GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 200,000 Max Cl/Cd: 44.35 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe780-il-200000.txt Download as CSV file: xf-goe780-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4805 0.09207 0.08874 -0.0518 1.0000 0.0375
-10.000 -0.4883 0.08719 0.08392 -0.0546 1.0000 0.0378
-9.750 -0.5016 0.08187 0.07865 -0.0583 1.0000 0.0380
-9.500 -0.5179 0.07778 0.07457 -0.0595 1.0000 0.0378
-9.250 -0.5390 0.07494 0.07178 -0.0578 1.0000 0.0377
-9.000 -0.5698 0.07430 0.07120 -0.0525 0.9972 0.0372
-8.750 -0.5719 0.06963 0.06637 -0.0552 0.9873 0.0381
-8.500 -0.5704 0.06508 0.06161 -0.0568 0.9782 0.0397
-8.250 -0.5667 0.06319 0.05913 -0.0565 0.9697 0.0423
-8.000 -0.5623 0.06070 0.05628 -0.0551 0.9618 0.0426
-7.750 -0.5620 0.05288 0.04823 -0.0552 0.9572 0.0437
-7.500 -0.5461 0.04802 0.04339 -0.0560 0.9534 0.0454
-7.250 -0.5338 0.04518 0.04040 -0.0550 0.9470 0.0470
-7.000 -0.5176 0.04219 0.03713 -0.0543 0.9429 0.0501
-5.750 -0.4350 0.02639 0.01903 -0.0416 0.9177 0.0339
-5.500 -0.4035 0.02422 0.01654 -0.0422 0.9154 0.0351
-5.250 -0.3658 0.02173 0.01368 -0.0435 0.9129 0.0344
-5.000 -0.3304 0.02002 0.01182 -0.0450 0.9098 0.0371
-4.750 -0.3007 0.01924 0.01088 -0.0454 0.9066 0.0420
-4.500 -0.2679 0.01718 0.00883 -0.0468 0.9044 0.0491
-4.250 -0.2475 0.01616 0.00773 -0.0455 0.9014 0.0577
-4.000 -0.2388 0.01564 0.00727 -0.0419 0.8957 0.0731
-3.750 -0.2217 0.01519 0.00690 -0.0400 0.8916 0.1015
-3.500 -0.2243 0.01361 0.00638 -0.0346 0.8878 0.3324
-3.250 -0.1551 0.01328 0.00802 -0.0405 0.8893 0.8512
-3.000 -0.1042 0.01432 0.00885 -0.0440 0.8885 0.8679
-2.750 -0.0527 0.01516 0.00951 -0.0480 0.8876 0.8806
-2.500 0.0047 0.01604 0.01022 -0.0532 0.8866 0.8936
-2.250 0.0446 0.01652 0.01062 -0.0555 0.8840 0.9050
-2.000 0.0994 0.01707 0.01108 -0.0606 0.8829 0.9178
-1.750 0.1555 0.01716 0.01109 -0.0666 0.8816 0.9240
-1.500 0.1840 0.01722 0.01111 -0.0672 0.8783 0.9320
-1.250 0.2256 0.01709 0.01094 -0.0706 0.8762 0.9360
-1.000 0.2526 0.01721 0.01103 -0.0709 0.8739 0.9442
-0.750 0.2945 0.01705 0.01090 -0.0745 0.8712 0.9486
-0.500 0.3218 0.01707 0.01094 -0.0752 0.8676 0.9543
-0.250 0.3520 0.01700 0.01088 -0.0764 0.8644 0.9591
0.000 0.3878 0.01672 0.01060 -0.0784 0.8600 0.9626
0.250 0.4110 0.01679 0.01076 -0.0781 0.8536 0.9689
0.500 0.4459 0.01642 0.01041 -0.0797 0.8474 0.9726
0.750 0.4772 0.01622 0.01029 -0.0810 0.8404 0.9772
1.000 0.5014 0.01593 0.01000 -0.0798 0.8252 0.9830
1.250 0.5356 0.01508 0.00912 -0.0803 0.8054 0.9862
1.500 0.5638 0.01430 0.00832 -0.0796 0.7775 0.9913
1.750 0.5916 0.01334 0.00735 -0.0787 0.7346 0.9968
2.000 0.5887 0.01367 0.00630 -0.0715 0.4221 1.0000
2.250 0.5744 0.01629 0.00730 -0.0644 0.0581 1.0000
2.500 0.5894 0.01673 0.00774 -0.0622 0.0423 1.0000
2.750 0.6036 0.01725 0.00832 -0.0597 0.0362 1.0000
3.000 0.6137 0.01810 0.00931 -0.0565 0.0337 1.0000
3.250 0.6251 0.01885 0.01013 -0.0535 0.0330 1.0000
3.500 0.6360 0.01978 0.01112 -0.0503 0.0326 1.0000
3.750 0.6500 0.02058 0.01197 -0.0477 0.0301 1.0000
4.000 0.6658 0.02150 0.01294 -0.0455 0.0283 1.0000
4.250 0.6875 0.02298 0.01449 -0.0439 0.0290 1.0000
4.500 0.7173 0.02512 0.01679 -0.0434 0.0310 1.0000
7.000 0.8731 0.05536 0.04964 -0.0190 0.0457 1.0000
7.250 0.8738 0.05280 0.04768 -0.0122 0.0405 1.0000
7.500 0.8745 0.05509 0.05011 -0.0086 0.0380 1.0000
7.750 0.8752 0.05778 0.05285 -0.0056 0.0364 1.0000
8.000 0.8767 0.06142 0.05649 -0.0032 0.0354 1.0000
8.250 0.8617 0.06984 0.06493 -0.0002 0.0342 1.0000
8.500 0.8513 0.07156 0.06686 0.0050 0.0341 1.0000
8.750 0.8361 0.07195 0.06750 0.0114 0.0338 1.0000
9.000 0.8163 0.07200 0.06779 0.0184 0.0331 1.0000
9.250 0.7966 0.07317 0.06911 0.0246 0.0326 1.0000
9.500 0.7742 0.07489 0.07088 0.0306 0.0327 1.0000
9.750 0.7480 0.07628 0.07236 0.0364 0.0323 1.0000
10.000 0.7260 0.07867 0.07482 0.0401 0.0322 1.0000
10.250 0.7123 0.08209 0.07826 0.0421 0.0330 1.0000
10.500 0.6895 0.08516 0.08140 0.0440 0.0328 1.0000
10.750 0.6651 0.08906 0.08538 0.0444 0.0324 1.0000
11.000 0.6499 0.09346 0.08981 0.0441 0.0327 1.0000
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Polar data table (+)
Polar graphs
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