EPPLER 637 AIRFOIL (e637-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 637 AIRFOIL (e637-il) Reynolds number: 100,000 Max Cl/Cd: 31.49 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e637-il-100000.txt Download as CSV file: xf-e637-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 637 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3528 0.09652 0.09221 -0.0162 1.0000 0.0793
-8.250 -0.3552 0.09332 0.08909 -0.0189 1.0000 0.0818
-8.000 -0.3677 0.09021 0.08610 -0.0240 1.0000 0.0835
-7.750 -0.3876 0.08787 0.08381 -0.0272 1.0000 0.0842
-7.500 -0.4058 0.08632 0.08217 -0.0294 1.0000 0.0848
-7.250 -0.3821 0.07939 0.07548 -0.0275 1.0000 0.0869
-7.000 -0.3698 0.07622 0.07242 -0.0260 1.0000 0.0899
-6.750 -0.3691 0.07336 0.06965 -0.0261 1.0000 0.0931
-6.500 -0.3783 0.07133 0.06776 -0.0257 0.9979 0.0957
-6.250 -0.3486 0.06529 0.06144 -0.0360 0.9499 0.1022
-6.000 -0.3099 0.06069 0.05677 -0.0407 0.9170 0.1098
-5.750 -0.2566 0.04316 0.03913 -0.0413 0.8206 0.1224
-5.500 -0.2750 0.05409 0.04963 -0.0432 0.8518 0.1259
-5.250 -0.2672 0.05149 0.04673 -0.0421 0.8261 0.1352
-5.000 -0.2584 0.05008 0.04492 -0.0405 0.8048 0.1491
-4.750 -0.2421 0.04696 0.04185 -0.0390 0.7853 0.1563
-4.500 -0.2297 0.04479 0.03951 -0.0374 0.7675 0.1716
-4.250 -0.2165 0.04292 0.03745 -0.0357 0.7513 0.1912
-4.000 -0.2047 0.04080 0.03524 -0.0336 0.7366 0.2189
-3.750 -0.1924 0.03903 0.03342 -0.0312 0.7229 0.2545
-3.500 -0.1818 0.03713 0.03153 -0.0284 0.7094 0.2975
-3.250 -0.1675 0.03517 0.02958 -0.0258 0.6966 0.3321
-3.000 -0.0934 0.03026 0.02179 -0.0269 0.6888 0.0830
-2.750 -0.0667 0.02801 0.01891 -0.0250 0.6777 0.0719
-2.500 -0.0397 0.02650 0.01716 -0.0241 0.6658 0.0693
-2.250 -0.0121 0.02496 0.01536 -0.0233 0.6556 0.0680
-2.000 0.0160 0.02391 0.01403 -0.0225 0.6456 0.0694
-1.750 0.0442 0.02269 0.01272 -0.0221 0.6350 0.0729
-1.500 0.0719 0.02169 0.01166 -0.0215 0.6267 0.0766
-1.250 0.2748 0.01709 0.00973 -0.0506 0.6070 1.0000
-1.000 0.2971 0.01718 0.00954 -0.0497 0.5983 1.0000
-0.750 0.3196 0.01733 0.00946 -0.0488 0.5900 1.0000
-0.500 0.3422 0.01745 0.00937 -0.0480 0.5821 1.0000
-0.250 0.3649 0.01764 0.00940 -0.0472 0.5748 1.0000
0.000 0.3878 0.01782 0.00941 -0.0465 0.5673 1.0000
0.250 0.4107 0.01802 0.00944 -0.0457 0.5609 1.0000
0.500 0.4335 0.01825 0.00960 -0.0450 0.5533 1.0000
0.750 0.4566 0.01845 0.00960 -0.0441 0.5479 1.0000
1.000 0.4792 0.01880 0.00995 -0.0435 0.5408 1.0000
1.250 0.5021 0.01905 0.01008 -0.0427 0.5348 1.0000
1.500 0.5249 0.01936 0.01029 -0.0419 0.5293 1.0000
1.750 0.5470 0.01975 0.01068 -0.0412 0.5225 1.0000
2.000 0.5701 0.02004 0.01086 -0.0404 0.5178 1.0000
2.250 0.5921 0.02050 0.01130 -0.0396 0.5123 1.0000
2.500 0.6140 0.02093 0.01175 -0.0388 0.5061 1.0000
2.750 0.6371 0.02123 0.01194 -0.0380 0.5015 1.0000
3.000 0.6582 0.02183 0.01258 -0.0372 0.4962 1.0000
3.250 0.6793 0.02239 0.01319 -0.0363 0.4907 1.0000
3.500 0.7022 0.02272 0.01344 -0.0354 0.4862 1.0000
3.750 0.7229 0.02336 0.01411 -0.0346 0.4813 1.0000
4.000 0.7425 0.02409 0.01494 -0.0336 0.4755 1.0000
4.250 0.7649 0.02450 0.01533 -0.0327 0.4714 1.0000
4.500 0.7872 0.02500 0.01578 -0.0318 0.4675 1.0000
4.750 0.8027 0.02610 0.01709 -0.0307 0.4610 1.0000
5.000 0.8243 0.02660 0.01759 -0.0297 0.4566 1.0000
5.250 0.8483 0.02696 0.01789 -0.0289 0.4533 1.0000
5.500 0.8597 0.02847 0.01966 -0.0275 0.4470 1.0000
5.750 0.8788 0.02919 0.02043 -0.0263 0.4421 1.0000
6.000 0.9034 0.02945 0.02063 -0.0255 0.4387 1.0000
6.250 0.9136 0.03110 0.02248 -0.0239 0.4331 1.0000
6.500 0.9271 0.03231 0.02385 -0.0225 0.4275 1.0000
6.750 0.9523 0.03247 0.02399 -0.0217 0.4239 1.0000
7.000 0.9651 0.03386 0.02550 -0.0202 0.4191 1.0000
7.250 0.9670 0.03607 0.02792 -0.0181 0.4124 1.0000
7.500 0.9942 0.03600 0.02785 -0.0174 0.4087 1.0000
7.750 1.0080 0.03723 0.02918 -0.0159 0.4040 1.0000
8.000 0.9952 0.04057 0.03276 -0.0130 0.3963 1.0000
8.250 1.0314 0.03966 0.03182 -0.0127 0.3930 1.0000
8.500 0.9730 0.04696 0.03939 -0.0081 0.3831 1.0000
8.750 1.0093 0.04585 0.03834 -0.0073 0.3792 1.0000
9.000 1.0725 0.04262 0.03508 -0.0081 0.3769 1.0000
9.250 0.8515 0.06613 0.05856 -0.0040 0.3589 1.0000
9.500 1.0229 0.05069 0.04341 -0.0018 0.3622 1.0000
9.750 1.1315 0.04373 0.03644 -0.0043 0.3606 1.0000
10.000 0.7791 0.08303 0.07547 -0.0062 0.3348 1.0000
10.250 0.8365 0.07905 0.07161 -0.0032 0.3313 1.0000
12.000 0.8051 0.10422 0.09708 -0.0060 0.2777 1.0000
12.250 0.8555 0.10012 0.09313 -0.0026 0.2732 1.0000
12.500 1.2673 0.04682 0.04069 0.0166 0.2850 1.0000
12.750 1.3275 0.04284 0.03676 0.0165 0.2731 1.0000
13.250 1.2718 0.04934 0.04348 0.0215 0.2602 1.0000
13.500 1.3447 0.04343 0.03753 0.0228 0.2447 1.0000
13.750 1.2871 0.05044 0.04473 0.0235 0.2410 1.0000
14.000 1.3138 0.04886 0.04313 0.0249 0.2280 1.0000
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Polar data table (+)
Polar graphs
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