GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 200,000 Max Cl/Cd: 70.2 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe07k-il-200000-n5.txt Download as CSV file: xf-goe07k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2107 0.09126 0.08748 -0.1009 0.9387 0.0170
-8.750 -0.2042 0.08841 0.08463 -0.1015 0.9360 0.0162
-8.500 -0.1992 0.08455 0.08078 -0.1040 0.9336 0.0154
-8.250 -0.1948 0.08006 0.07630 -0.1078 0.9316 0.0148
-8.000 -0.2099 0.07775 0.07405 -0.1059 0.9237 0.0151
-7.750 -0.2234 0.06968 0.06595 -0.1120 0.9180 0.0131
-7.500 -0.2299 0.06645 0.06271 -0.1114 0.9116 0.0130
-7.250 -0.2323 0.06137 0.05755 -0.1127 0.9060 0.0131
-7.000 -0.2227 0.05709 0.05316 -0.1148 0.9035 0.0128
-6.750 -0.2071 0.05390 0.04985 -0.1169 0.9019 0.0141
-6.500 -0.2271 0.04830 0.04402 -0.1116 0.8918 0.0130
-6.250 -0.2097 0.04703 0.04267 -0.1121 0.8899 0.0144
-6.000 -0.2003 0.04053 0.03574 -0.1117 0.8878 0.0140
-5.750 -0.2104 0.03776 0.03272 -0.1054 0.8791 0.0139
-5.500 -0.2024 0.03256 0.02696 -0.1026 0.8761 0.0140
-5.250 -0.1857 0.02907 0.02296 -0.1010 0.8745 0.0144
-5.000 -0.1646 0.02645 0.01985 -0.0999 0.8734 0.0153
-4.750 -0.1661 0.02559 0.01871 -0.0941 0.8656 0.0160
-4.500 -0.1453 0.02383 0.01644 -0.0925 0.8633 0.0175
-4.250 -0.1218 0.02232 0.01466 -0.0918 0.8618 0.0184
-4.000 -0.0945 0.02157 0.01377 -0.0918 0.8606 0.0201
-3.750 -0.0658 0.02077 0.01276 -0.0920 0.8597 0.0228
-3.250 -0.0375 0.01983 0.01161 -0.0866 0.8505 0.0280
-2.750 0.0145 0.01900 0.01059 -0.0859 0.8471 0.0388
-2.500 0.0429 0.01871 0.01019 -0.0861 0.8460 0.0466
-2.250 0.0707 0.01824 0.00971 -0.0863 0.8451 0.0545
-2.000 0.0933 0.01805 0.00942 -0.0854 0.8427 0.0615
-1.000 0.1787 0.01749 0.00870 -0.0808 0.8311 0.0855
-0.500 0.4032 0.01451 0.00841 -0.1199 0.8447 0.9628
-0.250 0.4504 0.01482 0.00860 -0.1245 0.8447 1.0000
0.250 0.4687 0.01550 0.00917 -0.1173 0.8335 1.0000
0.500 0.4976 0.01545 0.00904 -0.1177 0.8321 1.0000
0.750 0.5277 0.01538 0.00891 -0.1183 0.8310 1.0000
1.000 0.5586 0.01532 0.00881 -0.1192 0.8301 1.0000
1.500 0.5764 0.01616 0.00962 -0.1120 0.8187 1.0000
1.750 0.6058 0.01612 0.00955 -0.1125 0.8174 1.0000
2.000 0.6381 0.01597 0.00941 -0.1135 0.8162 1.0000
2.500 0.6704 0.01622 0.00966 -0.1090 0.8043 1.0000
2.750 0.7056 0.01587 0.00934 -0.1104 0.8025 1.0000
3.000 0.7418 0.01556 0.00907 -0.1122 0.8011 1.0000
3.500 0.7679 0.01614 0.00974 -0.1065 0.7892 1.0000
3.750 0.8033 0.01582 0.00948 -0.1081 0.7873 1.0000
4.000 0.8097 0.01615 0.00986 -0.1038 0.7776 1.0000
4.250 0.8505 0.01544 0.00922 -0.1060 0.7730 1.0000
4.500 0.8619 0.01558 0.00942 -0.1027 0.7626 1.0000
4.750 0.8961 0.01507 0.00900 -0.1036 0.7542 1.0000
5.000 0.9174 0.01501 0.00902 -0.1022 0.7441 1.0000
5.250 0.9354 0.01504 0.00914 -0.1002 0.7321 1.0000
5.500 0.9671 0.01459 0.00875 -0.1005 0.7130 1.0000
5.750 0.9821 0.01464 0.00883 -0.0977 0.6876 1.0000
6.000 1.0073 0.01435 0.00812 -0.0964 0.5839 1.0000
6.250 0.9916 0.01562 0.00861 -0.0877 0.4744 1.0000
6.500 0.9780 0.01704 0.00956 -0.0801 0.3926 1.0000
6.750 0.9655 0.01863 0.01066 -0.0732 0.2992 1.0000
7.000 0.9588 0.02021 0.01177 -0.0678 0.2186 1.0000
7.250 0.9584 0.02163 0.01281 -0.0636 0.1454 1.0000
7.500 0.9590 0.02312 0.01390 -0.0596 0.0806 1.0000
7.750 0.9680 0.02415 0.01484 -0.0569 0.0539 1.0000
8.000 0.9775 0.02520 0.01577 -0.0544 0.0326 1.0000
8.250 0.9878 0.02625 0.01684 -0.0519 0.0252 1.0000
8.500 0.9995 0.02719 0.01788 -0.0497 0.0212 1.0000
8.750 1.0082 0.02837 0.01914 -0.0471 0.0190 1.0000
9.000 1.0182 0.02948 0.02036 -0.0448 0.0170 1.0000
9.250 1.0293 0.03052 0.02149 -0.0427 0.0153 1.0000
9.500 1.0381 0.03178 0.02281 -0.0403 0.0144 1.0000
9.750 1.0454 0.03324 0.02437 -0.0378 0.0137 1.0000
10.000 1.0558 0.03453 0.02579 -0.0357 0.0129 1.0000
10.250 1.0681 0.03562 0.02697 -0.0340 0.0117 1.0000
10.500 1.0792 0.03697 0.02838 -0.0321 0.0112 1.0000
10.750 1.0908 0.03845 0.02991 -0.0304 0.0105 1.0000
11.000 1.1068 0.03991 0.03156 -0.0289 0.0101 1.0000
11.250 1.1239 0.04147 0.03335 -0.0276 0.0097 1.0000
11.500 1.1420 0.04332 0.03542 -0.0264 0.0093 1.0000
11.750 1.1545 0.04501 0.03729 -0.0249 0.0089 1.0000
12.000 1.1630 0.04667 0.03906 -0.0232 0.0084 1.0000
12.250 1.1722 0.04873 0.04129 -0.0216 0.0082 1.0000
12.500 1.1762 0.05139 0.04430 -0.0193 0.0080 1.0000
12.750 1.1740 0.05460 0.04795 -0.0164 0.0077 1.0000
13.000 1.1692 0.05781 0.05149 -0.0137 0.0076 1.0000
13.250 1.1587 0.06157 0.05561 -0.0108 0.0075 1.0000
13.500 1.1454 0.06551 0.05987 -0.0082 0.0074 1.0000
13.750 1.1305 0.06962 0.06426 -0.0060 0.0074 1.0000
14.000 1.1144 0.07391 0.06881 -0.0043 0.0074 1.0000
14.250 1.0947 0.07890 0.07406 -0.0031 0.0074 1.0000
14.500 1.0757 0.08403 0.07941 -0.0027 0.0074 1.0000
14.750 1.0549 0.08976 0.08536 -0.0031 0.0074 1.0000
15.000 1.0374 0.09541 0.09118 -0.0043 0.0075 1.0000
15.250 1.0166 0.10223 0.09819 -0.0066 0.0075 1.0000
15.500 0.9938 0.11027 0.10641 -0.0102 0.0076 1.0000
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Polar data table (+)
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