GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.05 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795-il-1000000.txt Download as CSV file: xf-goe795-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.9435 0.03748 0.03550 -0.0594 1.0000 0.0037
-11.750 -0.9652 0.03070 0.02827 -0.0575 1.0000 0.0037
-11.500 -0.9628 0.02796 0.02528 -0.0554 1.0000 0.0037
-11.250 -0.9553 0.02592 0.02304 -0.0533 1.0000 0.0039
-11.000 -0.9467 0.02405 0.02095 -0.0512 1.0000 0.0040
-10.750 -0.9350 0.02263 0.01935 -0.0491 1.0000 0.0041
-10.500 -0.9177 0.02199 0.01869 -0.0476 1.0000 0.0045
-10.250 -0.8983 0.02171 0.01841 -0.0463 1.0000 0.0048
-10.000 -0.8734 0.02230 0.01912 -0.0456 1.0000 0.0052
-9.750 -0.8463 0.02328 0.02025 -0.0450 1.0000 0.0060
-9.500 -0.8187 0.02439 0.02148 -0.0445 1.0000 0.0067
-9.000 -0.7676 0.02212 0.01893 -0.0459 0.9978 0.0079
-8.750 -0.7307 0.02370 0.02073 -0.0473 0.9970 0.0086
-8.500 -0.6933 0.02551 0.02273 -0.0487 0.9963 0.0094
-8.250 -0.6604 0.02557 0.02277 -0.0502 0.9951 0.0102
-8.000 -0.6343 0.02308 0.01997 -0.0516 0.9934 0.0105
-7.750 -0.6034 0.02325 0.02013 -0.0524 0.9916 0.0111
-7.500 -0.5751 0.02229 0.01898 -0.0533 0.9892 0.0120
-7.250 -0.5517 0.01923 0.01550 -0.0539 0.9863 0.0121
-7.000 -0.5255 0.01674 0.01263 -0.0546 0.9842 0.0125
-6.750 -0.4951 0.01543 0.01113 -0.0557 0.9829 0.0133
-6.500 -0.4668 0.01417 0.00967 -0.0561 0.9807 0.0132
-6.250 -0.4411 0.01335 0.00874 -0.0559 0.9767 0.0136
-6.000 -0.4102 0.01291 0.00824 -0.0567 0.9742 0.0144
-5.750 -0.3771 0.01276 0.00809 -0.0580 0.9724 0.0156
-5.500 -0.3451 0.01189 0.00710 -0.0590 0.9708 0.0159
-5.250 -0.3133 0.01084 0.00589 -0.0599 0.9694 0.0157
-5.000 -0.2886 0.01009 0.00503 -0.0592 0.9639 0.0155
-4.750 -0.2580 0.00946 0.00429 -0.0597 0.9605 0.0155
-4.500 -0.2244 0.00890 0.00365 -0.0609 0.9580 0.0156
-4.250 -0.1885 0.00846 0.00312 -0.0627 0.9558 0.0158
-4.000 -0.1602 0.00813 0.00273 -0.0627 0.9490 0.0162
-3.750 -0.1252 0.00779 0.00233 -0.0642 0.9445 0.0174
-3.500 -0.0932 0.00751 0.00203 -0.0650 0.9372 0.0218
-3.250 -0.0595 0.00728 0.00179 -0.0662 0.9291 0.0300
-3.000 -0.0309 0.00711 0.00161 -0.0663 0.9179 0.0371
-2.750 -0.0024 0.00701 0.00146 -0.0663 0.9060 0.0427
-2.500 0.0249 0.00688 0.00133 -0.0661 0.8923 0.0515
-2.250 0.0508 0.00669 0.00123 -0.0657 0.8772 0.0846
-2.000 0.0770 0.00662 0.00115 -0.0652 0.8609 0.1000
-1.750 0.1024 0.00655 0.00106 -0.0646 0.8432 0.1138
-1.500 0.1273 0.00647 0.00098 -0.0639 0.8243 0.1329
-1.250 0.1513 0.00632 0.00093 -0.0630 0.8063 0.1865
-1.000 0.1755 0.00619 0.00089 -0.0622 0.7907 0.2353
-0.750 0.2001 0.00609 0.00085 -0.0615 0.7763 0.2744
-0.500 0.2236 0.00588 0.00083 -0.0606 0.7634 0.3569
-0.250 0.2455 0.00557 0.00082 -0.0594 0.7496 0.4770
0.000 0.2653 0.00522 0.00083 -0.0578 0.7329 0.6158
0.250 0.2797 0.00472 0.00086 -0.0547 0.7189 0.7979
0.750 0.4117 0.00475 0.00115 -0.0717 0.6844 0.9847
1.000 0.4504 0.00488 0.00122 -0.0741 0.6684 0.9915
1.250 0.4895 0.00501 0.00125 -0.0766 0.6460 0.9958
1.500 0.5331 0.00515 0.00125 -0.0803 0.6131 0.9999
1.750 0.5557 0.00529 0.00127 -0.0791 0.5817 1.0000
2.000 0.5761 0.00552 0.00130 -0.0775 0.5325 1.0000
2.250 0.5960 0.00582 0.00137 -0.0759 0.4769 1.0000
2.500 0.6158 0.00617 0.00147 -0.0743 0.4186 1.0000
2.750 0.6364 0.00650 0.00159 -0.0728 0.3708 1.0000
3.000 0.6583 0.00675 0.00173 -0.0716 0.3385 1.0000
3.250 0.6803 0.00702 0.00186 -0.0704 0.3081 1.0000
3.500 0.7023 0.00728 0.00200 -0.0693 0.2781 1.0000
3.750 0.7236 0.00761 0.00216 -0.0680 0.2354 1.0000
4.000 0.7422 0.00814 0.00241 -0.0662 0.1733 1.0000
4.250 0.7631 0.00852 0.00267 -0.0649 0.1425 1.0000
4.500 0.7841 0.00889 0.00290 -0.0635 0.1106 1.0000
4.750 0.8033 0.00942 0.00322 -0.0619 0.0680 1.0000
5.000 0.8251 0.00974 0.00347 -0.0607 0.0558 1.0000
5.250 0.8477 0.01000 0.00373 -0.0596 0.0507 1.0000
5.500 0.8701 0.01028 0.00400 -0.0585 0.0476 1.0000
5.750 0.8916 0.01064 0.00437 -0.0573 0.0423 1.0000
6.000 0.9146 0.01086 0.00461 -0.0564 0.0402 1.0000
6.250 0.9382 0.01102 0.00479 -0.0556 0.0388 1.0000
6.500 0.9614 0.01121 0.00501 -0.0547 0.0352 1.0000
6.750 0.9836 0.01149 0.00528 -0.0536 0.0292 1.0000
7.000 1.0002 0.01227 0.00587 -0.0515 0.0083 1.0000
7.250 1.0201 0.01276 0.00644 -0.0500 0.0065 1.0000
7.500 1.0378 0.01346 0.00723 -0.0480 0.0052 1.0000
7.750 1.0565 0.01406 0.00790 -0.0463 0.0049 1.0000
8.000 1.0762 0.01455 0.00845 -0.0448 0.0048 1.0000
8.250 1.0943 0.01519 0.00918 -0.0429 0.0045 1.0000
8.500 1.1125 0.01579 0.00986 -0.0413 0.0043 1.0000
8.750 1.1300 0.01645 0.01059 -0.0394 0.0041 1.0000
9.000 1.1485 0.01701 0.01119 -0.0379 0.0037 1.0000
9.250 1.1638 0.01783 0.01213 -0.0358 0.0036 1.0000
9.500 1.1797 0.01858 0.01295 -0.0338 0.0034 1.0000
9.750 1.1914 0.01967 0.01414 -0.0312 0.0031 1.0000
10.000 1.1936 0.02164 0.01631 -0.0272 0.0029 1.0000
10.250 1.1922 0.02400 0.01892 -0.0226 0.0028 1.0000
10.500 1.2001 0.02510 0.02014 -0.0195 0.0027 1.0000
10.750 1.2072 0.02627 0.02145 -0.0165 0.0027 1.0000
11.000 1.2124 0.02765 0.02298 -0.0134 0.0026 1.0000
11.250 1.2142 0.02939 0.02489 -0.0101 0.0026 1.0000
11.500 1.2131 0.03141 0.02710 -0.0069 0.0026 1.0000
11.750 1.2096 0.03367 0.02956 -0.0039 0.0026 1.0000
12.000 1.2027 0.03631 0.03240 -0.0012 0.0026 1.0000
12.250 1.1948 0.03916 0.03545 0.0010 0.0026 1.0000
12.500 1.1835 0.04254 0.03902 0.0026 0.0027 1.0000
12.750 1.1702 0.04646 0.04316 0.0034 0.0026 1.0000
13.000 1.1467 0.05205 0.04898 0.0031 0.0027 1.0000
13.250 1.1291 0.05743 0.05455 0.0016 0.0027 1.0000
13.500 1.1124 0.06321 0.06051 -0.0007 0.0027 1.0000
13.750 1.0869 0.07090 0.06834 -0.0041 0.0028 1.0000
14.000 1.0771 0.07660 0.07415 -0.0074 0.0028 1.0000
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