GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 200,000 Max Cl/Cd: 75.6 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe79-il-200000-n5.txt Download as CSV file: xf-goe79-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 79 (PFALZ 11) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2890 0.09897 0.09542 -0.0144 1.0000 0.0233
-7.750 -0.2833 0.09651 0.09300 -0.0152 1.0000 0.0237
-7.500 -0.2783 0.09418 0.09072 -0.0160 1.0000 0.0240
-7.250 -0.2705 0.09174 0.08832 -0.0179 1.0000 0.0243
-7.000 -0.2619 0.08945 0.08608 -0.0204 1.0000 0.0245
-6.750 -0.2468 0.08718 0.08383 -0.0260 0.9973 0.0246
-6.500 -0.2237 0.08288 0.07954 -0.0298 0.9869 0.0247
-6.000 -0.1755 0.07532 0.07195 -0.0379 0.9542 0.0253
-5.750 -0.1448 0.07167 0.06825 -0.0439 0.9371 0.0258
-5.500 -0.1121 0.06806 0.06458 -0.0502 0.9214 0.0264
-5.250 -0.0791 0.06466 0.06109 -0.0562 0.9056 0.0273
-5.000 -0.0351 0.06158 0.05784 -0.0655 0.8889 0.0281
-4.750 0.0055 0.05863 0.05470 -0.0729 0.8726 0.0282
-4.500 0.0257 0.05544 0.05146 -0.0740 0.8571 0.0284
-4.250 0.0451 0.05259 0.04857 -0.0748 0.8422 0.0286
-4.000 0.0698 0.05004 0.04592 -0.0768 0.8266 0.0291
-3.750 0.0975 0.04761 0.04337 -0.0793 0.8094 0.0296
-3.500 0.1271 0.04527 0.04089 -0.0820 0.7908 0.0306
-3.250 0.1663 0.04316 0.03853 -0.0860 0.7718 0.0322
-3.000 0.2093 0.04123 0.03626 -0.0901 0.7540 0.0325
-2.750 0.2340 0.03861 0.03354 -0.0913 0.7366 0.0327
-2.500 0.2578 0.03639 0.03122 -0.0922 0.7191 0.0332
-2.250 0.2858 0.03452 0.02920 -0.0934 0.7015 0.0338
-2.000 0.3161 0.03280 0.02728 -0.0948 0.6848 0.0348
-1.750 0.3486 0.03120 0.02546 -0.0963 0.6698 0.0363
-1.500 0.3867 0.02973 0.02363 -0.0979 0.6574 0.0379
-1.250 0.4131 0.02800 0.02184 -0.0988 0.6446 0.0387
-1.000 0.4427 0.02666 0.02033 -0.0996 0.6329 0.0398
-0.750 0.4738 0.02546 0.01892 -0.1003 0.6218 0.0416
-0.500 0.5099 0.02464 0.01770 -0.1008 0.6107 0.0436
-0.250 0.5370 0.02306 0.01609 -0.1016 0.5999 0.0445
0.250 0.5983 0.02135 0.01392 -0.1022 0.5772 0.0503
0.500 0.6260 0.02031 0.01283 -0.1027 0.5660 0.0527
0.750 0.6553 0.01960 0.01195 -0.1029 0.5541 0.0594
1.000 0.6842 0.01896 0.01117 -0.1031 0.5410 0.0677
1.250 0.7125 0.01840 0.01048 -0.1032 0.5261 0.0774
1.500 0.7403 0.01792 0.00988 -0.1033 0.5088 0.0902
1.750 0.7728 0.01713 0.00861 -0.1021 0.4921 0.0491
2.000 0.8011 0.01643 0.00774 -0.1018 0.4711 0.0412
2.250 0.8290 0.01602 0.00708 -0.1014 0.4467 0.0387
2.500 0.8559 0.01579 0.00668 -0.1011 0.4197 0.0391
2.750 0.8825 0.01568 0.00641 -0.1008 0.3939 0.0408
3.000 0.9089 0.01559 0.00614 -0.1004 0.3721 0.0404
3.250 0.9352 0.01555 0.00598 -0.1000 0.3544 0.0400
3.500 0.9615 0.01557 0.00590 -0.0997 0.3389 0.0399
3.750 0.9877 0.01561 0.00588 -0.0993 0.3250 0.0402
4.000 1.0139 0.01570 0.00592 -0.0990 0.3133 0.0408
4.250 1.0400 0.01586 0.00604 -0.0987 0.3037 0.0431
4.500 1.0665 0.01592 0.00612 -0.0985 0.2955 0.0449
4.750 1.0926 0.01611 0.00626 -0.0982 0.2875 0.0461
5.000 1.1187 0.01631 0.00644 -0.0979 0.2807 0.0477
5.250 1.1446 0.01652 0.00664 -0.0975 0.2740 0.0502
5.750 1.1949 0.01607 0.00729 -0.0968 0.2619 0.7867
6.250 1.2433 0.01648 0.00781 -0.0953 0.2490 1.0000
6.500 1.2686 0.01678 0.00812 -0.0949 0.2420 1.0000
6.750 1.2931 0.01718 0.00848 -0.0944 0.2347 1.0000
7.000 1.3183 0.01748 0.00884 -0.0939 0.2276 1.0000
7.250 1.3424 0.01788 0.00922 -0.0934 0.2198 1.0000
7.500 1.3671 0.01822 0.00962 -0.0929 0.2113 1.0000
7.750 1.3906 0.01865 0.01006 -0.0924 0.2006 1.0000
8.000 1.4138 0.01911 0.01051 -0.0917 0.1874 1.0000
8.250 1.4365 0.01961 0.01100 -0.0910 0.1727 1.0000
8.500 1.4580 0.02022 0.01158 -0.0902 0.1507 1.0000
8.750 1.4764 0.02115 0.01233 -0.0891 0.1211 1.0000
9.000 1.4940 0.02215 0.01321 -0.0879 0.1060 1.0000
9.250 1.5123 0.02301 0.01407 -0.0867 0.1001 1.0000
9.500 1.5293 0.02394 0.01504 -0.0854 0.0954 1.0000
9.750 1.5464 0.02480 0.01597 -0.0840 0.0923 1.0000
10.000 1.5626 0.02568 0.01695 -0.0826 0.0898 1.0000
10.250 1.5767 0.02667 0.01802 -0.0809 0.0874 1.0000
10.500 1.5879 0.02781 0.01924 -0.0788 0.0851 1.0000
10.750 1.5942 0.02917 0.02064 -0.0762 0.0826 1.0000
11.000 1.6033 0.03017 0.02176 -0.0738 0.0806 1.0000
11.250 1.6119 0.03127 0.02300 -0.0716 0.0781 1.0000
11.500 1.6184 0.03259 0.02445 -0.0695 0.0754 1.0000
11.750 1.6213 0.03430 0.02622 -0.0674 0.0729 1.0000
12.000 1.6202 0.03649 0.02846 -0.0653 0.0707 1.0000
12.250 1.6293 0.03792 0.03006 -0.0642 0.0689 1.0000
12.500 1.6366 0.03959 0.03190 -0.0632 0.0667 1.0000
12.750 1.6418 0.04152 0.03398 -0.0623 0.0645 1.0000
13.000 1.6452 0.04373 0.03631 -0.0616 0.0625 1.0000
13.250 1.6449 0.04643 0.03909 -0.0610 0.0607 1.0000
13.500 1.6481 0.04887 0.04169 -0.0607 0.0588 1.0000
13.750 1.6522 0.05129 0.04430 -0.0605 0.0564 1.0000
14.000 1.6538 0.05407 0.04723 -0.0605 0.0540 1.0000
14.250 1.6523 0.05733 0.05061 -0.0609 0.0521 1.0000
14.500 1.6499 0.06079 0.05419 -0.0612 0.0502 1.0000
14.750 1.6484 0.06416 0.05774 -0.0616 0.0477 1.0000
15.000 1.6440 0.06803 0.06174 -0.0624 0.0455 1.0000
15.250 1.6360 0.07251 0.06632 -0.0634 0.0437 1.0000
15.500 1.6285 0.07695 0.07090 -0.0644 0.0418 1.0000
15.750 1.6202 0.08167 0.07577 -0.0657 0.0398 1.0000
16.000 1.6095 0.08693 0.08115 -0.0673 0.0381 1.0000
16.250 1.5965 0.09270 0.08702 -0.0693 0.0368 1.0000
16.500 1.5849 0.09829 0.09274 -0.0712 0.0353 1.0000
16.750 1.5739 0.10391 0.09851 -0.0732 0.0338 1.0000
17.000 1.5617 0.10989 0.10460 -0.0756 0.0325 1.0000
17.250 1.5484 0.11614 0.11095 -0.0782 0.0314 1.0000
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Polar data table (+)
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