EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.14 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e639-il-1000000-n5.txt Download as CSV file: xf-e639-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 639 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2062 0.08420 0.08094 -0.0546 0.5708 0.0064
-9.000 -0.2065 0.08056 0.07729 -0.0561 0.5629 0.0066
-8.750 -0.2116 0.07607 0.07280 -0.0581 0.5571 0.0070
-8.500 -0.2216 0.07119 0.06796 -0.0606 0.5535 0.0071
-8.000 -0.2497 0.06255 0.05932 -0.0644 0.5428 0.0074
-7.750 -0.2472 0.05950 0.05622 -0.0655 0.5359 0.0075
-7.500 -0.2395 0.05714 0.05380 -0.0661 0.5291 0.0076
-7.250 -0.2354 0.05348 0.05006 -0.0667 0.5235 0.0077
-7.000 -0.2282 0.05007 0.04655 -0.0670 0.5174 0.0078
-6.750 -0.2173 0.04726 0.04364 -0.0669 0.5116 0.0080
-6.500 -0.2055 0.04431 0.04056 -0.0666 0.5051 0.0083
-6.000 -0.1835 0.03664 0.03251 -0.0647 0.4939 0.0087
-5.750 -0.1726 0.03216 0.02776 -0.0628 0.4887 0.0089
-5.500 -0.1864 0.01837 0.01271 -0.0555 0.4887 0.0101
-5.250 -0.1640 0.01726 0.01139 -0.0546 0.4818 0.0102
-5.000 -0.1396 0.01665 0.01065 -0.0540 0.4746 0.0104
-4.750 -0.1152 0.01597 0.00983 -0.0533 0.4684 0.0105
-4.500 -0.0901 0.01531 0.00903 -0.0528 0.4629 0.0107
-4.250 -0.0650 0.01463 0.00820 -0.0522 0.4569 0.0109
-4.000 -0.0397 0.01394 0.00736 -0.0516 0.4515 0.0111
-3.750 -0.0139 0.01336 0.00667 -0.0511 0.4457 0.0113
-3.500 0.0119 0.01280 0.00597 -0.0505 0.4399 0.0115
-3.250 0.0381 0.01239 0.00547 -0.0501 0.4355 0.0119
-3.000 0.0644 0.01198 0.00499 -0.0497 0.4308 0.0122
-2.750 0.0903 0.01157 0.00449 -0.0491 0.4261 0.0124
-2.500 0.1164 0.01124 0.00409 -0.0487 0.4219 0.0127
-2.250 0.1427 0.01096 0.00376 -0.0482 0.4175 0.0129
-2.000 0.1692 0.01080 0.00354 -0.0479 0.4127 0.0131
-1.500 0.2201 0.01015 0.00282 -0.0467 0.4053 0.0138
-1.250 0.2464 0.00998 0.00263 -0.0464 0.4016 0.0141
-1.000 0.2729 0.00985 0.00247 -0.0460 0.3975 0.0145
-0.750 0.2992 0.00974 0.00233 -0.0456 0.3933 0.0149
-0.500 0.3260 0.00963 0.00221 -0.0453 0.3901 0.0154
-0.250 0.3529 0.00955 0.00211 -0.0451 0.3866 0.0161
0.000 0.3797 0.00948 0.00202 -0.0448 0.3832 0.0166
0.250 0.4064 0.00944 0.00195 -0.0445 0.3797 0.0170
0.500 0.4332 0.00936 0.00185 -0.0442 0.3767 0.0179
0.750 0.4602 0.00932 0.00179 -0.0440 0.3733 0.0190
1.000 0.4873 0.00930 0.00176 -0.0438 0.3701 0.0202
1.250 0.5143 0.00930 0.00174 -0.0436 0.3670 0.0218
1.500 0.5404 0.00923 0.00176 -0.0433 0.3640 0.0606
1.750 0.5506 0.00768 0.00180 -0.0404 0.3621 0.6653
2.000 0.5668 0.00704 0.00197 -0.0374 0.3595 0.9294
2.250 0.6076 0.00719 0.00212 -0.0401 0.3561 0.9608
2.500 0.6371 0.00731 0.00220 -0.0404 0.3530 0.9713
2.750 0.6872 0.00753 0.00236 -0.0452 0.3496 0.9806
3.000 0.7181 0.00762 0.00243 -0.0459 0.3471 0.9840
3.250 0.7506 0.00770 0.00248 -0.0470 0.3445 0.9848
3.500 0.7826 0.00778 0.00254 -0.0480 0.3414 0.9857
3.750 0.8142 0.00787 0.00260 -0.0489 0.3387 0.9868
4.000 0.8453 0.00798 0.00268 -0.0498 0.3357 0.9881
4.250 0.8761 0.00807 0.00276 -0.0506 0.3331 0.9894
4.500 0.9065 0.00815 0.00284 -0.0513 0.3307 0.9909
4.750 0.9363 0.00825 0.00294 -0.0518 0.3280 0.9924
5.000 0.9653 0.00836 0.00304 -0.0523 0.3252 0.9938
5.250 0.9959 0.00847 0.00314 -0.0531 0.3221 0.9948
5.500 1.0270 0.00859 0.00325 -0.0540 0.3191 0.9957
5.750 1.0581 0.00867 0.00335 -0.0549 0.3167 0.9968
6.000 1.0886 0.00878 0.00346 -0.0557 0.3133 0.9978
6.250 1.1188 0.00891 0.00359 -0.0565 0.3093 0.9989
6.500 1.1489 0.00906 0.00373 -0.0573 0.3054 0.9998
6.750 1.1739 0.00917 0.00386 -0.0569 0.3018 1.0000
7.000 1.1962 0.00930 0.00400 -0.0560 0.2976 1.0000
7.250 1.2176 0.00948 0.00417 -0.0549 0.2926 1.0000
7.500 1.2398 0.00961 0.00433 -0.0540 0.2885 1.0000
7.750 1.2617 0.00977 0.00449 -0.0530 0.2837 1.0000
8.000 1.2829 0.00996 0.00468 -0.0519 0.2791 1.0000
8.250 1.3045 0.01012 0.00487 -0.0509 0.2748 1.0000
8.500 1.3260 0.01029 0.00506 -0.0499 0.2698 1.0000
8.750 1.3460 0.01054 0.00529 -0.0487 0.2626 1.0000
9.000 1.3650 0.01085 0.00556 -0.0473 0.2504 1.0000
9.250 1.3848 0.01111 0.00582 -0.0460 0.2411 1.0000
9.500 1.4020 0.01150 0.00615 -0.0444 0.2269 1.0000
9.750 1.4188 0.01191 0.00651 -0.0427 0.2137 1.0000
10.000 1.4335 0.01242 0.00695 -0.0407 0.1976 1.0000
10.250 1.4456 0.01303 0.00748 -0.0383 0.1792 1.0000
10.750 1.4569 0.01475 0.00893 -0.0315 0.1324 1.0000
11.000 1.4591 0.01548 0.00959 -0.0275 0.1180 1.0000
11.250 1.4620 0.01625 0.01031 -0.0237 0.1054 1.0000
11.500 1.4658 0.01707 0.01110 -0.0204 0.0941 1.0000
11.750 1.4699 0.01797 0.01198 -0.0175 0.0843 1.0000
12.000 1.4660 0.01938 0.01333 -0.0141 0.0704 1.0000
12.250 1.4648 0.02087 0.01481 -0.0115 0.0605 1.0000
12.500 1.4672 0.02237 0.01633 -0.0099 0.0541 1.0000
12.750 1.4673 0.02425 0.01823 -0.0085 0.0483 1.0000
13.000 1.4636 0.02669 0.02069 -0.0076 0.0410 1.0000
13.250 1.4596 0.02941 0.02343 -0.0070 0.0343 1.0000
13.500 1.4528 0.03257 0.02662 -0.0067 0.0283 1.0000
13.750 1.4486 0.03559 0.02969 -0.0067 0.0251 1.0000
14.000 1.4408 0.03904 0.03320 -0.0067 0.0213 1.0000
14.250 1.4232 0.04362 0.03782 -0.0069 0.0156 1.0000
14.500 1.4185 0.04684 0.04112 -0.0070 0.0145 1.0000
14.750 1.4098 0.05054 0.04488 -0.0073 0.0126 1.0000
15.000 1.3873 0.05594 0.05033 -0.0079 0.0070 1.0000
15.250 1.3756 0.06025 0.05470 -0.0085 0.0053 1.0000
15.500 1.3634 0.06469 0.05921 -0.0091 0.0040 1.0000
15.750 1.3626 0.06775 0.06235 -0.0096 0.0044 1.0000
16.000 1.3517 0.07216 0.06683 -0.0104 0.0034 1.0000
16.250 1.3462 0.07589 0.07064 -0.0111 0.0032 1.0000
16.500 1.3402 0.07978 0.07459 -0.0119 0.0031 1.0000
16.750 1.3365 0.08340 0.07829 -0.0127 0.0031 1.0000
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Polar data table (+)
Polar graphs
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