GOE 445 AIRFOIL (goe445-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 445 AIRFOIL (goe445-il) Reynolds number: 1,000,000 Max Cl/Cd: 46.38 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe445-il-1000000.txt Download as CSV file: xf-goe445-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 445 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6269 0.08112 0.07953 -0.0064 1.0000 0.0057
-8.500 -0.6303 0.07490 0.07334 -0.0127 1.0000 0.0057
-8.250 -0.6394 0.06951 0.06791 -0.0171 1.0000 0.0057
-8.000 -0.6459 0.06488 0.06321 -0.0180 1.0000 0.0057
-7.750 -0.6481 0.06020 0.05842 -0.0187 1.0000 0.0057
-7.500 -0.6488 0.05555 0.05365 -0.0185 1.0000 0.0057
-7.250 -0.6466 0.05130 0.04925 -0.0178 1.0000 0.0057
-7.000 -0.6426 0.04712 0.04490 -0.0166 1.0000 0.0057
-6.750 -0.6370 0.04302 0.04060 -0.0150 1.0000 0.0057
-6.500 -0.6293 0.03926 0.03662 -0.0131 1.0000 0.0057
-6.250 -0.6205 0.03549 0.03260 -0.0109 1.0000 0.0057
-6.000 -0.6212 0.02880 0.02542 -0.0071 1.0000 0.0059
-5.750 -0.6106 0.02501 0.02128 -0.0043 1.0000 0.0060
-5.250 -0.5848 0.01747 0.01291 0.0016 1.0000 0.0063
-5.000 -0.5652 0.01681 0.01220 0.0027 1.0000 0.0075
-4.750 -0.5446 0.01545 0.01065 0.0042 1.0000 0.0079
-4.500 -0.5235 0.01421 0.00926 0.0058 1.0000 0.0083
-4.250 -0.5023 0.01288 0.00779 0.0074 1.0000 0.0084
-4.000 -0.4805 0.01217 0.00702 0.0086 1.0000 0.0092
-3.750 -0.4603 0.01086 0.00560 0.0105 1.0000 0.0090
-3.500 -0.4409 0.00977 0.00440 0.0125 1.0000 0.0089
-3.250 -0.4154 0.00896 0.00348 0.0130 0.9993 0.0094
-3.000 -0.3820 0.00858 0.00302 0.0117 0.9976 0.0112
-2.750 -0.3488 0.00809 0.00245 0.0105 0.9957 0.0123
-2.500 -0.3153 0.00761 0.00188 0.0092 0.9939 0.0182
-2.250 -0.2856 0.00695 0.00151 0.0086 0.9910 0.1049
-2.000 -0.2566 0.00605 0.00130 0.0077 0.9877 0.2912
-1.750 -0.2278 0.00511 0.00116 0.0068 0.9847 0.5167
-1.500 -0.1953 0.00468 0.00108 0.0055 0.9824 0.6213
-1.250 -0.1691 0.00417 0.00102 0.0059 0.9768 0.7411
-1.000 -0.1340 0.00389 0.00094 0.0043 0.9713 0.8042
-0.750 -0.1003 0.00370 0.00088 0.0032 0.9636 0.8414
-0.500 -0.0666 0.00357 0.00083 0.0020 0.9558 0.8721
-0.250 -0.0345 0.00347 0.00082 0.0013 0.9438 0.9049
0.000 0.0000 0.00344 0.00081 0.0000 0.9276 0.9276
0.250 0.0345 0.00347 0.00082 -0.0013 0.9051 0.9438
0.500 0.0667 0.00357 0.00083 -0.0020 0.8736 0.9558
0.750 0.1004 0.00371 0.00088 -0.0032 0.8411 0.9638
1.000 0.1342 0.00389 0.00094 -0.0044 0.8042 0.9714
1.250 0.1692 0.00415 0.00102 -0.0059 0.7437 0.9767
1.500 0.1951 0.00470 0.00108 -0.0055 0.6148 0.9824
1.750 0.2274 0.00517 0.00114 -0.0068 0.5009 0.9847
2.000 0.2565 0.00607 0.00130 -0.0077 0.2871 0.9878
2.250 0.2857 0.00693 0.00151 -0.0086 0.1074 0.9911
2.500 0.3153 0.00762 0.00188 -0.0093 0.0180 0.9940
2.750 0.3491 0.00804 0.00239 -0.0106 0.0127 0.9957
3.000 0.3822 0.00857 0.00301 -0.0118 0.0112 0.9976
3.250 0.4156 0.00896 0.00348 -0.0130 0.0097 0.9994
3.500 0.4408 0.00977 0.00440 -0.0124 0.0089 1.0000
3.750 0.4602 0.01087 0.00560 -0.0105 0.0090 1.0000
4.000 0.4804 0.01216 0.00700 -0.0086 0.0092 1.0000
4.250 0.5020 0.01298 0.00790 -0.0073 0.0085 1.0000
4.500 0.5235 0.01398 0.00901 -0.0059 0.0081 1.0000
4.750 0.5444 0.01558 0.01079 -0.0041 0.0080 1.0000
5.000 0.5651 0.01671 0.01209 -0.0027 0.0074 1.0000
5.250 0.5838 0.01776 0.01322 -0.0015 0.0062 1.0000
5.500 0.5962 0.02199 0.01803 0.0020 0.0054 1.0000
5.750 0.6103 0.02508 0.02136 0.0044 0.0060 1.0000
6.000 0.6223 0.02846 0.02506 0.0070 0.0059 1.0000
6.250 0.6206 0.03551 0.03262 0.0109 0.0057 1.0000
6.500 0.6295 0.03921 0.03657 0.0131 0.0057 1.0000
6.750 0.6366 0.04319 0.04077 0.0150 0.0057 1.0000
7.000 0.6425 0.04720 0.04498 0.0166 0.0057 1.0000
7.250 0.6467 0.05133 0.04928 0.0178 0.0057 1.0000
7.500 0.6488 0.05561 0.05371 0.0185 0.0057 1.0000
7.750 0.6485 0.06015 0.05838 0.0186 0.0057 1.0000
8.000 0.6464 0.06481 0.06314 0.0180 0.0057 1.0000
8.250 0.6400 0.06947 0.06787 0.0170 0.0057 1.0000
8.500 0.6307 0.07496 0.07340 0.0126 0.0057 1.0000
8.750 0.6272 0.08128 0.07970 0.0062 0.0057 1.0000
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