GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 100,000 Max Cl/Cd: 57.45 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe596-il-100000-n5.txt Download as CSV file: xf-goe596-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3287 0.09965 0.09449 -0.0339 1.0000 0.0619
-8.750 -0.3289 0.09700 0.09190 -0.0345 1.0000 0.0636
-8.500 -0.3351 0.09464 0.08962 -0.0357 1.0000 0.0658
-8.250 -0.2730 0.08245 0.07792 -0.0360 1.0000 0.0699
-8.000 -0.2722 0.08002 0.07556 -0.0342 1.0000 0.0714
-7.750 -0.2784 0.07787 0.07349 -0.0325 1.0000 0.0727
-7.500 -0.3896 0.08516 0.08055 -0.0398 1.0000 0.0681
-7.000 -0.3798 0.08069 0.07620 -0.0307 0.9999 0.0713
-6.750 -0.3564 0.07640 0.07188 -0.0364 0.9923 0.0737
-6.500 -0.3244 0.06965 0.06472 -0.0558 0.9772 0.0808
-6.250 -0.3030 0.06412 0.05909 -0.0602 0.9695 0.0816
-6.000 -0.2816 0.06058 0.05564 -0.0603 0.9638 0.0832
-5.750 -0.2523 0.05031 0.04472 -0.0683 0.9535 0.0550
-5.500 -0.2238 0.04652 0.04081 -0.0715 0.9477 0.0535
-5.250 -0.1992 0.04268 0.03671 -0.0737 0.9381 0.0523
-5.000 -0.1672 0.03859 0.03223 -0.0769 0.9320 0.0517
-4.750 -0.1418 0.03556 0.02880 -0.0779 0.9215 0.0527
-4.500 -0.1101 0.03256 0.02534 -0.0798 0.9146 0.0528
-4.250 -0.0835 0.03017 0.02258 -0.0801 0.9043 0.0524
-4.000 -0.0536 0.02802 0.02003 -0.0809 0.8957 0.0523
-3.750 -0.0230 0.02616 0.01780 -0.0814 0.8865 0.0523
-3.500 0.0056 0.02467 0.01596 -0.0815 0.8758 0.0529
-3.250 0.0377 0.02348 0.01439 -0.0820 0.8667 0.0547
-3.000 0.0672 0.02247 0.01308 -0.0820 0.8555 0.0555
-2.750 0.0960 0.02141 0.01182 -0.0819 0.8436 0.0559
-2.500 0.1253 0.02026 0.01056 -0.0820 0.8322 0.0566
-2.250 0.1553 0.01934 0.00956 -0.0821 0.8210 0.0575
-2.000 0.1827 0.01864 0.00880 -0.0817 0.8077 0.0586
-1.750 0.2098 0.01805 0.00817 -0.0813 0.7941 0.0602
-1.500 0.2368 0.01758 0.00766 -0.0809 0.7804 0.0633
-1.250 0.2637 0.01716 0.00716 -0.0804 0.7669 0.0663
-1.000 0.2902 0.01673 0.00667 -0.0798 0.7535 0.0684
-0.750 0.3164 0.01632 0.00622 -0.0792 0.7400 0.0715
-0.500 0.3429 0.01604 0.00585 -0.0786 0.7261 0.0759
-0.250 0.3693 0.01580 0.00552 -0.0780 0.7118 0.0828
0.000 0.3957 0.01551 0.00525 -0.0775 0.6979 0.1031
0.250 0.4166 0.01387 0.00520 -0.0766 0.6856 0.5518
0.750 0.5106 0.01317 0.00494 -0.0832 0.6621 1.0000
1.000 0.5355 0.01333 0.00492 -0.0824 0.6517 1.0000
1.250 0.5604 0.01351 0.00496 -0.0817 0.6414 1.0000
1.500 0.5857 0.01369 0.00499 -0.0810 0.6324 1.0000
1.750 0.6104 0.01388 0.00509 -0.0803 0.6224 1.0000
2.000 0.6356 0.01409 0.00520 -0.0796 0.6135 1.0000
2.250 0.6606 0.01430 0.00532 -0.0790 0.6045 1.0000
2.500 0.6855 0.01453 0.00549 -0.0783 0.5955 1.0000
2.750 0.7108 0.01475 0.00563 -0.0777 0.5871 1.0000
3.000 0.7353 0.01499 0.00586 -0.0770 0.5777 1.0000
3.250 0.7608 0.01523 0.00602 -0.0765 0.5698 1.0000
3.500 0.7849 0.01548 0.00631 -0.0757 0.5601 1.0000
3.750 0.8100 0.01574 0.00653 -0.0751 0.5518 1.0000
4.000 0.8342 0.01599 0.00681 -0.0744 0.5422 1.0000
4.250 0.8587 0.01626 0.00709 -0.0737 0.5330 1.0000
4.500 0.8830 0.01650 0.00732 -0.0729 0.5228 1.0000
4.750 0.9062 0.01675 0.00761 -0.0720 0.5107 1.0000
5.000 0.9293 0.01699 0.00788 -0.0711 0.4983 1.0000
5.250 0.9525 0.01723 0.00815 -0.0701 0.4861 1.0000
5.500 0.9760 0.01749 0.00842 -0.0692 0.4751 1.0000
5.750 0.9988 0.01778 0.00881 -0.0683 0.4634 1.0000
6.000 1.0212 0.01804 0.00915 -0.0673 0.4500 1.0000
6.250 1.0425 0.01829 0.00943 -0.0660 0.4338 1.0000
6.500 1.0628 0.01854 0.00966 -0.0646 0.4147 1.0000
6.750 1.0823 0.01884 0.00998 -0.0631 0.3938 1.0000
7.000 1.1019 0.01921 0.01036 -0.0617 0.3746 1.0000
7.250 1.1204 0.01964 0.01075 -0.0601 0.3545 1.0000
7.500 1.1388 0.02012 0.01124 -0.0586 0.3356 1.0000
7.750 1.1568 0.02064 0.01181 -0.0571 0.3165 1.0000
8.000 1.1726 0.02126 0.01240 -0.0552 0.2931 1.0000
8.250 1.1864 0.02196 0.01306 -0.0532 0.2624 1.0000
8.500 1.1970 0.02285 0.01382 -0.0507 0.2210 1.0000
8.750 1.2028 0.02406 0.01477 -0.0478 0.1790 1.0000
9.000 1.2062 0.02545 0.01595 -0.0446 0.1419 1.0000
9.250 1.2060 0.02698 0.01728 -0.0411 0.1033 1.0000
9.500 1.2054 0.02860 0.01872 -0.0377 0.0847 1.0000
9.750 1.2067 0.03017 0.02026 -0.0348 0.0759 1.0000
10.250 1.2097 0.03348 0.02368 -0.0299 0.0672 1.0000
10.500 1.2112 0.03527 0.02558 -0.0279 0.0641 1.0000
10.750 1.2104 0.03735 0.02773 -0.0260 0.0614 1.0000
11.250 1.2096 0.04179 0.03240 -0.0232 0.0571 1.0000
11.500 1.2113 0.04401 0.03475 -0.0221 0.0551 1.0000
11.750 1.2127 0.04633 0.03717 -0.0212 0.0530 1.0000
12.000 1.2137 0.04879 0.03970 -0.0205 0.0511 1.0000
12.250 1.2141 0.05135 0.04227 -0.0197 0.0493 1.0000
12.500 1.2194 0.05352 0.04453 -0.0189 0.0476 1.0000
12.750 1.2256 0.05566 0.04683 -0.0182 0.0459 1.0000
13.000 1.2310 0.05793 0.04924 -0.0177 0.0439 1.0000
13.250 1.2361 0.06025 0.05164 -0.0173 0.0421 1.0000
13.500 1.2426 0.06246 0.05386 -0.0168 0.0405 1.0000
13.750 1.2529 0.06450 0.05593 -0.0159 0.0390 1.0000
14.000 1.2562 0.06726 0.05894 -0.0158 0.0377 1.0000
14.250 1.2584 0.07019 0.06208 -0.0158 0.0363 1.0000
14.500 1.2591 0.07332 0.06538 -0.0160 0.0350 1.0000
14.750 1.2609 0.07638 0.06859 -0.0163 0.0339 1.0000
15.000 1.2636 0.07940 0.07171 -0.0165 0.0330 1.0000
15.250 1.2698 0.08212 0.07446 -0.0164 0.0320 1.0000
15.500 1.2641 0.08641 0.07898 -0.0174 0.0313 1.0000
15.750 1.2536 0.09145 0.08432 -0.0192 0.0308 1.0000
16.000 1.2416 0.09690 0.09004 -0.0214 0.0302 1.0000
16.250 1.2293 0.10264 0.09603 -0.0239 0.0298 1.0000
16.500 1.2148 0.10899 0.10263 -0.0271 0.0293 1.0000
16.750 1.1996 0.11578 0.10964 -0.0307 0.0291 1.0000
17.000 1.1820 0.12335 0.11744 -0.0351 0.0288 1.0000
17.250 1.1611 0.13210 0.12642 -0.0405 0.0289 1.0000
17.500 1.1349 0.14280 0.13734 -0.0474 0.0291 1.0000
17.750 1.1000 0.15691 0.15165 -0.0567 0.0296 1.0000
18.000 1.0561 0.17606 0.17089 -0.0686 0.0305 1.0000
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