EPPLER 638 AIRFOIL (e638-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 638 AIRFOIL (e638-il) Reynolds number: 50,000 Max Cl/Cd: 25.27 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e638-il-50000-n5.txt Download as CSV file: xf-e638-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 638 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3033 0.10157 0.09557 -0.0239 1.0000 0.1087
-8.500 -0.3110 0.09924 0.09338 -0.0265 1.0000 0.1132
-8.250 -0.3333 0.09758 0.09191 -0.0307 1.0000 0.1148
-8.000 -0.3103 0.09259 0.08699 -0.0280 1.0000 0.1190
-7.750 -0.3076 0.08971 0.08423 -0.0279 1.0000 0.1239
-7.500 -0.3195 0.08748 0.08219 -0.0286 1.0000 0.1273
-7.250 -0.3532 0.08710 0.08197 -0.0308 1.0000 0.1306
-7.000 -0.3182 0.08103 0.07601 -0.0316 0.9714 0.1360
-6.750 -0.3058 0.07694 0.07177 -0.0403 0.9198 0.1479
-6.500 -0.2733 0.07183 0.06660 -0.0428 0.8925 0.1536
-6.000 -0.2307 0.05835 0.05168 -0.0538 0.8429 0.0564
-5.750 -0.2126 0.05469 0.04789 -0.0539 0.8215 0.0549
-5.500 -0.1978 0.05166 0.04457 -0.0533 0.8010 0.0538
-5.250 -0.1828 0.04892 0.04146 -0.0524 0.7828 0.0538
-5.000 -0.1671 0.04635 0.03844 -0.0511 0.7662 0.0544
-4.750 -0.1501 0.04393 0.03558 -0.0497 0.7508 0.0548
-4.500 -0.1320 0.04160 0.03282 -0.0482 0.7363 0.0546
-4.250 -0.1125 0.03935 0.03013 -0.0467 0.7227 0.0542
-4.000 -0.0914 0.03729 0.02760 -0.0453 0.7102 0.0542
-3.750 -0.0685 0.03553 0.02528 -0.0438 0.6986 0.0556
-3.500 -0.0457 0.03381 0.02319 -0.0427 0.6860 0.0579
-3.250 -0.0213 0.03227 0.02142 -0.0419 0.6741 0.0599
-3.000 0.0055 0.03086 0.01965 -0.0411 0.6636 0.0612
-2.750 0.0334 0.02968 0.01816 -0.0405 0.6532 0.0644
-2.500 0.0626 0.02873 0.01688 -0.0400 0.6423 0.0689
-2.250 0.0959 0.02758 0.01554 -0.0403 0.6326 0.0721
-2.000 0.1281 0.02673 0.01451 -0.0406 0.6230 0.0769
-1.750 0.1565 0.02621 0.01377 -0.0403 0.6135 0.0851
-1.500 0.1822 0.02555 0.01301 -0.0397 0.6058 0.0934
-1.250 0.3280 0.02148 0.01164 -0.0597 0.5919 1.0000
-1.000 0.3504 0.02169 0.01146 -0.0588 0.5836 1.0000
-0.750 0.3729 0.02188 0.01130 -0.0578 0.5763 1.0000
-0.500 0.3948 0.02214 0.01132 -0.0569 0.5684 1.0000
-0.250 0.4170 0.02238 0.01130 -0.0560 0.5616 1.0000
0.000 0.4388 0.02268 0.01138 -0.0551 0.5547 1.0000
0.250 0.4605 0.02299 0.01151 -0.0542 0.5478 1.0000
0.500 0.4828 0.02327 0.01156 -0.0532 0.5423 1.0000
0.750 0.5034 0.02370 0.01191 -0.0522 0.5350 1.0000
1.000 0.5256 0.02401 0.01203 -0.0512 0.5297 1.0000
1.250 0.5462 0.02448 0.01241 -0.0503 0.5234 1.0000
1.500 0.5671 0.02491 0.01275 -0.0493 0.5175 1.0000
1.750 0.5898 0.02522 0.01288 -0.0483 0.5130 1.0000
2.000 0.6085 0.02588 0.01355 -0.0473 0.5065 1.0000
2.250 0.6294 0.02634 0.01393 -0.0462 0.5013 1.0000
2.500 0.6523 0.02667 0.01412 -0.0453 0.4973 1.0000
2.750 0.6690 0.02751 0.01502 -0.0441 0.4907 1.0000
3.000 0.6895 0.02803 0.01550 -0.0430 0.4859 1.0000
3.250 0.7125 0.02840 0.01576 -0.0421 0.4822 1.0000
3.500 0.7271 0.02941 0.01688 -0.0408 0.4759 1.0000
3.750 0.7465 0.03005 0.01750 -0.0397 0.4711 1.0000
4.000 0.7692 0.03044 0.01782 -0.0388 0.4675 1.0000
4.500 0.7990 0.03245 0.02000 -0.0360 0.4568 1.0000
4.750 0.8209 0.03293 0.02044 -0.0351 0.4531 1.0000
5.000 0.8337 0.03411 0.02170 -0.0336 0.4480 1.0000
5.250 0.8454 0.03535 0.02307 -0.0320 0.4426 1.0000
5.500 0.8655 0.03596 0.02368 -0.0309 0.4388 1.0000
5.750 0.8821 0.03687 0.02463 -0.0297 0.4348 1.0000
6.000 0.8829 0.03890 0.02682 -0.0274 0.4283 1.0000
6.250 0.9004 0.03973 0.02769 -0.0263 0.4243 1.0000
6.500 0.9260 0.04001 0.02799 -0.0256 0.4215 1.0000
6.750 0.9042 0.04368 0.03187 -0.0223 0.4132 1.0000
7.000 0.9215 0.04451 0.03276 -0.0211 0.4092 1.0000
7.250 0.9488 0.04467 0.03294 -0.0206 0.4065 1.0000
7.500 0.8986 0.05055 0.03897 -0.0165 0.3962 1.0000
7.750 0.9233 0.05081 0.03928 -0.0157 0.3931 1.0000
8.250 0.8783 0.05916 0.04771 -0.0122 0.3781 1.0000
8.500 0.8355 0.06667 0.05523 -0.0130 0.3664 1.0000
8.750 0.8569 0.06714 0.05580 -0.0121 0.3631 1.0000
9.250 0.8454 0.07418 0.06293 -0.0121 0.3490 1.0000
9.750 0.8390 0.08079 0.06965 -0.0122 0.3354 1.0000
10.000 0.8651 0.08073 0.06968 -0.0111 0.3325 1.0000
10.250 0.8376 0.08696 0.07594 -0.0125 0.3221 1.0000
10.500 0.8607 0.08724 0.07632 -0.0116 0.3186 1.0000
10.750 0.8406 0.09270 0.08182 -0.0128 0.3090 1.0000
11.000 0.8593 0.09351 0.08277 -0.0121 0.3048 1.0000
11.250 0.8462 0.09825 0.08756 -0.0132 0.2960 1.0000
11.500 0.8621 0.09933 0.08875 -0.0126 0.2910 1.0000
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Polar data table (+)
Polar graphs
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