GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.45 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe79-il-1000000-n5.txt Download as CSV file: xf-goe79-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3762 0.12190 0.12019 -0.0025 1.0000 0.0091
-10.250 -0.3691 0.11873 0.11703 -0.0038 1.0000 0.0094
-10.000 -0.3656 0.11429 0.11259 -0.0055 1.0000 0.0099
-9.750 -0.3566 0.11189 0.11019 -0.0066 1.0000 0.0100
-9.500 -0.3475 0.10948 0.10779 -0.0077 1.0000 0.0101
-9.250 -0.3384 0.10707 0.10540 -0.0089 1.0000 0.0103
-9.000 -0.3296 0.10456 0.10291 -0.0100 1.0000 0.0106
-8.750 -0.3216 0.10186 0.10022 -0.0112 1.0000 0.0110
-8.500 -0.3103 0.09863 0.09698 -0.0137 0.9756 0.0112
-8.250 -0.2974 0.09376 0.09194 -0.0184 0.9036 0.0119
-8.000 -0.2885 0.09168 0.08975 -0.0192 0.8779 0.0120
-7.750 -0.2788 0.08952 0.08752 -0.0204 0.8593 0.0121
-7.500 -0.2658 0.08700 0.08495 -0.0227 0.8431 0.0122
-7.250 -0.2512 0.08433 0.08222 -0.0254 0.8277 0.0125
-7.000 -0.2352 0.08161 0.07944 -0.0284 0.8128 0.0129
-6.750 -0.2178 0.07848 0.07625 -0.0321 0.7971 0.0134
-6.500 -0.1982 0.07480 0.07250 -0.0367 0.7797 0.0142
-6.250 -0.1789 0.07253 0.07013 -0.0394 0.7577 0.0144
-6.000 -0.1571 0.07013 0.06762 -0.0427 0.7324 0.0159
-5.750 -0.1335 0.06688 0.06425 -0.0471 0.7079 0.0160
-5.500 -0.1082 0.06361 0.06088 -0.0517 0.6865 0.0160
-5.250 -0.0767 0.05974 0.05687 -0.0580 0.6680 0.0162
-4.750 -0.0225 0.05366 0.05059 -0.0657 0.6364 0.0164
-4.250 0.0317 0.04919 0.04597 -0.0714 0.6116 0.0169
-4.000 0.0615 0.04688 0.04356 -0.0746 0.6001 0.0175
-3.750 0.0972 0.04404 0.04059 -0.0787 0.5886 0.0185
-3.500 0.1335 0.04111 0.03753 -0.0828 0.5791 0.0186
-3.250 0.1696 0.03830 0.03456 -0.0864 0.5682 0.0187
-3.000 0.2052 0.03567 0.03179 -0.0894 0.5582 0.0187
-2.750 0.2392 0.03325 0.02922 -0.0918 0.5505 0.0187
-2.500 0.2653 0.03132 0.02724 -0.0931 0.5419 0.0189
-2.250 0.2930 0.02995 0.02579 -0.0943 0.5330 0.0191
-2.000 0.3229 0.02856 0.02432 -0.0956 0.5247 0.0195
-1.750 0.3543 0.02703 0.02267 -0.0969 0.5168 0.0201
-1.500 0.3903 0.02523 0.02067 -0.0982 0.5045 0.0213
-1.250 0.4244 0.02344 0.01867 -0.0993 0.4893 0.0214
-1.000 0.4563 0.02191 0.01693 -0.1001 0.4717 0.0214
-0.750 0.4875 0.02052 0.01536 -0.1008 0.4573 0.0214
-0.500 0.5186 0.01929 0.01392 -0.1013 0.4386 0.0214
-0.250 0.5485 0.01817 0.01256 -0.1019 0.4097 0.0214
0.000 0.5763 0.01736 0.01154 -0.1026 0.3718 0.0211
0.250 0.6056 0.01656 0.01050 -0.1030 0.3443 0.0208
0.500 0.6360 0.01560 0.00930 -0.1032 0.3244 0.0208
0.750 0.6666 0.01461 0.00806 -0.1033 0.3108 0.0211
1.000 0.6966 0.01376 0.00699 -0.1033 0.3003 0.0213
1.500 0.7540 0.01282 0.00580 -0.1035 0.2817 0.0219
1.750 0.7832 0.01217 0.00497 -0.1035 0.2731 0.0218
2.000 0.8116 0.01181 0.00450 -0.1034 0.2657 0.0218
2.250 0.8397 0.01159 0.00423 -0.1034 0.2585 0.0220
2.500 0.8676 0.01146 0.00403 -0.1034 0.2492 0.0223
2.750 0.8955 0.01133 0.00384 -0.1033 0.2419 0.0227
3.000 0.9233 0.01123 0.00368 -0.1032 0.2346 0.0233
3.250 0.9513 0.01112 0.00354 -0.1032 0.2286 0.0237
3.500 0.9789 0.01110 0.00347 -0.1031 0.2211 0.0243
3.750 1.0066 0.01109 0.00344 -0.1030 0.2145 0.0249
4.000 1.0341 0.01114 0.00344 -0.1030 0.2052 0.0252
4.250 1.0616 0.01120 0.00349 -0.1029 0.1981 0.0257
4.500 1.0888 0.01132 0.00357 -0.1028 0.1892 0.0264
4.750 1.1160 0.01143 0.00367 -0.1027 0.1809 0.0272
5.000 1.1428 0.01161 0.00380 -0.1025 0.1701 0.0278
5.250 1.1692 0.01185 0.00397 -0.1023 0.1558 0.0290
5.500 1.1924 0.01259 0.00443 -0.1017 0.1039 0.0302
5.750 1.2176 0.01301 0.00477 -0.1014 0.0885 0.0313
6.000 1.2436 0.01328 0.00502 -0.1011 0.0827 0.0325
6.250 1.2699 0.01347 0.00522 -0.1008 0.0810 0.0348
6.500 1.2962 0.01367 0.00545 -0.1006 0.0796 0.0407
7.000 1.3449 0.01300 0.00621 -0.0997 0.0762 1.0000
7.250 1.3703 0.01331 0.00651 -0.0994 0.0745 1.0000
7.500 1.3956 0.01362 0.00683 -0.0990 0.0727 1.0000
7.750 1.4206 0.01396 0.00718 -0.0986 0.0707 1.0000
8.000 1.4460 0.01422 0.00746 -0.0982 0.0702 1.0000
8.250 1.4713 0.01448 0.00776 -0.0979 0.0697 1.0000
8.500 1.4964 0.01474 0.00805 -0.0975 0.0687 1.0000
8.750 1.5212 0.01503 0.00835 -0.0971 0.0669 1.0000
9.000 1.5455 0.01536 0.00870 -0.0967 0.0648 1.0000
9.250 1.5693 0.01574 0.00908 -0.0962 0.0627 1.0000
9.500 1.5926 0.01616 0.00951 -0.0956 0.0604 1.0000
9.750 1.6166 0.01646 0.00984 -0.0951 0.0593 1.0000
10.000 1.6404 0.01677 0.01019 -0.0946 0.0574 1.0000
10.250 1.6634 0.01715 0.01057 -0.0940 0.0548 1.0000
10.500 1.6855 0.01759 0.01100 -0.0933 0.0520 1.0000
10.750 1.7077 0.01800 0.01144 -0.0926 0.0498 1.0000
11.000 1.7292 0.01845 0.01190 -0.0918 0.0464 1.0000
11.250 1.7495 0.01900 0.01242 -0.0909 0.0425 1.0000
11.500 1.7690 0.01957 0.01300 -0.0898 0.0383 1.0000
11.750 1.7873 0.02021 0.01364 -0.0886 0.0345 1.0000
12.000 1.8037 0.02096 0.01439 -0.0872 0.0302 1.0000
12.250 1.8186 0.02176 0.01519 -0.0855 0.0260 1.0000
12.500 1.8310 0.02266 0.01610 -0.0835 0.0219 1.0000
12.750 1.8404 0.02362 0.01708 -0.0810 0.0187 1.0000
13.000 1.8455 0.02464 0.01814 -0.0779 0.0167 1.0000
13.250 1.8516 0.02570 0.01926 -0.0752 0.0153 1.0000
13.500 1.8566 0.02696 0.02058 -0.0726 0.0142 1.0000
13.750 1.8623 0.02829 0.02199 -0.0705 0.0134 1.0000
14.000 1.8680 0.02976 0.02354 -0.0688 0.0128 1.0000
14.250 1.8723 0.03146 0.02532 -0.0672 0.0122 1.0000
14.500 1.8750 0.03344 0.02738 -0.0659 0.0117 1.0000
14.750 1.8762 0.03570 0.02972 -0.0648 0.0111 1.0000
15.000 1.8769 0.03815 0.03227 -0.0640 0.0107 1.0000
15.250 1.8782 0.04066 0.03488 -0.0634 0.0105 1.0000
15.500 1.8776 0.04349 0.03781 -0.0630 0.0102 1.0000
15.750 1.8754 0.04665 0.04107 -0.0629 0.0099 1.0000
16.000 1.8711 0.05016 0.04470 -0.0630 0.0097 1.0000
16.250 1.8643 0.05407 0.04871 -0.0633 0.0094 1.0000
16.500 1.8553 0.05838 0.05313 -0.0639 0.0092 1.0000
16.750 1.8442 0.06302 0.05789 -0.0645 0.0090 1.0000
17.000 1.8311 0.06807 0.06306 -0.0655 0.0088 1.0000
17.250 1.8163 0.07355 0.06866 -0.0667 0.0086 1.0000
17.500 1.8000 0.07937 0.07460 -0.0682 0.0085 1.0000
17.750 1.7822 0.08559 0.08095 -0.0699 0.0084 1.0000
18.000 1.7630 0.09221 0.08771 -0.0720 0.0083 1.0000
18.250 1.7450 0.09876 0.09438 -0.0742 0.0082 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 79 (PFALZ 11) AIRFOIL (goe79-il)