GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 200,000 Max Cl/Cd: 73.5 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe279-il-200000-n5.txt Download as CSV file: xf-goe279-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 279 (DAIMLER X) 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 -0.3231 0.09736 0.09398 -0.0251 1.0000 0.0197
-7.750 -0.3322 0.09593 0.09262 -0.0226 1.0000 0.0199
-7.500 -0.3345 0.09382 0.09056 -0.0223 0.9983 0.0201
-7.250 -0.3171 0.08985 0.08660 -0.0274 0.9936 0.0206
-7.000 -0.2953 0.08555 0.08229 -0.0338 0.9885 0.0212
-6.750 -0.2712 0.08120 0.07791 -0.0409 0.9831 0.0220
-6.500 -0.2380 0.07645 0.07311 -0.0516 0.9776 0.0229
-6.250 -0.2071 0.07188 0.06847 -0.0605 0.9714 0.0231
-6.000 -0.1739 0.06707 0.06356 -0.0685 0.9673 0.0232
-5.750 -0.1394 0.06234 0.05871 -0.0758 0.9632 0.0233
-5.500 -0.1070 0.05794 0.05416 -0.0814 0.9576 0.0234
-5.250 -0.0749 0.05344 0.04953 -0.0861 0.9541 0.0234
-5.000 -0.0483 0.04917 0.04518 -0.0893 0.9499 0.0233
-4.750 -0.0320 0.04596 0.04199 -0.0901 0.9439 0.0220
-4.500 0.0018 0.04183 0.03768 -0.0942 0.9401 0.0209
-4.250 0.0390 0.03786 0.03347 -0.0983 0.9373 0.0211
-4.000 0.0719 0.03412 0.02939 -0.1002 0.9307 0.0228
-3.750 0.1058 0.03048 0.02542 -0.1022 0.9263 0.0229
-3.500 0.1424 0.02672 0.02120 -0.1043 0.9228 0.0239
-3.250 0.1664 0.02608 0.02059 -0.1046 0.9145 0.0257
-3.000 0.1999 0.02398 0.01818 -0.1057 0.9085 0.0278
-2.750 0.2305 0.02171 0.01551 -0.1058 0.9003 0.0288
-2.500 0.2632 0.01981 0.01314 -0.1063 0.8934 0.0320
-2.250 0.2907 0.01863 0.01182 -0.1063 0.8840 0.0332
-2.000 0.3205 0.01752 0.01049 -0.1064 0.8751 0.0347
-1.750 0.3493 0.01670 0.00945 -0.1062 0.8643 0.0378
-1.500 0.3775 0.01579 0.00830 -0.1058 0.8528 0.0388
-1.250 0.4059 0.01509 0.00740 -0.1055 0.8423 0.0398
-1.000 0.4341 0.01445 0.00660 -0.1052 0.8318 0.0419
-0.750 0.4616 0.01376 0.00584 -0.1049 0.8197 0.0428
-0.500 0.4888 0.01324 0.00527 -0.1045 0.8058 0.0436
-0.250 0.5159 0.01281 0.00480 -0.1042 0.7907 0.0446
0.000 0.5430 0.01246 0.00441 -0.1038 0.7733 0.0459
0.250 0.5697 0.01223 0.00413 -0.1033 0.7508 0.0487
0.500 0.5964 0.01200 0.00382 -0.1029 0.7230 0.0500
0.750 0.6228 0.01185 0.00353 -0.1023 0.6903 0.0509
1.000 0.6486 0.01183 0.00331 -0.1016 0.6569 0.0519
1.250 0.6740 0.01188 0.00313 -0.1010 0.6253 0.0537
1.500 0.6994 0.01200 0.00306 -0.1004 0.5967 0.0567
1.750 0.7250 0.01215 0.00306 -0.0999 0.5709 0.0608
2.000 0.7507 0.01229 0.00310 -0.0994 0.5474 0.0727
2.250 0.7695 0.01060 0.00327 -0.0976 0.5259 1.0000
2.500 0.7948 0.01089 0.00335 -0.0970 0.4996 1.0000
2.750 0.8197 0.01120 0.00347 -0.0965 0.4711 1.0000
3.000 0.8447 0.01151 0.00362 -0.0959 0.4438 1.0000
3.250 0.8695 0.01183 0.00379 -0.0954 0.4188 1.0000
3.500 0.8939 0.01219 0.00399 -0.0949 0.3944 1.0000
3.750 0.9184 0.01256 0.00423 -0.0943 0.3727 1.0000
4.000 0.9431 0.01291 0.00447 -0.0938 0.3558 1.0000
4.250 0.9675 0.01328 0.00474 -0.0933 0.3392 1.0000
4.500 0.9920 0.01365 0.00504 -0.0928 0.3233 1.0000
4.750 1.0166 0.01400 0.00533 -0.0923 0.3095 1.0000
5.000 1.0413 0.01433 0.00562 -0.0919 0.2970 1.0000
5.250 1.0660 0.01466 0.00595 -0.0914 0.2868 1.0000
5.500 1.0906 0.01500 0.00627 -0.0910 0.2755 1.0000
5.750 1.1152 0.01532 0.00660 -0.0905 0.2623 1.0000
6.000 1.1395 0.01566 0.00695 -0.0900 0.2492 1.0000
6.250 1.1636 0.01602 0.00732 -0.0895 0.2367 1.0000
6.500 1.1873 0.01639 0.00771 -0.0889 0.2232 1.0000
6.750 1.2107 0.01680 0.00812 -0.0883 0.2083 1.0000
7.000 1.2335 0.01725 0.00857 -0.0876 0.1923 1.0000
7.250 1.2557 0.01775 0.00906 -0.0869 0.1764 1.0000
7.750 1.2975 0.01897 0.01019 -0.0851 0.1448 1.0000
8.000 1.3183 0.01956 0.01080 -0.0841 0.1345 1.0000
8.250 1.3388 0.02017 0.01147 -0.0831 0.1255 1.0000
8.500 1.3580 0.02087 0.01218 -0.0820 0.1153 1.0000
8.750 1.3775 0.02152 0.01289 -0.0809 0.1047 1.0000
9.000 1.3968 0.02217 0.01361 -0.0797 0.0917 1.0000
9.250 1.4134 0.02302 0.01445 -0.0782 0.0691 1.0000
9.500 1.4270 0.02411 0.01544 -0.0764 0.0571 1.0000
9.750 1.4406 0.02510 0.01648 -0.0745 0.0520 1.0000
10.000 1.4507 0.02620 0.01763 -0.0720 0.0477 1.0000
10.250 1.4599 0.02731 0.01883 -0.0695 0.0444 1.0000
10.500 1.4702 0.02835 0.02003 -0.0672 0.0419 1.0000
10.750 1.4782 0.02958 0.02141 -0.0648 0.0394 1.0000
11.000 1.4828 0.03108 0.02301 -0.0622 0.0370 1.0000
11.250 1.4836 0.03290 0.02495 -0.0594 0.0349 1.0000
11.500 1.4931 0.03412 0.02636 -0.0576 0.0332 1.0000
11.750 1.4995 0.03562 0.02805 -0.0557 0.0312 1.0000
12.000 1.5033 0.03739 0.02997 -0.0539 0.0291 1.0000
12.250 1.5027 0.03964 0.03233 -0.0520 0.0272 1.0000
12.500 1.4965 0.04252 0.03533 -0.0501 0.0256 1.0000
12.750 1.5034 0.04429 0.03732 -0.0491 0.0238 1.0000
13.000 1.5053 0.04663 0.03986 -0.0481 0.0216 1.0000
13.250 1.5057 0.04923 0.04260 -0.0474 0.0199 1.0000
13.750 1.4980 0.05589 0.04955 -0.0469 0.0174 1.0000
14.000 1.4928 0.05969 0.05352 -0.0472 0.0164 1.0000
14.250 1.4865 0.06385 0.05784 -0.0479 0.0156 1.0000
14.500 1.4787 0.06839 0.06253 -0.0490 0.0150 1.0000
14.750 1.4691 0.07342 0.06769 -0.0505 0.0145 1.0000
15.000 1.4573 0.07897 0.07338 -0.0523 0.0141 1.0000
15.250 1.4432 0.08501 0.07955 -0.0545 0.0137 1.0000
15.500 1.4302 0.09100 0.08569 -0.0566 0.0134 1.0000
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Polar data table (+)
Polar graphs
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