GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 200,000 Max Cl/Cd: 73.88 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe329-il-200000.txt Download as CSV file: xf-goe329-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2672 0.10367 0.10035 -0.0342 1.0000 0.0317
-8.500 -0.2849 0.10346 0.10023 -0.0298 1.0000 0.0319
-8.250 -0.3032 0.10325 0.10009 -0.0255 1.0000 0.0320
-8.000 -0.2839 0.09919 0.09603 -0.0306 0.9959 0.0329
-7.750 -0.2626 0.09495 0.09177 -0.0368 0.9904 0.0340
-7.500 -0.2373 0.09069 0.08749 -0.0495 0.9809 0.0358
-7.250 -0.2007 0.08484 0.08155 -0.0680 0.9721 0.0364
-7.000 -0.1828 0.08018 0.07690 -0.0658 0.9707 0.0369
-6.750 -0.1634 0.07658 0.07330 -0.0677 0.9644 0.0376
-6.500 -0.1357 0.07257 0.06925 -0.0733 0.9598 0.0387
-6.250 -0.1057 0.06845 0.06508 -0.0803 0.9549 0.0402
-6.000 -0.0753 0.06451 0.06104 -0.0881 0.9463 0.0424
-5.750 -0.0344 0.05917 0.05546 -0.0998 0.9395 0.0443
-5.500 -0.0188 0.05624 0.05256 -0.0996 0.9316 0.0451
-5.250 0.0064 0.05323 0.04950 -0.1019 0.9263 0.0464
-5.000 0.0279 0.05060 0.04678 -0.1037 0.9163 0.0482
-4.750 0.0781 0.04861 0.04415 -0.1114 0.9088 0.0529
-4.500 0.0922 0.04402 0.03966 -0.1116 0.8998 0.0539
-4.250 0.1112 0.04153 0.03718 -0.1116 0.8922 0.0551
-4.000 0.1330 0.03950 0.03508 -0.1119 0.8830 0.0573
-3.750 0.1716 0.03809 0.03306 -0.1144 0.8747 0.0646
-3.500 0.1902 0.03487 0.02994 -0.1145 0.8659 0.0662
-3.250 0.2127 0.03305 0.02808 -0.1145 0.8565 0.0687
-2.750 0.2687 0.02941 0.02395 -0.1156 0.8378 0.0798
-2.500 0.2939 0.02793 0.02239 -0.1156 0.8288 0.0846
-2.250 0.3225 0.02636 0.02055 -0.1159 0.8184 0.0944
-2.000 0.3506 0.02544 0.01936 -0.1161 0.8072 0.1079
-1.750 0.3755 0.02387 0.01780 -0.1160 0.7965 0.1155
-1.500 0.4028 0.02292 0.01662 -0.1162 0.7850 0.1402
-1.250 0.4279 0.02166 0.01539 -0.1162 0.7717 0.1600
-1.000 0.4535 0.02062 0.01429 -0.1163 0.7577 0.1915
-0.250 0.4439 0.03683 0.03250 -0.1408 0.7160 0.1493
0.000 0.5816 0.01669 0.00860 -0.1132 0.6934 0.0774
0.250 0.6090 0.01549 0.00728 -0.1128 0.6738 0.0714
0.500 0.6361 0.01500 0.00662 -0.1123 0.6517 0.0701
0.750 0.6630 0.01464 0.00609 -0.1117 0.6305 0.0695
1.000 0.6898 0.01437 0.00566 -0.1112 0.6097 0.0671
1.250 0.7165 0.01421 0.00538 -0.1108 0.5902 0.0661
1.500 0.7431 0.01410 0.00516 -0.1105 0.5726 0.0661
1.750 0.7700 0.01402 0.00501 -0.1104 0.5565 0.0670
2.000 0.7969 0.01404 0.00493 -0.1102 0.5418 0.0689
2.250 0.8239 0.01414 0.00492 -0.1101 0.5288 0.0732
2.500 0.8510 0.01428 0.00494 -0.1100 0.5176 0.0821
2.750 0.8728 0.01299 0.00522 -0.1092 0.5076 0.7756
3.000 0.8956 0.01287 0.00522 -0.1076 0.4978 1.0000
3.250 0.9225 0.01323 0.00535 -0.1074 0.4890 1.0000
3.500 0.9493 0.01349 0.00556 -0.1073 0.4796 1.0000
3.750 0.9762 0.01385 0.00578 -0.1073 0.4721 1.0000
4.000 1.0030 0.01413 0.00604 -0.1072 0.4642 1.0000
4.250 1.0301 0.01453 0.00630 -0.1072 0.4579 1.0000
4.500 1.0566 0.01480 0.00662 -0.1071 0.4506 1.0000
4.750 1.0834 0.01515 0.00689 -0.1071 0.4443 1.0000
5.000 1.1100 0.01551 0.00725 -0.1071 0.4382 1.0000
5.250 1.1365 0.01584 0.00761 -0.1070 0.4324 1.0000
5.500 1.1637 0.01626 0.00796 -0.1071 0.4275 1.0000
5.750 1.1898 0.01662 0.00839 -0.1070 0.4221 1.0000
6.000 1.2161 0.01697 0.00879 -0.1069 0.4167 1.0000
6.250 1.2431 0.01740 0.00918 -0.1070 0.4122 1.0000
6.500 1.2690 0.01782 0.00970 -0.1069 0.4076 1.0000
6.750 1.2946 0.01819 0.01017 -0.1067 0.4025 1.0000
7.000 1.3208 0.01856 0.01047 -0.1066 0.3963 1.0000
7.250 1.3435 0.01876 0.01083 -0.1059 0.3877 1.0000
7.500 1.3677 0.01902 0.01103 -0.1054 0.3791 1.0000
7.750 1.3894 0.01916 0.01133 -0.1045 0.3698 1.0000
8.000 1.4121 0.01942 0.01162 -0.1038 0.3614 1.0000
8.250 1.4333 0.01958 0.01185 -0.1028 0.3517 1.0000
8.500 1.4536 0.01979 0.01219 -0.1017 0.3414 1.0000
8.750 1.4721 0.01996 0.01246 -0.1003 0.3285 1.0000
9.000 1.4894 0.02016 0.01276 -0.0986 0.3134 1.0000
9.250 1.5017 0.02047 0.01307 -0.0962 0.2871 1.0000
9.500 1.5041 0.02143 0.01378 -0.0924 0.2218 1.0000
9.750 1.4782 0.02442 0.01597 -0.0852 0.1139 1.0000
10.000 1.4586 0.02756 0.01874 -0.0797 0.0634 1.0000
10.250 1.4544 0.02979 0.02093 -0.0764 0.0486 1.0000
10.500 1.4527 0.03197 0.02318 -0.0737 0.0436 1.0000
10.750 1.4537 0.03404 0.02541 -0.0717 0.0409 1.0000
11.000 1.4517 0.03649 0.02799 -0.0697 0.0389 1.0000
11.250 1.4456 0.03947 0.03110 -0.0679 0.0374 1.0000
11.500 1.4350 0.04309 0.03486 -0.0664 0.0363 1.0000
11.750 1.4293 0.04641 0.03832 -0.0654 0.0354 1.0000
12.000 1.4242 0.04981 0.04187 -0.0647 0.0345 1.0000
12.250 1.4179 0.05348 0.04567 -0.0642 0.0335 1.0000
12.500 1.4111 0.05734 0.04965 -0.0639 0.0328 1.0000
12.750 1.4040 0.06131 0.05372 -0.0637 0.0321 1.0000
13.000 1.3978 0.06525 0.05776 -0.0636 0.0315 1.0000
13.250 1.3926 0.06905 0.06164 -0.0635 0.0310 1.0000
13.500 1.3886 0.07260 0.06524 -0.0631 0.0304 1.0000
13.750 1.3871 0.07560 0.06826 -0.0623 0.0298 1.0000
14.000 1.3921 0.07711 0.06973 -0.0599 0.0291 1.0000
14.250 1.3990 0.07909 0.07179 -0.0588 0.0287 1.0000
14.500 1.4052 0.08132 0.07414 -0.0582 0.0281 1.0000
14.750 1.4114 0.08355 0.07649 -0.0575 0.0274 1.0000
15.000 1.4186 0.08562 0.07866 -0.0566 0.0267 1.0000
15.250 1.4276 0.08739 0.08054 -0.0554 0.0262 1.0000
15.500 1.4369 0.08921 0.08247 -0.0542 0.0259 1.0000
15.750 1.4454 0.09123 0.08463 -0.0531 0.0256 1.0000
16.000 1.4523 0.09361 0.08717 -0.0522 0.0254 1.0000
16.250 1.4565 0.09651 0.09026 -0.0517 0.0254 1.0000
16.500 1.4567 0.10011 0.09408 -0.0517 0.0254 1.0000
16.750 1.4535 0.10424 0.09844 -0.0522 0.0254 1.0000
17.000 1.4471 0.10889 0.10332 -0.0534 0.0255 1.0000
17.250 1.4386 0.11397 0.10862 -0.0550 0.0254 1.0000
17.500 1.4273 0.11964 0.11454 -0.0573 0.0255 1.0000
17.750 1.4134 0.12599 0.12113 -0.0603 0.0257 1.0000
18.000 1.3981 0.13282 0.12821 -0.0639 0.0259 1.0000
18.250 1.3808 0.14033 0.13596 -0.0681 0.0262 1.0000
18.500 1.3625 0.14833 0.14419 -0.0731 0.0265 1.0000
18.750 1.3432 0.15703 0.15310 -0.0787 0.0270 1.0000
19.000 1.3237 0.16617 0.16243 -0.0849 0.0275 1.0000
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Polar data table (+)
Polar graphs
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