EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 331 AIRFOIL (e331-il) Reynolds number: 50,000 Max Cl/Cd: 27.09 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e331-il-50000-n5.txt Download as CSV file: xf-e331-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4652 0.10340 0.09709 -0.0034 1.0000 0.1113
-8.750 -0.4664 0.09964 0.09342 -0.0055 1.0000 0.1134
-8.250 -0.4983 0.09235 0.08634 -0.0123 1.0000 0.1206
-8.000 -0.4944 0.08845 0.08249 -0.0122 1.0000 0.1216
-7.750 -0.4921 0.07880 0.07253 -0.0165 1.0000 0.0496
-7.500 -0.4924 0.07504 0.06876 -0.0161 1.0000 0.0474
-7.250 -0.5071 0.07043 0.06380 -0.0157 1.0000 0.0424
-7.000 -0.4984 0.06699 0.06038 -0.0148 1.0000 0.0414
-6.750 -0.4936 0.06366 0.05700 -0.0136 1.0000 0.0404
-6.500 -0.4890 0.06036 0.05358 -0.0122 1.0000 0.0394
-6.250 -0.4837 0.05708 0.05015 -0.0105 1.0000 0.0384
-6.000 -0.4777 0.05385 0.04671 -0.0085 1.0000 0.0374
-5.750 -0.4707 0.05081 0.04344 -0.0062 1.0000 0.0369
-5.500 -0.4629 0.04810 0.04049 -0.0038 1.0000 0.0368
-5.250 -0.4556 0.04572 0.03793 -0.0011 1.0000 0.0371
-5.000 -0.4505 0.04370 0.03573 0.0019 1.0000 0.0374
-4.750 -0.4155 0.04043 0.03198 -0.0003 0.9666 0.0381
-4.500 -0.3782 0.03730 0.02830 -0.0023 0.9368 0.0390
-4.250 -0.3372 0.03433 0.02475 -0.0043 0.9116 0.0394
-4.000 -0.2964 0.03177 0.02169 -0.0060 0.8864 0.0399
-3.750 -0.2544 0.02958 0.01894 -0.0074 0.8627 0.0419
-3.500 -0.2165 0.02787 0.01706 -0.0087 0.8381 0.0462
-3.250 -0.1733 0.02634 0.01514 -0.0100 0.8158 0.0513
-3.000 -0.1368 0.02511 0.01376 -0.0108 0.7933 0.0594
-2.500 0.0924 0.02080 0.01183 -0.0355 0.7493 1.0000
-2.250 0.1133 0.02079 0.01140 -0.0343 0.7289 1.0000
-2.000 0.1346 0.02079 0.01103 -0.0332 0.7108 1.0000
-1.750 0.1561 0.02080 0.01071 -0.0322 0.6940 1.0000
-1.500 0.1780 0.02083 0.01043 -0.0312 0.6783 1.0000
-1.250 0.2002 0.02088 0.01022 -0.0303 0.6635 1.0000
-1.000 0.2226 0.02095 0.01004 -0.0295 0.6495 1.0000
-0.750 0.2452 0.02103 0.00990 -0.0287 0.6362 1.0000
-0.500 0.2678 0.02113 0.00980 -0.0279 0.6240 1.0000
-0.250 0.2905 0.02123 0.00970 -0.0270 0.6130 1.0000
0.000 0.3134 0.02136 0.00970 -0.0263 0.6010 1.0000
0.250 0.3365 0.02152 0.00972 -0.0257 0.5899 1.0000
0.500 0.3594 0.02167 0.00972 -0.0248 0.5803 1.0000
0.750 0.3823 0.02186 0.00982 -0.0241 0.5698 1.0000
1.000 0.4051 0.02207 0.00995 -0.0234 0.5601 1.0000
1.250 0.4277 0.02227 0.01003 -0.0225 0.5516 1.0000
1.500 0.4510 0.02254 0.01029 -0.0221 0.5418 1.0000
1.750 0.4740 0.02276 0.01040 -0.0212 0.5340 1.0000
2.000 0.4969 0.02309 0.01074 -0.0207 0.5246 1.0000
2.250 0.5196 0.02337 0.01096 -0.0199 0.5171 1.0000
2.500 0.5420 0.02372 0.01133 -0.0192 0.5083 1.0000
2.750 0.5644 0.02405 0.01165 -0.0184 0.5011 1.0000
3.000 0.5864 0.02445 0.01209 -0.0176 0.4927 1.0000
3.250 0.6085 0.02480 0.01241 -0.0167 0.4858 1.0000
3.500 0.6301 0.02527 0.01295 -0.0160 0.4776 1.0000
3.750 0.6521 0.02562 0.01327 -0.0150 0.4714 1.0000
4.000 0.6728 0.02620 0.01401 -0.0143 0.4629 1.0000
4.250 0.6950 0.02651 0.01429 -0.0132 0.4571 1.0000
4.500 0.7146 0.02723 0.01518 -0.0124 0.4486 1.0000
4.750 0.7363 0.02758 0.01553 -0.0113 0.4425 1.0000
5.000 0.7552 0.02834 0.01650 -0.0104 0.4345 1.0000
5.250 0.7761 0.02878 0.01698 -0.0093 0.4281 1.0000
5.500 0.7945 0.02953 0.01789 -0.0083 0.4204 1.0000
5.750 0.8144 0.03007 0.01855 -0.0071 0.4136 1.0000
6.000 0.8326 0.03078 0.01940 -0.0059 0.4065 1.0000
6.250 0.8508 0.03144 0.02019 -0.0046 0.3990 1.0000
6.500 0.8692 0.03208 0.02095 -0.0033 0.3923 1.0000
6.750 0.8852 0.03291 0.02198 -0.0019 0.3843 1.0000
7.000 0.9037 0.03345 0.02263 -0.0005 0.3777 1.0000
7.250 0.9173 0.03443 0.02382 0.0011 0.3693 1.0000
7.750 0.9471 0.03597 0.02571 0.0044 0.3538 1.0000
8.000 0.9624 0.03664 0.02652 0.0061 0.3463 1.0000
8.250 0.9746 0.03751 0.02757 0.0080 0.3379 1.0000
8.500 0.9847 0.03849 0.02874 0.0100 0.3296 1.0000
8.750 1.0006 0.03891 0.02931 0.0119 0.3216 1.0000
9.000 1.0026 0.04040 0.03102 0.0144 0.3126 1.0000
9.250 1.0276 0.03996 0.03064 0.0159 0.3048 1.0000
9.500 1.0172 0.04224 0.03317 0.0191 0.2953 1.0000
9.750 1.0294 0.04265 0.03373 0.0213 0.2868 1.0000
10.000 1.0317 0.04372 0.03494 0.0240 0.2778 1.0000
10.250 1.0214 0.04573 0.03709 0.0271 0.2697 1.0000
10.500 1.0460 0.04492 0.03635 0.0289 0.2601 1.0000
10.750 0.9940 0.04994 0.04144 0.0333 0.2548 1.0000
11.000 1.0194 0.04888 0.04047 0.0352 0.2451 1.0000
11.250 0.9331 0.05998 0.05150 0.0338 0.2395 1.0000
11.500 0.9771 0.05630 0.04800 0.0370 0.2303 1.0000
11.750 0.9033 0.06876 0.06035 0.0325 0.2217 1.0000
12.000 0.8809 0.07486 0.06644 0.0307 0.2126 1.0000
12.250 0.9263 0.06996 0.06178 0.0346 0.2049 1.0000
12.500 0.8582 0.08411 0.07575 0.0284 0.1948 1.0000
12.750 0.8958 0.08017 0.07204 0.0318 0.1881 1.0000
13.000 0.8555 0.09031 0.08209 0.0276 0.1789 1.0000
13.250 0.8347 0.09737 0.08912 0.0250 0.1706 1.0000
13.500 0.8564 0.09605 0.08798 0.0268 0.1639 1.0000
13.750 0.8166 0.10741 0.09921 0.0218 0.1557 1.0000
14.000 0.8555 0.10230 0.09438 0.0255 0.1495 1.0000
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Polar data table (+)
Polar graphs
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