GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 200,000 Max Cl/Cd: 68.76 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe595-il-200000-n5.txt Download as CSV file: xf-goe595-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 595 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4045 0.08774 0.08435 -0.0371 1.0000 0.0151
-8.500 -0.4128 0.08487 0.08154 -0.0364 1.0000 0.0149
-8.250 -0.4250 0.08226 0.07901 -0.0352 1.0000 0.0146
-8.000 -0.4436 0.07996 0.07679 -0.0332 1.0000 0.0145
-7.750 -0.4411 0.07456 0.07141 -0.0394 0.9952 0.0141
-7.500 -0.4276 0.06656 0.06335 -0.0499 0.9883 0.0137
-7.250 -0.4157 0.05822 0.05487 -0.0585 0.9811 0.0135
-7.000 -0.4032 0.04938 0.04575 -0.0651 0.9746 0.0130
-6.750 -0.3912 0.04093 0.03683 -0.0686 0.9680 0.0128
-6.500 -0.3772 0.03494 0.03031 -0.0696 0.9621 0.0130
-6.250 -0.3567 0.03128 0.02620 -0.0702 0.9572 0.0137
-6.000 -0.3310 0.02791 0.02228 -0.0711 0.9543 0.0147
-5.750 -0.3107 0.02521 0.01902 -0.0701 0.9489 0.0156
-5.500 -0.2855 0.02296 0.01628 -0.0698 0.9447 0.0162
-5.250 -0.2553 0.02135 0.01421 -0.0704 0.9421 0.0169
-5.000 -0.2253 0.01951 0.01225 -0.0714 0.9402 0.0187
-4.750 -0.1994 0.01871 0.01131 -0.0712 0.9355 0.0207
-4.500 -0.1704 0.01761 0.01003 -0.0713 0.9311 0.0225
-4.250 -0.1364 0.01668 0.00890 -0.0725 0.9280 0.0246
-4.000 -0.1022 0.01550 0.00767 -0.0740 0.9253 0.0283
-3.750 -0.0783 0.01484 0.00694 -0.0731 0.9178 0.0310
-3.500 -0.0458 0.01426 0.00625 -0.0740 0.9136 0.0349
-3.250 -0.0148 0.01354 0.00547 -0.0747 0.9091 0.0400
-3.000 0.0119 0.01315 0.00499 -0.0743 0.9014 0.0454
-2.750 0.0462 0.01264 0.00454 -0.0756 0.8966 0.0586
-2.500 0.0710 0.01234 0.00424 -0.0748 0.8878 0.0841
-2.250 0.1011 0.01180 0.00395 -0.0754 0.8828 0.1472
-2.000 0.1252 0.01146 0.00380 -0.0748 0.8754 0.2081
-1.750 0.1538 0.01112 0.00359 -0.0750 0.8695 0.2703
-1.500 0.1782 0.01076 0.00345 -0.0744 0.8616 0.3451
-1.250 0.2020 0.01012 0.00335 -0.0737 0.8547 0.5110
-1.000 0.2227 0.00971 0.00332 -0.0720 0.8459 0.6212
-0.750 0.2488 0.00920 0.00330 -0.0710 0.8396 0.7764
-0.500 0.3317 0.00902 0.00339 -0.0820 0.8352 0.9573
-0.250 0.3898 0.00898 0.00325 -0.0883 0.8261 0.9888
0.000 0.4330 0.00894 0.00311 -0.0916 0.8129 1.0000
0.250 0.4569 0.00892 0.00299 -0.0907 0.7975 1.0000
0.500 0.4807 0.00891 0.00289 -0.0897 0.7811 1.0000
0.750 0.5043 0.00893 0.00282 -0.0887 0.7624 1.0000
1.000 0.5282 0.00897 0.00276 -0.0878 0.7441 1.0000
1.250 0.5521 0.00904 0.00271 -0.0869 0.7245 1.0000
1.500 0.5748 0.00914 0.00270 -0.0857 0.7008 1.0000
1.750 0.5970 0.00928 0.00271 -0.0844 0.6744 1.0000
2.000 0.6184 0.00944 0.00273 -0.0830 0.6457 1.0000
2.250 0.6398 0.00963 0.00280 -0.0816 0.6191 1.0000
2.750 0.6815 0.01006 0.00301 -0.0786 0.5673 1.0000
3.000 0.7019 0.01031 0.00314 -0.0771 0.5428 1.0000
3.500 0.7430 0.01084 0.00350 -0.0741 0.5002 1.0000
3.750 0.7639 0.01111 0.00371 -0.0728 0.4823 1.0000
4.000 0.7843 0.01142 0.00393 -0.0713 0.4629 1.0000
4.250 0.8045 0.01173 0.00419 -0.0699 0.4409 1.0000
4.500 0.8242 0.01208 0.00445 -0.0683 0.4180 1.0000
4.750 0.8448 0.01238 0.00471 -0.0669 0.3954 1.0000
5.000 0.8659 0.01267 0.00501 -0.0657 0.3767 1.0000
5.250 0.8865 0.01298 0.00530 -0.0644 0.3535 1.0000
5.500 0.9060 0.01335 0.00559 -0.0629 0.3233 1.0000
5.750 0.9249 0.01376 0.00593 -0.0613 0.2934 1.0000
6.000 0.9428 0.01427 0.00631 -0.0596 0.2646 1.0000
6.250 0.9605 0.01481 0.00679 -0.0579 0.2397 1.0000
6.500 0.9789 0.01533 0.00727 -0.0564 0.2180 1.0000
6.750 0.9966 0.01591 0.00778 -0.0547 0.1894 1.0000
7.250 1.0147 0.01851 0.00951 -0.0491 0.0562 1.0000
7.500 1.0313 0.01921 0.01028 -0.0473 0.0475 1.0000
7.750 1.0454 0.02008 0.01122 -0.0452 0.0403 1.0000
8.000 1.0618 0.02070 0.01197 -0.0434 0.0348 1.0000
8.250 1.0729 0.02160 0.01292 -0.0408 0.0298 1.0000
8.500 1.0862 0.02231 0.01376 -0.0385 0.0256 1.0000
8.750 1.0962 0.02324 0.01472 -0.0358 0.0219 1.0000
9.000 1.1057 0.02419 0.01578 -0.0331 0.0197 1.0000
9.250 1.1141 0.02523 0.01695 -0.0304 0.0181 1.0000
9.500 1.1223 0.02633 0.01815 -0.0278 0.0167 1.0000
9.750 1.1310 0.02742 0.01935 -0.0254 0.0152 1.0000
10.000 1.1341 0.02897 0.02097 -0.0226 0.0139 1.0000
10.250 1.1382 0.03057 0.02269 -0.0200 0.0130 1.0000
10.500 1.1446 0.03208 0.02435 -0.0178 0.0125 1.0000
10.750 1.1504 0.03377 0.02617 -0.0156 0.0119 1.0000
11.000 1.1564 0.03554 0.02808 -0.0137 0.0114 1.0000
11.250 1.1623 0.03736 0.03004 -0.0119 0.0109 1.0000
11.500 1.1680 0.03919 0.03201 -0.0103 0.0105 1.0000
11.750 1.1725 0.04114 0.03408 -0.0088 0.0101 1.0000
12.000 1.1755 0.04307 0.03612 -0.0075 0.0096 1.0000
12.250 1.1766 0.04565 0.03884 -0.0062 0.0094 1.0000
12.500 1.1754 0.04860 0.04197 -0.0049 0.0090 1.0000
12.750 1.1760 0.05118 0.04478 -0.0041 0.0087 1.0000
13.000 1.1730 0.05446 0.04832 -0.0033 0.0085 1.0000
13.250 1.1677 0.05805 0.05218 -0.0028 0.0082 1.0000
13.500 1.1608 0.06194 0.05630 -0.0028 0.0083 1.0000
13.750 1.1514 0.06627 0.06087 -0.0033 0.0081 1.0000
14.000 1.1393 0.07117 0.06601 -0.0044 0.0079 1.0000
14.250 1.1267 0.07642 0.07149 -0.0060 0.0079 1.0000
14.500 1.1120 0.08231 0.07760 -0.0084 0.0079 1.0000
14.750 1.0965 0.08871 0.08421 -0.0113 0.0079 1.0000
15.000 1.0790 0.09591 0.09162 -0.0150 0.0079 1.0000
15.250 1.0614 0.10352 0.09941 -0.0192 0.0080 1.0000
15.500 1.0431 0.11173 0.10779 -0.0240 0.0080 1.0000
15.750 1.0237 0.12073 0.11692 -0.0294 0.0081 1.0000
16.000 1.0028 0.13081 0.12715 -0.0355 0.0082 1.0000
16.250 0.9842 0.14090 0.13735 -0.0415 0.0084 1.0000
16.500 0.9622 0.15286 0.14940 -0.0484 0.0086 1.0000
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