0.4569 0.1295
-0.500 0.0040 0.00721 0.00147 0.0237 0.4507 0.4757
-0.250 -0.0006 0.00574 0.00141 0.0307 0.4449 0.8573
0.000 0.0212 0.00602 0.00175 0.0328 0.4380 0.9140
0.250 0.0478 0.00640 0.00212 0.0338 0.4307 0.9308
0.500 0.0779 0.00673 0.00238 0.0338 0.4236 0.9386
0.750 0.1146 0.00712 0.00271 0.0325 0.4159 0.9455
1.000 0.1683 0.00757 0.00307 0.0273 0.4078 0.9480
1.250 0.2168 0.00782 0.00324 0.0230 0.3999 0.9492
1.500 0.2467 0.00788 0.00324 0.0226 0.3938 0.9505
1.750 0.2740 0.00790 0.00323 0.0227 0.3882 0.9522
2.000 0.2775 0.00789 0.00319 0.0279 0.3839 0.9577
2.250 0.3094 0.00792 0.00317 0.0270 0.3780 0.9581
2.500 0.3415 0.00794 0.00317 0.0260 0.3724 0.9585
2.750 0.3726 0.00800 0.00317 0.0252 0.3665 0.9589
3.000 0.4033 0.00803 0.00318 0.0245 0.3617 0.9594
3.250 0.4341 0.00806 0.00319 0.0237 0.3561 0.9599
3.500 0.4642 0.00814 0.00323 0.0231 0.3503 0.9605
3.750 0.4937 0.00817 0.00325 0.0227 0.3455 0.9611
4.000 0.5231 0.00822 0.00329 0.0222 0.3402 0.9618
4.250 0.5519 0.00832 0.00334 0.0219 0.3342 0.9626
4.500 0.5803 0.00834 0.00339 0.0216 0.3296 0.9634
4.750 0.6073 0.00840 0.00343 0.0216 0.3241 0.9644
5.000 0.6332 0.00848 0.00350 0.0219 0.3187 0.9654
5.250 0.6591 0.00852 0.00356 0.0222 0.3137 0.9668
5.500 0.6794 0.00859 0.00362 0.0236 0.3084 0.9688
5.750 0.6921 0.00865 0.00367 0.0268 0.3036 0.9714
6.000 0.7222 0.00869 0.00373 0.0261 0.2978 0.9718
6.250 0.7516 0.00881 0.00383 0.0255 0.2905 0.9722
6.500 0.7815 0.00887 0.00392 0.0248 0.2850 0.9726
6.750 0.8113 0.00900 0.00403 0.0241 0.2771 0.9731
7.000 0.8412 0.00910 0.00416 0.0234 0.2702 0.9736
7.250 0.8699 0.00925 0.00430 0.0229 0.2621 0.9742
7.500 0.8982 0.00937 0.00444 0.0225 0.2543 0.9749
7.750 0.9256 0.00955 0.00460 0.0223 0.2452 0.9756
8.000 0.9528 0.00971 0.00477 0.0221 0.2358 0.9764
8.250 0.9793 0.00990 0.00496 0.0220 0.2259 0.9774
8.500 1.0046 0.01014 0.00518 0.0221 0.2140 0.9785
8.750 1.0285 0.01040 0.00542 0.0225 0.2019 0.9798
9.000 1.0493 0.01069 0.00568 0.0235 0.1890 0.9816
9.250 1.0683 0.01102 0.00597 0.0249 0.1747 0.9836
9.500 1.0962 0.01145 0.00634 0.0242 0.1556 0.9842
9.750 1.1228 0.01196 0.00678 0.0236 0.1371 0.9849
10.000 1.1484 0.01252 0.00726 0.0232 0.1181 0.9857
10.250 1.1720 0.01326 0.00788 0.0230 0.0960 0.9867
10.500 1.1955 0.01393 0.00847 0.0228 0.0791 0.9879
10.750 1.2183 0.01458 0.00908 0.0228 0.0667 0.9893
11.000 1.2382 0.01539 0.00980 0.0231 0.0527 0.9911
11.250 1.2579 0.01606 0.01045 0.0237 0.0445 0.9930
11.500 1.2789 0.01681 0.01118 0.0237 0.0364 0.9944
11.750 1.3029 0.01755 0.01193 0.0231 0.0307 0.9955
12.000 1.3256 0.01837 0.01277 0.0226 0.0254 0.9970
12.250 1.3477 0.01925 0.01366 0.0221 0.0214 0.9986
12.500 1.3682 0.02018 0.01463 0.0217 0.0184 1.0000
12.750 1.3435 0.02053 0.01505 0.0306 0.0181 1.0000
13.000 1.3249 0.02120 0.01576 0.0374 0.0174 1.0000
13.250 1.3166 0.02247 0.01706 0.0411 0.0156 1.0000
13.500 1.3160 0.02396 0.01864 0.0428 0.0148 1.0000
13.750 1.3153 0.02586 0.02059 0.0438 0.0132 1.0000
14.000 1.3142 0.02810 0.02290 0.0442 0.0119 1.0000
14.250 1.3148 0.03040 0.02528 0.0441 0.0109 1.0000
14.500 1.3115 0.03324 0.02818 0.0439 0.0098 1.0000
14.750 1.3080 0.03622 0.03126 0.0434 0.0094 1.0000
15.000 1.3050 0.03920 0.03432 0.0429 0.0087 1.0000
15.250 1.2990 0.04256 0.03777 0.0422 0.0082 1.0000
15.500 1.2918 0.04612 0.04141 0.0414 0.0079 1.0000
15.750 1.2815 0.05009 0.04546 0.0404 0.0074 1.0000
16.000 1.2757 0.05354 0.04899 0.0395 0.0067 1.0000
16.250 1.2666 0.05748 0.05301 0.0384 0.0064 1.0000
16.500 1.2574 0.06157 0.05718 0.0371 0.0059 1.0000
16.750 1.2459 0.06612 0.06182 0.0356 0.0055 1.0000
17.000 1.2367 0.07041 0.06616 0.0341 0.0046 1.0000
17.250 1.2246 0.07520 0.07109 0.0325 0.0054 1.0000
17.500 1.2201 0.07897 0.07492 0.0312 0.0048 1.0000
17.750 1.2088 0.08377 0.07980 0.0294 0.0045 1.0000
18.000 1.2000 0.08830 0.08441 0.0277 0.0042 1.0000
18.250 1.1873 0.09349 0.08968 0.0257 0.0040 1.0000
18.500 1.1780 0.09820 0.09446 0.0239 0.0034 1.0000
18.750 1.1672 0.10326 0.09963 0.0218 0.0038 1.0000
19.000 1.1584 0.10807 0.10450 0.0199 0.0033 1.0000
19.250 1.1484 0.11313 0.10965 0.0177 0.0033 1.0000
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Polar data table (+)
Polar graphs
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