GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.59 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe595-il-1000000.txt Download as CSV file: xf-goe595-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4245 0.08724 0.08567 -0.0357 1.0000 0.0118
-9.000 -0.4321 0.08408 0.08255 -0.0354 1.0000 0.0118
-8.750 -0.4378 0.08005 0.07855 -0.0368 0.9995 0.0118
-8.500 -0.4290 0.07341 0.07192 -0.0448 0.9970 0.0118
-8.250 -0.4725 0.01277 0.01007 -0.0800 0.9759 0.0088
-8.000 -0.4918 0.02207 0.01866 -0.0793 0.9742 0.0090
-7.750 -0.4595 0.02215 0.01876 -0.0808 0.9732 0.0094
-7.500 -0.4320 0.01976 0.01604 -0.0821 0.9718 0.0097
-7.250 -0.4056 0.01819 0.01424 -0.0825 0.9691 0.0100
-7.000 -0.3813 0.01668 0.01249 -0.0822 0.9644 0.0105
-6.750 -0.3534 0.01493 0.01047 -0.0827 0.9612 0.0109
-6.500 -0.3228 0.01384 0.00920 -0.0835 0.9587 0.0113
-6.250 -0.2940 0.01336 0.00860 -0.0838 0.9548 0.0118
-6.000 -0.2712 0.01191 0.00701 -0.0831 0.9491 0.0128
-5.750 -0.2408 0.01159 0.00664 -0.0837 0.9454 0.0136
-5.500 -0.2132 0.01116 0.00615 -0.0837 0.9403 0.0143
-5.250 -0.1872 0.01072 0.00564 -0.0833 0.9344 0.0151
-5.000 -0.1576 0.01040 0.00526 -0.0837 0.9299 0.0159
-4.750 -0.1358 0.00955 0.00432 -0.0825 0.9230 0.0172
-4.500 -0.1083 0.00931 0.00406 -0.0824 0.9171 0.0185
-4.250 -0.0822 0.00912 0.00383 -0.0820 0.9101 0.0200
-4.000 -0.0556 0.00889 0.00356 -0.0817 0.9032 0.0212
-3.750 -0.0294 0.00868 0.00329 -0.0813 0.8971 0.0222
-3.500 -0.0061 0.00808 0.00263 -0.0803 0.8908 0.0248
-3.250 0.0207 0.00788 0.00238 -0.0801 0.8854 0.0271
-3.000 0.0461 0.00769 0.00217 -0.0795 0.8787 0.0289
-2.750 0.0731 0.00756 0.00197 -0.0792 0.8720 0.0299
-2.500 0.0980 0.00731 0.00167 -0.0785 0.8633 0.0335
-2.250 0.1242 0.00716 0.00148 -0.0780 0.8551 0.0372
-2.000 0.1502 0.00703 0.00132 -0.0775 0.8456 0.0440
-1.750 0.1754 0.00680 0.00122 -0.0770 0.8363 0.0847
-1.500 0.1999 0.00651 0.00112 -0.0763 0.8268 0.1530
-1.250 0.2242 0.00623 0.00105 -0.0757 0.8159 0.2307
-1.000 0.2483 0.00599 0.00099 -0.0750 0.8027 0.3071
-0.750 0.2693 0.00552 0.00094 -0.0737 0.7880 0.4657
-0.500 0.2915 0.00525 0.00092 -0.0726 0.7727 0.5682
-0.250 0.3127 0.00498 0.00092 -0.0711 0.7581 0.6721
0.000 0.3320 0.00472 0.00094 -0.0692 0.7420 0.7812
0.250 0.3525 0.00453 0.00101 -0.0672 0.7241 0.8854
0.500 0.3906 0.00458 0.00110 -0.0693 0.7046 0.9448
0.750 0.4326 0.00475 0.00118 -0.0724 0.6805 0.9687
1.000 0.4739 0.00497 0.00126 -0.0754 0.6502 0.9783
1.250 0.5132 0.00519 0.00135 -0.0779 0.6172 0.9862
1.500 0.5505 0.00543 0.00142 -0.0801 0.5799 0.9913
1.750 0.5849 0.00569 0.00150 -0.0817 0.5430 0.9951
2.000 0.6226 0.00591 0.00157 -0.0841 0.5103 0.9984
2.250 0.6534 0.00615 0.00166 -0.0850 0.4761 1.0000
2.500 0.6737 0.00633 0.00173 -0.0835 0.4538 1.0000
2.750 0.6949 0.00648 0.00181 -0.0822 0.4360 1.0000
3.000 0.7166 0.00662 0.00190 -0.0810 0.4229 1.0000
3.250 0.7384 0.00676 0.00200 -0.0797 0.4102 1.0000
3.500 0.7601 0.00691 0.00210 -0.0785 0.3938 1.0000
3.750 0.7819 0.00707 0.00221 -0.0773 0.3759 1.0000
4.000 0.8029 0.00728 0.00233 -0.0759 0.3518 1.0000
4.250 0.8230 0.00755 0.00247 -0.0745 0.3177 1.0000
4.500 0.8409 0.00798 0.00268 -0.0726 0.2723 1.0000
4.750 0.8594 0.00838 0.00292 -0.0708 0.2402 1.0000
5.000 0.8794 0.00871 0.00315 -0.0693 0.2169 1.0000
5.250 0.8995 0.00904 0.00339 -0.0679 0.1927 1.0000
5.500 0.9171 0.00956 0.00367 -0.0660 0.1466 1.0000
5.750 0.9248 0.01081 0.00439 -0.0624 0.0508 1.0000
6.000 0.9456 0.01114 0.00472 -0.0611 0.0424 1.0000
6.250 0.9664 0.01147 0.00504 -0.0598 0.0379 1.0000
6.500 0.9869 0.01184 0.00542 -0.0584 0.0331 1.0000
6.750 1.0089 0.01207 0.00569 -0.0574 0.0310 1.0000
7.000 1.0295 0.01243 0.00603 -0.0561 0.0273 1.0000
7.250 1.0496 0.01282 0.00645 -0.0547 0.0238 1.0000
7.500 1.0711 0.01308 0.00673 -0.0536 0.0213 1.0000
7.750 1.0888 0.01366 0.00731 -0.0518 0.0178 1.0000
8.000 1.1099 0.01395 0.00763 -0.0507 0.0167 1.0000
8.250 1.1301 0.01430 0.00799 -0.0494 0.0152 1.0000
8.500 1.1476 0.01483 0.00854 -0.0476 0.0137 1.0000
8.750 1.1635 0.01545 0.00923 -0.0456 0.0126 1.0000
9.000 1.1823 0.01584 0.00967 -0.0441 0.0118 1.0000
9.250 1.1984 0.01634 0.01021 -0.0421 0.0112 1.0000
9.500 1.2136 0.01679 0.01070 -0.0400 0.0105 1.0000
9.750 1.2243 0.01748 0.01144 -0.0371 0.0098 1.0000
10.000 1.2266 0.01865 0.01273 -0.0329 0.0092 1.0000
10.250 1.2385 0.01933 0.01349 -0.0304 0.0090 1.0000
10.500 1.2507 0.02001 0.01425 -0.0281 0.0087 1.0000
10.750 1.2626 0.02072 0.01503 -0.0258 0.0084 1.0000
11.000 1.2727 0.02157 0.01596 -0.0234 0.0080 1.0000
11.250 1.2825 0.02244 0.01690 -0.0211 0.0078 1.0000
11.500 1.2932 0.02329 0.01781 -0.0191 0.0075 1.0000
11.750 1.3039 0.02415 0.01873 -0.0172 0.0072 1.0000
12.000 1.3121 0.02520 0.01983 -0.0151 0.0069 1.0000
12.250 1.3135 0.02682 0.02156 -0.0125 0.0067 1.0000
12.500 1.2970 0.03004 0.02499 -0.0084 0.0063 1.0000
12.750 1.3036 0.03145 0.02649 -0.0067 0.0063 1.0000
13.000 1.3096 0.03296 0.02811 -0.0053 0.0062 1.0000
13.250 1.3120 0.03488 0.03016 -0.0038 0.0061 1.0000
13.500 1.3132 0.03699 0.03239 -0.0024 0.0061 1.0000
13.750 1.3166 0.03896 0.03447 -0.0015 0.0059 1.0000
14.000 1.3182 0.04120 0.03682 -0.0007 0.0058 1.0000
14.250 1.3139 0.04418 0.03996 0.0001 0.0057 1.0000
14.500 1.3127 0.04696 0.04285 0.0004 0.0056 1.0000
14.750 1.3065 0.05043 0.04647 0.0005 0.0055 1.0000
15.000 1.3012 0.05401 0.05018 0.0002 0.0054 1.0000
15.250 1.2950 0.05786 0.05417 -0.0004 0.0054 1.0000
15.500 1.2857 0.06231 0.05877 -0.0015 0.0054 1.0000
15.750 1.2775 0.06688 0.06347 -0.0029 0.0053 1.0000
16.000 1.2647 0.07231 0.06905 -0.0048 0.0053 1.0000
16.250 1.2614 0.07653 0.07336 -0.0068 0.0051 1.0000
16.500 1.2466 0.08263 0.07961 -0.0093 0.0051 1.0000
16.750 1.2330 0.08872 0.08584 -0.0120 0.0051 1.0000
17.000 1.2113 0.09640 0.09369 -0.0155 0.0051 1.0000
17.250 1.1876 0.10480 0.10226 -0.0195 0.0052 1.0000
17.500 1.1670 0.11302 0.11064 -0.0237 0.0052 1.0000
17.750 1.1435 0.12222 0.11999 -0.0286 0.0052 1.0000
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