GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 500,000 Max Cl/Cd: 94.96 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe548-il-500000.txt Download as CSV file: xf-goe548-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6669 0.05611 0.05362 -0.0693 1.0000 0.0122
-11.250 -0.6929 0.05222 0.04967 -0.0695 1.0000 0.0122
-11.000 -0.7191 0.04973 0.04709 -0.0672 1.0000 0.0121
-10.750 -0.7456 0.04613 0.04332 -0.0667 0.9986 0.0121
-10.500 -0.7566 0.04212 0.03901 -0.0676 0.9940 0.0120
-10.250 -0.7642 0.03740 0.03388 -0.0673 0.9884 0.0121
-10.000 -0.7622 0.03239 0.02838 -0.0677 0.9848 0.0122
-9.750 -0.7452 0.03116 0.02709 -0.0677 0.9822 0.0128
-9.500 -0.7302 0.02982 0.02558 -0.0668 0.9783 0.0134
-9.250 -0.7091 0.02828 0.02385 -0.0670 0.9756 0.0139
-9.000 -0.6880 0.02602 0.02128 -0.0673 0.9735 0.0144
-8.750 -0.6645 0.02384 0.01878 -0.0676 0.9721 0.0150
-8.500 -0.6495 0.02233 0.01704 -0.0658 0.9683 0.0153
-8.250 -0.6280 0.02120 0.01571 -0.0651 0.9651 0.0159
-8.000 -0.6057 0.01925 0.01352 -0.0648 0.9627 0.0166
-7.750 -0.5776 0.01823 0.01242 -0.0655 0.9610 0.0180
-7.500 -0.5456 0.01773 0.01187 -0.0668 0.9598 0.0193
-7.250 -0.5128 0.01714 0.01118 -0.0681 0.9588 0.0209
-7.000 -0.4974 0.01630 0.01024 -0.0659 0.9541 0.0222
-6.750 -0.4725 0.01556 0.00948 -0.0656 0.9510 0.0243
-6.500 -0.4405 0.01512 0.00899 -0.0667 0.9491 0.0269
-6.250 -0.4084 0.01440 0.00820 -0.0679 0.9476 0.0303
-6.000 -0.3728 0.01401 0.00783 -0.0698 0.9466 0.0348
-5.750 -0.3362 0.01368 0.00743 -0.0718 0.9458 0.0385
-5.500 -0.3021 0.01287 0.00660 -0.0736 0.9449 0.0448
-5.250 -0.2861 0.01266 0.00635 -0.0711 0.9384 0.0481
-5.000 -0.2530 0.01214 0.00576 -0.0725 0.9363 0.0516
-4.750 -0.2196 0.01156 0.00516 -0.0739 0.9343 0.0577
-4.500 -0.1839 0.01118 0.00471 -0.0757 0.9327 0.0624
-4.250 -0.1479 0.01066 0.00421 -0.0776 0.9310 0.0718
-4.000 -0.1279 0.01032 0.00394 -0.0759 0.9238 0.0885
-3.750 -0.0986 0.00936 0.00347 -0.0767 0.9193 0.2090
-3.250 -0.0471 0.00841 0.00302 -0.0762 0.9070 0.3563
-3.000 -0.0156 0.00808 0.00282 -0.0771 0.9028 0.4106
-2.750 0.0046 0.00786 0.00274 -0.0754 0.8949 0.4548
-2.500 0.0326 0.00760 0.00261 -0.0755 0.8895 0.5073
-2.250 0.0542 0.00742 0.00254 -0.0741 0.8816 0.5486
-2.000 0.0806 0.00721 0.00243 -0.0737 0.8751 0.5917
-1.750 0.1024 0.00706 0.00237 -0.0723 0.8666 0.6266
-1.500 0.1286 0.00688 0.00227 -0.0718 0.8598 0.6623
-1.250 0.1493 0.00672 0.00223 -0.0701 0.8500 0.6979
-1.000 0.1729 0.00656 0.00218 -0.0690 0.8417 0.7402
-0.750 0.1956 0.00640 0.00215 -0.0677 0.8322 0.7852
-0.500 0.2192 0.00631 0.00214 -0.0666 0.8217 0.8173
-0.250 0.2448 0.00623 0.00208 -0.0658 0.8097 0.8434
0.000 0.2715 0.00618 0.00204 -0.0654 0.7973 0.8672
0.250 0.3013 0.00617 0.00201 -0.0656 0.7838 0.8885
0.500 0.3337 0.00621 0.00202 -0.0664 0.7713 0.9094
0.750 0.3717 0.00633 0.00208 -0.0685 0.7584 0.9277
1.250 0.4495 0.00666 0.00228 -0.0732 0.7338 0.9507
1.500 0.4858 0.00681 0.00239 -0.0750 0.7216 0.9577
1.750 0.5236 0.00698 0.00251 -0.0772 0.7110 0.9629
2.000 0.5565 0.00714 0.00263 -0.0783 0.7007 0.9702
2.250 0.5953 0.00728 0.00273 -0.0808 0.6883 0.9739
2.500 0.6304 0.00741 0.00284 -0.0824 0.6732 0.9798
2.750 0.6663 0.00752 0.00295 -0.0843 0.6585 0.9848
3.000 0.7039 0.00761 0.00302 -0.0866 0.6360 0.9895
3.250 0.7372 0.00784 0.00307 -0.0879 0.5860 0.9953
3.500 0.7739 0.00815 0.00316 -0.0902 0.5363 1.0000
3.750 0.7844 0.00841 0.00327 -0.0868 0.5034 1.0000
4.000 0.7920 0.00878 0.00342 -0.0828 0.4572 1.0000
4.250 0.7996 0.00921 0.00361 -0.0789 0.4036 1.0000
4.500 0.8062 0.00974 0.00384 -0.0748 0.3400 1.0000
4.750 0.8063 0.01064 0.00425 -0.0696 0.2405 1.0000
5.000 0.8128 0.01135 0.00465 -0.0656 0.1826 1.0000
5.250 0.8228 0.01193 0.00500 -0.0622 0.1384 1.0000
5.500 0.8285 0.01272 0.00543 -0.0581 0.0809 1.0000
5.750 0.8360 0.01344 0.00589 -0.0543 0.0319 1.0000
6.000 0.8486 0.01391 0.00634 -0.0512 0.0242 1.0000
6.250 0.8616 0.01428 0.00678 -0.0483 0.0222 1.0000
6.500 0.8747 0.01465 0.00722 -0.0454 0.0211 1.0000
6.750 0.8851 0.01521 0.00783 -0.0421 0.0191 1.0000
7.000 0.8939 0.01590 0.00861 -0.0385 0.0177 1.0000
7.250 0.9062 0.01645 0.00921 -0.0357 0.0174 1.0000
7.500 0.9188 0.01702 0.00985 -0.0330 0.0167 1.0000
7.750 0.9299 0.01770 0.01060 -0.0301 0.0162 1.0000
8.000 0.9406 0.01845 0.01140 -0.0272 0.0159 1.0000
8.250 0.9506 0.01929 0.01230 -0.0243 0.0154 1.0000
8.500 0.9605 0.02021 0.01327 -0.0215 0.0150 1.0000
8.750 0.9713 0.02114 0.01424 -0.0190 0.0144 1.0000
9.000 0.9818 0.02216 0.01530 -0.0166 0.0139 1.0000
9.250 0.9902 0.02397 0.01712 -0.0141 0.0131 1.0000
9.500 1.0110 0.02581 0.01898 -0.0133 0.0129 1.0000
9.750 1.0414 0.02778 0.02100 -0.0139 0.0128 1.0000
10.000 1.0521 0.02855 0.02192 -0.0115 0.0125 1.0000
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Polar data table (+)
Polar graphs
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