GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 776 AIRFOIL (goe776-il) Reynolds number: 50,000 Max Cl/Cd: 19.25 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe776-il-50000-n5.txt Download as CSV file: xf-goe776-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 776 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4795 0.10744 0.09714 -0.0420 1.0000 0.2304
-12.000 -0.5135 0.09660 0.08626 -0.0439 1.0000 0.2447
-11.750 -0.4940 0.09671 0.08642 -0.0427 1.0000 0.2472
-11.250 -0.5364 0.08568 0.07537 -0.0435 1.0000 0.2631
-10.750 -0.5955 0.07417 0.06383 -0.0429 1.0000 0.2804
-10.250 -0.6953 0.06136 0.05089 -0.0388 1.0000 0.2982
-10.000 -0.6540 0.06367 0.05335 -0.0375 1.0000 0.3009
-9.750 -0.6526 0.06271 0.05244 -0.0352 1.0000 0.3061
-9.500 -0.8082 0.05175 0.04116 -0.0244 1.0000 0.3161
-9.250 -0.7746 0.05290 0.04248 -0.0237 1.0000 0.3204
-9.000 -0.7939 0.05154 0.04114 -0.0189 1.0000 0.3256
-8.750 -0.8573 0.04868 0.03814 -0.0094 1.0000 0.3307
-8.500 -0.9193 0.04664 0.03595 0.0014 1.0000 0.3346
-8.250 -0.8734 0.04716 0.03666 -0.0012 0.9968 0.3408
-8.000 -0.8589 0.04597 0.03536 -0.0014 0.9872 0.3492
-7.750 -0.8360 0.04504 0.03438 -0.0024 0.9778 0.3571
-7.500 -0.8009 0.04480 0.03418 -0.0043 0.9692 0.3649
-7.250 -0.7938 0.04312 0.03229 -0.0037 0.9583 0.3745
-7.000 -0.7500 0.04337 0.03269 -0.0061 0.9492 0.3814
-6.750 -0.7263 0.04233 0.03154 -0.0071 0.9404 0.3911
-6.500 -0.7033 0.04187 0.03111 -0.0070 0.9282 0.3986
-6.250 -0.6609 0.04154 0.03079 -0.0100 0.9213 0.4077
-6.000 -0.6598 0.04040 0.02951 -0.0069 0.9066 0.4165
-5.750 -0.6033 0.04051 0.02976 -0.0115 0.9010 0.4248
-5.500 -0.5980 0.03969 0.02884 -0.0087 0.8866 0.4338
-5.250 -0.5513 0.03939 0.02860 -0.0120 0.8799 0.4426
-5.000 -0.5321 0.03908 0.02828 -0.0108 0.8672 0.4510
-4.750 -0.5068 0.03826 0.02739 -0.0110 0.8582 0.4609
-4.500 -0.4746 0.03827 0.02749 -0.0114 0.8471 0.4686
-4.250 -0.4611 0.03738 0.02647 -0.0097 0.8363 0.4794
-4.000 -0.4205 0.03737 0.02656 -0.0114 0.8273 0.4871
-3.750 -0.4002 0.03702 0.02620 -0.0102 0.8154 0.4965
-3.500 -0.3632 0.03642 0.02557 -0.0116 0.8088 0.5066
-3.250 -0.3467 0.03649 0.02570 -0.0095 0.7943 0.5144
-3.000 -0.3233 0.03566 0.02476 -0.0089 0.7864 0.5262
-2.750 -0.2970 0.03590 0.02511 -0.0082 0.7732 0.5334
-2.500 -0.2719 0.03530 0.02443 -0.0077 0.7644 0.5448
-2.250 -0.2481 0.03531 0.02449 -0.0067 0.7523 0.5532
-2.000 -0.2171 0.03507 0.02426 -0.0068 0.7426 0.5632
-1.750 -0.1977 0.03472 0.02386 -0.0053 0.7323 0.5738
-1.500 -0.1666 0.03478 0.02398 -0.0053 0.7208 0.5826
-1.250 -0.1408 0.03407 0.02316 -0.0048 0.7137 0.5952
-1.000 -0.1184 0.03450 0.02370 -0.0035 0.6993 0.6028
-0.750 -0.0906 0.03399 0.02310 -0.0031 0.6913 0.6152
-0.500 -0.0706 0.03426 0.02344 -0.0016 0.6783 0.6237
-0.250 -0.0365 0.03408 0.02324 -0.0020 0.6692 0.6344
0.000 -0.0211 0.03408 0.02324 0.0001 0.6578 0.6454
0.250 0.0133 0.03417 0.02335 -0.0003 0.6475 0.6546
0.500 0.0321 0.03389 0.02301 0.0013 0.6384 0.6674
0.750 0.0615 0.03429 0.02349 0.0016 0.6262 0.6756
1.000 0.0848 0.03380 0.02288 0.0026 0.6188 0.6897
1.250 0.1095 0.03447 0.02367 0.0034 0.6057 0.6971
1.500 0.1400 0.03431 0.02345 0.0035 0.5971 0.7090
1.750 0.1595 0.03468 0.02386 0.0050 0.5860 0.7189
2.000 0.1909 0.03483 0.02400 0.0049 0.5761 0.7291
2.250 0.2134 0.03486 0.02401 0.0061 0.5671 0.7409
2.500 0.2399 0.03535 0.02455 0.0065 0.5559 0.7499
2.750 0.2686 0.03506 0.02416 0.0069 0.5486 0.7629
3.000 0.2894 0.03587 0.02508 0.0080 0.5364 0.7711
3.250 0.3080 0.03571 0.02486 0.0098 0.5286 0.7854
3.500 0.3415 0.03636 0.02555 0.0090 0.5180 0.7924
3.750 0.3613 0.03655 0.02573 0.0104 0.5088 0.8051
4.000 0.3997 0.03673 0.02585 0.0090 0.5005 0.8136
4.250 0.4159 0.03740 0.02661 0.0107 0.4898 0.8246
4.500 0.4512 0.03732 0.02643 0.0098 0.4823 0.8353
4.750 0.4708 0.03818 0.02739 0.0107 0.4718 0.8449
5.000 0.4925 0.03834 0.02753 0.0117 0.4636 0.8575
5.250 0.5317 0.03880 0.02797 0.0097 0.4545 0.8650
5.500 0.5397 0.03940 0.02863 0.0124 0.4457 0.8792
5.750 0.6005 0.03926 0.02833 0.0073 0.4375 0.8845
6.000 0.5956 0.04037 0.02961 0.0115 0.4282 0.9001
6.250 0.6450 0.04057 0.02975 0.0077 0.4191 0.9061
6.500 0.6637 0.04122 0.03043 0.0084 0.4109 0.9186
6.750 0.6924 0.04195 0.03122 0.0072 0.4014 0.9274
7.000 0.7382 0.04177 0.03088 0.0044 0.3942 0.9362
7.250 0.7439 0.04329 0.03261 0.0058 0.3844 0.9480
7.500 0.7786 0.04339 0.03264 0.0043 0.3770 0.9582
7.750 0.8017 0.04444 0.03377 0.0033 0.3682 0.9673
8.000 0.8242 0.04521 0.03459 0.0027 0.3599 0.9775
8.250 0.8699 0.04519 0.03447 -0.0007 0.3525 0.9843
8.500 0.8677 0.04710 0.03660 0.0008 0.3438 0.9960
8.750 0.8918 0.04722 0.03665 0.0006 0.3375 1.0000
9.000 0.8828 0.04772 0.03709 0.0054 0.3330 1.0000
9.250 0.8091 0.05069 0.04024 0.0164 0.3284 1.0000
9.500 0.7638 0.05327 0.04288 0.0233 0.3228 1.0000
9.750 0.7789 0.05299 0.04248 0.0255 0.3182 1.0000
10.000 0.7431 0.05575 0.04527 0.0308 0.3129 1.0000
10.250 0.6387 0.06473 0.05443 0.0369 0.3023 1.0000
10.500 0.6718 0.06300 0.05258 0.0385 0.2993 1.0000
11.000 0.5820 0.07532 0.06499 0.0420 0.2814 1.0000
11.250 0.6173 0.07316 0.06273 0.0438 0.2796 1.0000
11.750 0.5543 0.08518 0.07481 0.0442 0.2623 1.0000
12.250 0.5101 0.09663 0.08629 0.0431 0.2461 1.0000
12.750 0.4738 0.10777 0.09746 0.0412 0.2316 1.0000
13.000 0.4890 0.10861 0.09826 0.0418 0.2287 1.0000
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Polar data table (+)
Polar graphs
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