GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 50,000 Max Cl/Cd: 19.49 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe780-il-50000-n5.txt Download as CSV file: xf-goe780-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4764 0.10772 0.10099 -0.0483 1.0000 0.0474
-10.500 -0.4796 0.10291 0.09627 -0.0500 1.0000 0.0444
-10.000 -0.5006 0.09180 0.08528 -0.0583 1.0000 0.0388
-9.750 -0.5062 0.08795 0.08148 -0.0584 1.0000 0.0379
-9.500 -0.5164 0.08441 0.07798 -0.0583 1.0000 0.0373
-9.250 -0.5291 0.08145 0.07504 -0.0573 1.0000 0.0367
-9.000 -0.5481 0.07863 0.07226 -0.0548 1.0000 0.0362
-8.750 -0.5686 0.07673 0.07042 -0.0507 1.0000 0.0359
-8.500 -0.5925 0.07550 0.06924 -0.0452 1.0000 0.0356
-8.250 -0.6167 0.07425 0.06801 -0.0393 1.0000 0.0354
-8.000 -0.6386 0.07296 0.06669 -0.0336 1.0000 0.0350
-7.750 -0.6587 0.07131 0.06498 -0.0280 1.0000 0.0346
-7.500 -0.6760 0.06937 0.06294 -0.0227 1.0000 0.0343
-7.250 -0.6789 0.06597 0.05925 -0.0204 0.9954 0.0332
-7.000 -0.6765 0.06168 0.05450 -0.0185 0.9883 0.0320
-6.500 -0.6606 0.05496 0.04666 -0.0141 0.9760 0.0303
-6.250 -0.6509 0.05167 0.04295 -0.0118 0.9705 0.0302
-5.750 -0.6242 0.04586 0.03653 -0.0087 0.9610 0.0332
-5.500 -0.6054 0.04335 0.03347 -0.0074 0.9568 0.0346
-5.250 -0.5797 0.04054 0.03008 -0.0067 0.9538 0.0359
-5.000 -0.5569 0.03824 0.02729 -0.0054 0.9500 0.0368
-4.750 -0.5241 0.03597 0.02442 -0.0055 0.9471 0.0392
-4.500 -0.4829 0.03347 0.02176 -0.0080 0.9457 0.0473
-4.250 -0.4303 0.03120 0.01923 -0.0121 0.9457 0.0585
-4.000 -0.3982 0.02974 0.01753 -0.0130 0.9433 0.0742
-3.750 -0.3019 0.02606 0.01752 -0.0224 0.9517 0.7988
-3.500 -0.1750 0.02968 0.01992 -0.0350 0.9603 0.9537
-3.250 -0.1006 0.02943 0.01905 -0.0449 0.9616 0.9796
-3.000 -0.0540 0.02900 0.01819 -0.0501 0.9593 0.9900
-2.750 -0.0114 0.02860 0.01749 -0.0547 0.9569 0.9977
-2.500 0.0217 0.02837 0.01702 -0.0573 0.9538 1.0000
-2.250 0.0397 0.02829 0.01675 -0.0568 0.9475 1.0000
-2.000 0.0646 0.02820 0.01651 -0.0576 0.9429 1.0000
-1.750 0.0902 0.02814 0.01632 -0.0585 0.9389 1.0000
-1.500 0.1066 0.02818 0.01626 -0.0575 0.9330 1.0000
-1.250 0.1312 0.02819 0.01617 -0.0582 0.9288 1.0000
-1.000 0.1535 0.02825 0.01616 -0.0583 0.9246 1.0000
-0.750 0.1687 0.02840 0.01627 -0.0570 0.9190 1.0000
-0.500 0.1927 0.02849 0.01633 -0.0574 0.9151 1.0000
-0.250 0.2132 0.02865 0.01648 -0.0571 0.9109 1.0000
0.000 0.2256 0.02890 0.01674 -0.0552 0.9053 1.0000
0.250 0.2486 0.02908 0.01695 -0.0552 0.9015 1.0000
0.500 0.2724 0.02928 0.01722 -0.0555 0.8980 1.0000
0.750 0.2789 0.02967 0.01765 -0.0524 0.8918 1.0000
1.000 0.2997 0.02994 0.01801 -0.0519 0.8879 1.0000
1.250 0.3263 0.03018 0.01837 -0.0526 0.8850 1.0000
1.500 0.3273 0.03069 0.01894 -0.0484 0.8783 1.0000
1.750 0.3468 0.03104 0.01948 -0.0477 0.8743 1.0000
2.000 0.3721 0.03137 0.02001 -0.0481 0.8714 1.0000
2.250 0.3714 0.03195 0.02067 -0.0436 0.8644 1.0000
2.500 0.3906 0.03237 0.02132 -0.0428 0.8605 1.0000
2.750 0.4108 0.03283 0.02207 -0.0421 0.8570 1.0000
3.000 0.4128 0.03344 0.02284 -0.0382 0.8503 1.0000
3.250 0.4502 0.03360 0.02345 -0.0402 0.8445 1.0000
3.500 0.5329 0.02734 0.01422 -0.0326 0.0791 1.0000
3.750 0.5356 0.02848 0.01541 -0.0282 0.0615 1.0000
4.000 0.5397 0.02945 0.01645 -0.0242 0.0521 1.0000
4.250 0.5439 0.03039 0.01752 -0.0202 0.0460 1.0000
4.500 0.5465 0.03151 0.01868 -0.0159 0.0433 1.0000
4.750 0.5538 0.03257 0.01996 -0.0121 0.0410 1.0000
5.000 0.5703 0.03359 0.02116 -0.0097 0.0378 1.0000
5.250 0.6415 0.03543 0.02332 -0.0151 0.0324 1.0000
5.500 0.7046 0.03819 0.02645 -0.0193 0.0316 1.0000
5.750 0.7365 0.04081 0.02944 -0.0190 0.0315 1.0000
6.000 0.7594 0.04330 0.03232 -0.0175 0.0311 1.0000
6.250 0.7765 0.04577 0.03518 -0.0152 0.0307 1.0000
6.500 0.7894 0.04839 0.03820 -0.0124 0.0301 1.0000
6.750 0.7991 0.05093 0.04110 -0.0093 0.0300 1.0000
7.000 0.8055 0.05362 0.04416 -0.0057 0.0299 1.0000
7.250 0.8093 0.05648 0.04736 -0.0020 0.0306 1.0000
7.500 0.8105 0.05934 0.05052 0.0019 0.0313 1.0000
7.750 0.8099 0.06215 0.05358 0.0057 0.0320 1.0000
8.000 0.8070 0.06506 0.05680 0.0096 0.0327 1.0000
8.250 0.8034 0.06804 0.05995 0.0133 0.0334 1.0000
8.500 0.8045 0.07193 0.06386 0.0157 0.0343 1.0000
8.750 0.7852 0.07322 0.06563 0.0223 0.0361 1.0000
9.000 0.7676 0.07599 0.06859 0.0273 0.0374 1.0000
9.250 0.7498 0.07839 0.07109 0.0319 0.0381 1.0000
9.500 0.7309 0.08065 0.07343 0.0362 0.0387 1.0000
9.750 0.7106 0.08350 0.07634 0.0396 0.0392 1.0000
10.000 0.6930 0.08661 0.07951 0.0418 0.0400 1.0000
10.250 0.6762 0.09012 0.08305 0.0431 0.0405 1.0000
10.500 0.6630 0.09406 0.08700 0.0438 0.0414 1.0000
10.750 0.6594 0.09793 0.09093 0.0442 0.0446 1.0000
11.000 0.6336 0.10294 0.09597 0.0422 0.0457 1.0000
11.250 0.6163 0.10879 0.10169 0.0390 0.0471 1.0000
11.500 0.6069 0.11466 0.10750 0.0358 0.0491 1.0000
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