GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 500,000 Max Cl/Cd: 108.21 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe115-il-500000.txt Download as CSV file: xf-goe115-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 115 (MVA MK.2) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3819 0.08605 0.08387 -0.0395 1.0000 0.0205
-8.750 -0.3836 0.08228 0.08012 -0.0408 1.0000 0.0207
-8.500 -0.3890 0.07753 0.07543 -0.0430 1.0000 0.0224
-6.750 -0.3153 0.02695 0.02311 -0.0958 0.9503 0.0214
-6.250 -0.2592 0.02159 0.01690 -0.0979 0.9268 0.0223
-5.500 -0.1862 0.01618 0.01057 -0.0969 0.8845 0.0257
-5.250 -0.1614 0.01549 0.00983 -0.0965 0.8707 0.0282
-5.000 -0.1364 0.01453 0.00868 -0.0958 0.8571 0.0293
-4.750 -0.1112 0.01371 0.00771 -0.0951 0.8439 0.0303
-4.500 -0.0855 0.01317 0.00701 -0.0946 0.8310 0.0315
-4.250 -0.0606 0.01239 0.00609 -0.0939 0.8183 0.0333
-4.000 -0.0365 0.01149 0.00509 -0.0932 0.8055 0.0342
-3.750 -0.0117 0.01088 0.00438 -0.0926 0.7926 0.0354
-3.500 0.0137 0.01043 0.00383 -0.0921 0.7795 0.0372
-3.250 0.0394 0.01009 0.00338 -0.0916 0.7662 0.0388
-3.000 0.0655 0.00982 0.00299 -0.0912 0.7526 0.0397
-2.750 0.0919 0.00961 0.00266 -0.0908 0.7392 0.0406
-2.500 0.1184 0.00944 0.00236 -0.0904 0.7262 0.0415
-2.250 0.1452 0.00931 0.00212 -0.0901 0.7140 0.0428
-2.000 0.1721 0.00921 0.00192 -0.0899 0.7029 0.0449
-1.750 0.1991 0.00913 0.00177 -0.0896 0.6930 0.0501
-1.500 0.2243 0.00864 0.00157 -0.0893 0.6839 0.1553
-1.250 0.2504 0.00838 0.00157 -0.0891 0.6754 0.2439
-1.000 0.2775 0.00841 0.00160 -0.0889 0.6680 0.2715
-0.750 0.3050 0.00844 0.00162 -0.0888 0.6604 0.2863
-0.500 0.3323 0.00852 0.00165 -0.0886 0.6540 0.3021
-0.250 0.3597 0.00853 0.00170 -0.0886 0.6471 0.3149
0.000 0.3868 0.00858 0.00172 -0.0884 0.6407 0.3243
0.250 0.4142 0.00860 0.00175 -0.0883 0.6343 0.3337
0.500 0.4414 0.00864 0.00178 -0.0882 0.6286 0.3439
0.750 0.4686 0.00866 0.00182 -0.0881 0.6234 0.3506
1.000 0.4960 0.00867 0.00186 -0.0880 0.6178 0.3595
1.250 0.5231 0.00869 0.00192 -0.0879 0.6133 0.3728
1.500 0.5503 0.00870 0.00199 -0.0877 0.6087 0.3863
1.750 0.5774 0.00868 0.00204 -0.0876 0.6035 0.3978
2.000 0.6043 0.00868 0.00211 -0.0875 0.5988 0.4169
2.250 0.6307 0.00858 0.00222 -0.0873 0.5944 0.4670
2.500 0.6776 0.00743 0.00240 -0.0916 0.5892 1.0000
2.750 0.7044 0.00754 0.00249 -0.0914 0.5850 1.0000
3.000 0.7311 0.00767 0.00261 -0.0911 0.5805 1.0000
3.250 0.7572 0.00772 0.00268 -0.0907 0.5718 1.0000
3.500 0.7827 0.00778 0.00273 -0.0902 0.5600 1.0000
3.750 0.8080 0.00784 0.00279 -0.0896 0.5459 1.0000
4.000 0.8334 0.00792 0.00288 -0.0890 0.5321 1.0000
4.250 0.8583 0.00802 0.00296 -0.0884 0.5138 1.0000
4.500 0.8830 0.00816 0.00307 -0.0877 0.4901 1.0000
4.750 0.9029 0.00859 0.00322 -0.0862 0.4129 1.0000
5.000 0.9007 0.01113 0.00438 -0.0817 0.1626 1.0000
5.250 0.9081 0.01297 0.00560 -0.0785 0.0349 1.0000
5.500 0.9295 0.01350 0.00618 -0.0773 0.0286 1.0000
5.750 0.9480 0.01428 0.00700 -0.0756 0.0241 1.0000
6.000 0.9684 0.01484 0.00762 -0.0743 0.0221 1.0000
6.250 0.9879 0.01546 0.00830 -0.0729 0.0205 1.0000
6.500 1.0062 0.01614 0.00904 -0.0713 0.0191 1.0000
6.750 1.0223 0.01695 0.00990 -0.0694 0.0181 1.0000
7.000 1.0307 0.01832 0.01134 -0.0663 0.0170 1.0000
7.250 1.0402 0.01967 0.01278 -0.0633 0.0162 1.0000
7.500 1.0583 0.02026 0.01342 -0.0618 0.0154 1.0000
7.750 1.0721 0.02125 0.01448 -0.0595 0.0148 1.0000
8.000 1.0860 0.02240 0.01570 -0.0574 0.0144 1.0000
8.250 1.1022 0.02357 0.01694 -0.0556 0.0138 1.0000
8.500 1.1222 0.02506 0.01849 -0.0545 0.0135 1.0000
8.750 1.1457 0.02670 0.02022 -0.0540 0.0131 1.0000
9.000 1.1787 0.02998 0.02373 -0.0547 0.0133 1.0000
15.250 0.7779 0.16310 0.16126 -0.0727 0.0178 1.0000
15.500 0.7814 0.16558 0.16376 -0.0739 0.0172 1.0000
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Polar data table (+)
Polar graphs
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