GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 50,000 Max Cl/Cd: 26.06 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe514-il-50000-n5.txt Download as CSV file: xf-goe514-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3053 0.11881 0.11263 -0.0462 0.9848 0.0629
-9.750 -0.3058 0.11375 0.10760 -0.0496 0.9792 0.0632
-9.500 -0.3119 0.10750 0.10138 -0.0544 0.9736 0.0638
-9.250 -0.2996 0.10561 0.09951 -0.0553 0.9675 0.0659
-9.000 -0.2936 0.10225 0.09615 -0.0579 0.9617 0.0682
-8.750 -0.3022 0.09764 0.09158 -0.0605 0.9540 0.0692
-8.500 -0.3159 0.09201 0.08599 -0.0647 0.9466 0.0699
-8.250 -0.3408 0.08762 0.08164 -0.0646 0.9361 0.0700
-8.000 -0.3615 0.08143 0.07541 -0.0663 0.9274 0.0707
-7.750 -0.3884 0.07390 0.06775 -0.0671 0.9172 0.0714
-7.500 -0.4288 0.06352 0.05692 -0.0666 0.9067 0.0727
-7.250 -0.4347 0.05797 0.05095 -0.0658 0.8995 0.0758
-7.000 -0.4211 0.05742 0.05040 -0.0642 0.8921 0.0793
-6.750 -0.4267 0.05209 0.04437 -0.0621 0.8844 0.0846
-6.500 -0.3991 0.05223 0.04463 -0.0623 0.8792 0.0906
-6.250 -0.4015 0.04892 0.04073 -0.0589 0.8700 0.0974
-6.000 -0.3663 0.05006 0.04209 -0.0599 0.8643 0.1051
-5.750 -0.3553 0.04906 0.04090 -0.0575 0.8536 0.1125
-5.500 -0.3245 0.04754 0.03903 -0.0583 0.8472 0.1238
-5.250 -0.3101 0.04709 0.03846 -0.0560 0.8352 0.1316
-5.000 -0.2882 0.04613 0.03729 -0.0550 0.8260 0.1402
-4.750 -0.2665 0.04431 0.03494 -0.0542 0.8177 0.1518
-4.500 -0.2464 0.04437 0.03510 -0.0527 0.8078 0.1578
-4.250 -0.2194 0.04280 0.03308 -0.0525 0.8010 0.1698
-4.000 -0.2019 0.04278 0.03309 -0.0506 0.7905 0.1761
-3.750 -0.1707 0.04160 0.03159 -0.0509 0.7843 0.1884
-3.500 -0.1543 0.04143 0.03136 -0.0488 0.7733 0.1957
-3.250 -0.1193 0.04058 0.03029 -0.0495 0.7674 0.2081
-3.000 -0.1033 0.04012 0.02955 -0.0475 0.7558 0.2189
-2.750 -0.0657 0.03946 0.02880 -0.0484 0.7505 0.2295
-2.500 -0.0501 0.03931 0.02851 -0.0463 0.7380 0.2381
-2.250 -0.0234 0.03881 0.02775 -0.0457 0.7291 0.2491
-2.000 0.0043 0.03840 0.02730 -0.0452 0.7202 0.2586
-1.750 0.0271 0.03813 0.02689 -0.0441 0.7099 0.2700
-1.500 0.0594 0.03747 0.02601 -0.0442 0.7023 0.2830
-1.250 0.0821 0.03718 0.02569 -0.0431 0.6910 0.2908
-1.000 0.1215 0.03625 0.02446 -0.0444 0.6841 0.2989
-0.750 0.1477 0.03595 0.02409 -0.0440 0.6721 0.3041
-0.500 0.1937 0.03499 0.02290 -0.0464 0.6655 0.3140
-0.250 0.2215 0.03486 0.02267 -0.0465 0.6526 0.3209
0.000 0.2746 0.03383 0.02142 -0.0501 0.6465 0.3310
0.250 0.2997 0.03381 0.02132 -0.0497 0.6326 0.3378
0.500 0.3318 0.03354 0.02095 -0.0503 0.6212 0.3471
0.750 0.3746 0.03284 0.02014 -0.0524 0.6126 0.3596
1.000 0.3973 0.03292 0.02014 -0.0516 0.5997 0.3703
1.250 0.4334 0.03246 0.01958 -0.0527 0.5904 0.3835
1.500 0.4606 0.03228 0.01938 -0.0525 0.5795 0.3950
1.750 0.4828 0.03230 0.01937 -0.0516 0.5685 0.4076
2.000 0.5168 0.03181 0.01882 -0.0523 0.5604 0.4253
2.250 0.5310 0.03206 0.01912 -0.0503 0.5496 0.4417
2.500 0.5648 0.03137 0.01849 -0.0510 0.5425 0.4728
3.000 0.7553 0.03157 0.01969 -0.0776 0.5191 1.0000
3.250 0.7775 0.03187 0.01981 -0.0766 0.5115 1.0000
3.500 0.7963 0.03230 0.02010 -0.0752 0.5044 1.0000
3.750 0.8104 0.03286 0.02056 -0.0731 0.4971 1.0000
4.000 0.8451 0.03291 0.02039 -0.0741 0.4915 1.0000
4.250 0.8455 0.03389 0.02138 -0.0700 0.4843 1.0000
4.500 0.8656 0.03436 0.02175 -0.0689 0.4786 1.0000
4.750 0.8994 0.03451 0.02172 -0.0699 0.4738 1.0000
5.000 0.8949 0.03570 0.02298 -0.0652 0.4672 1.0000
5.250 0.9124 0.03630 0.02351 -0.0638 0.4619 1.0000
5.500 0.9469 0.03644 0.02351 -0.0648 0.4576 1.0000
5.750 0.9409 0.03783 0.02497 -0.0602 0.4521 1.0000
6.000 0.9459 0.03895 0.02611 -0.0572 0.4471 1.0000
6.250 0.9685 0.03948 0.02659 -0.0566 0.4429 1.0000
6.500 1.0064 0.03957 0.02655 -0.0582 0.4394 1.0000
6.750 0.9726 0.04217 0.02935 -0.0504 0.4334 1.0000
7.000 0.9735 0.04366 0.03088 -0.0473 0.4285 1.0000
7.250 0.9974 0.04416 0.03135 -0.0469 0.4249 1.0000
7.500 1.0359 0.04414 0.03124 -0.0483 0.4221 1.0000
7.750 0.9505 0.05041 0.03782 -0.0370 0.4144 1.0000
8.000 0.9417 0.05305 0.04053 -0.0340 0.4093 1.0000
8.250 0.9686 0.05326 0.04071 -0.0338 0.4064 1.0000
8.500 1.0118 0.05249 0.03988 -0.0349 0.4044 1.0000
9.000 0.7687 0.08178 0.06972 -0.0244 0.3745 1.0000
9.250 0.7850 0.08279 0.07072 -0.0237 0.3715 1.0000
9.500 0.8085 0.08291 0.07084 -0.0229 0.3697 1.0000
10.000 0.7568 0.09582 0.08388 -0.0227 0.3547 1.0000
10.250 0.7784 0.09626 0.08433 -0.0219 0.3523 1.0000
10.750 0.7432 0.10700 0.09519 -0.0222 0.3394 1.0000
11.000 0.7605 0.10806 0.09627 -0.0217 0.3364 1.0000
11.250 0.7846 0.10823 0.09646 -0.0209 0.3343 1.0000
11.500 0.7446 0.11629 0.10459 -0.0220 0.3246 1.0000
11.750 0.7584 0.11770 0.10604 -0.0216 0.3207 1.0000
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Polar data table (+)
Polar graphs
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