GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 500,000 Max Cl/Cd: 87.16 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe477-il-500000-n5.txt Download as CSV file: xf-goe477-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2233 0.07926 0.07625 -0.0866 0.8409 0.0092
-10.000 -0.3792 0.05348 0.05049 -0.0999 0.8299 0.0089
-9.750 -0.4623 0.02745 0.02355 -0.1154 0.8236 0.0083
-9.500 -0.4494 0.02443 0.02018 -0.1155 0.8216 0.0085
-9.250 -0.4321 0.02238 0.01781 -0.1153 0.8195 0.0088
-9.000 -0.4123 0.02082 0.01598 -0.1149 0.8174 0.0090
-8.750 -0.3922 0.01941 0.01438 -0.1145 0.8155 0.0094
-8.500 -0.3697 0.01842 0.01323 -0.1141 0.8138 0.0097
-8.250 -0.3462 0.01756 0.01221 -0.1138 0.8121 0.0100
-8.000 -0.3222 0.01676 0.01124 -0.1135 0.8103 0.0105
-7.750 -0.2977 0.01603 0.01036 -0.1131 0.8086 0.0111
-7.500 -0.2725 0.01541 0.00958 -0.1128 0.8066 0.0116
-7.250 -0.2480 0.01467 0.00876 -0.1125 0.8045 0.0125
-7.000 -0.2223 0.01415 0.00813 -0.1123 0.8025 0.0133
-6.750 -0.1964 0.01364 0.00751 -0.1120 0.8007 0.0141
-6.500 -0.1702 0.01318 0.00693 -0.1117 0.7990 0.0150
-6.250 -0.1442 0.01268 0.00636 -0.1115 0.7973 0.0165
-6.000 -0.1176 0.01231 0.00589 -0.1113 0.7957 0.0182
-5.750 -0.0909 0.01193 0.00543 -0.1111 0.7942 0.0204
-5.500 -0.0642 0.01158 0.00506 -0.1109 0.7926 0.0232
-5.250 -0.0373 0.01130 0.00477 -0.1107 0.7908 0.0278
-5.000 -0.0099 0.01114 0.00463 -0.1106 0.7888 0.0334
-4.750 0.0177 0.01103 0.00453 -0.1105 0.7867 0.0386
-4.500 0.0455 0.01099 0.00445 -0.1104 0.7842 0.0438
-4.250 0.0734 0.01095 0.00433 -0.1103 0.7814 0.0472
-4.000 0.1014 0.01096 0.00426 -0.1102 0.7786 0.0487
-3.750 0.1278 0.01066 0.00396 -0.1100 0.7755 0.0518
-3.500 0.1551 0.01051 0.00381 -0.1098 0.7721 0.0544
-3.250 0.1825 0.01040 0.00366 -0.1097 0.7692 0.0570
-3.000 0.2100 0.01027 0.00348 -0.1095 0.7665 0.0590
-2.750 0.2373 0.01014 0.00329 -0.1093 0.7625 0.0603
-2.500 0.2640 0.00995 0.00308 -0.1090 0.7566 0.0609
-2.250 0.2909 0.00977 0.00284 -0.1087 0.7508 0.0613
-2.000 0.3175 0.00957 0.00262 -0.1084 0.7440 0.0621
-1.750 0.3442 0.00936 0.00239 -0.1080 0.7374 0.0637
-1.500 0.3712 0.00921 0.00224 -0.1078 0.7321 0.0661
-1.250 0.3982 0.00908 0.00211 -0.1076 0.7253 0.0683
-1.000 0.4251 0.00897 0.00198 -0.1073 0.7181 0.0709
-0.750 0.4520 0.00888 0.00187 -0.1070 0.7084 0.0737
-0.500 0.4787 0.00877 0.00177 -0.1067 0.6978 0.0810
-0.250 0.5050 0.00867 0.00168 -0.1063 0.6850 0.0936
0.000 0.5307 0.00856 0.00162 -0.1059 0.6703 0.1258
0.250 0.5558 0.00849 0.00159 -0.1053 0.6522 0.1670
0.500 0.5800 0.00851 0.00158 -0.1046 0.6292 0.2003
0.750 0.6033 0.00859 0.00161 -0.1037 0.6006 0.2337
1.000 0.6250 0.00871 0.00170 -0.1025 0.5631 0.2856
1.250 0.6438 0.00883 0.00186 -0.1009 0.5111 0.3901
1.750 0.7139 0.00841 0.00243 -0.1049 0.4215 1.0000
2.000 0.7356 0.00868 0.00257 -0.1037 0.4029 1.0000
2.250 0.7578 0.00891 0.00271 -0.1026 0.3871 1.0000
2.500 0.7803 0.00914 0.00285 -0.1016 0.3727 1.0000
2.750 0.8029 0.00937 0.00300 -0.1006 0.3585 1.0000
3.000 0.8253 0.00961 0.00315 -0.0996 0.3435 1.0000
3.250 0.8476 0.00985 0.00331 -0.0986 0.3286 1.0000
3.500 0.8700 0.01010 0.00348 -0.0976 0.3138 1.0000
3.750 0.8925 0.01033 0.00365 -0.0967 0.3011 1.0000
4.000 0.9150 0.01057 0.00384 -0.0957 0.2898 1.0000
4.250 0.9371 0.01082 0.00403 -0.0947 0.2799 1.0000
4.500 0.9596 0.01105 0.00424 -0.0938 0.2709 1.0000
4.750 0.9817 0.01130 0.00445 -0.0928 0.2634 1.0000
5.000 1.0039 0.01154 0.00467 -0.0918 0.2564 1.0000
5.250 1.0255 0.01180 0.00492 -0.0908 0.2505 1.0000
5.500 1.0477 0.01202 0.00515 -0.0898 0.2456 1.0000
5.750 1.0688 0.01229 0.00541 -0.0887 0.2396 1.0000
6.000 1.0895 0.01258 0.00568 -0.0875 0.2314 1.0000
6.250 1.1089 0.01292 0.00597 -0.0861 0.2227 1.0000
6.500 1.1290 0.01319 0.00625 -0.0848 0.2144 1.0000
6.750 1.1464 0.01354 0.00656 -0.0831 0.2070 1.0000
7.000 1.1658 0.01380 0.00685 -0.0816 0.2002 1.0000
7.250 1.1827 0.01418 0.00720 -0.0799 0.1912 1.0000
7.500 1.2008 0.01453 0.00753 -0.0783 0.1790 1.0000
7.750 1.2165 0.01501 0.00794 -0.0764 0.1613 1.0000
8.000 1.2119 0.01674 0.00912 -0.0718 0.0736 1.0000
8.250 1.2158 0.01811 0.01028 -0.0685 0.0311 1.0000
8.500 1.2312 0.01874 0.01093 -0.0668 0.0243 1.0000
8.750 1.2453 0.01946 0.01166 -0.0650 0.0197 1.0000
9.000 1.2611 0.02008 0.01233 -0.0635 0.0175 1.0000
9.250 1.2747 0.02087 0.01315 -0.0619 0.0154 1.0000
9.500 1.2894 0.02158 0.01392 -0.0603 0.0143 1.0000
9.750 1.3033 0.02235 0.01474 -0.0588 0.0129 1.0000
10.000 1.3153 0.02328 0.01571 -0.0571 0.0118 1.0000
10.250 1.3284 0.02414 0.01664 -0.0556 0.0111 1.0000
10.500 1.3403 0.02510 0.01767 -0.0541 0.0105 1.0000
10.750 1.3516 0.02611 0.01876 -0.0525 0.0099 1.0000
11.000 1.3604 0.02733 0.02003 -0.0508 0.0094 1.0000
11.250 1.3692 0.02857 0.02136 -0.0492 0.0089 1.0000
11.500 1.3789 0.02974 0.02261 -0.0477 0.0083 1.0000
11.750 1.3865 0.03112 0.02407 -0.0462 0.0080 1.0000
12.000 1.3932 0.03259 0.02561 -0.0447 0.0076 1.0000
12.250 1.3977 0.03427 0.02736 -0.0431 0.0073 1.0000
12.500 1.3983 0.03634 0.02952 -0.0415 0.0071 1.0000
12.750 1.4016 0.03823 0.03155 -0.0401 0.0069 1.0000
13.000 1.4029 0.04037 0.03380 -0.0388 0.0067 1.0000
13.250 1.4027 0.04275 0.03629 -0.0376 0.0066 1.0000
13.500 1.4027 0.04520 0.03886 -0.0366 0.0064 1.0000
13.750 1.4009 0.04800 0.04176 -0.0358 0.0062 1.0000
14.000 1.3996 0.05087 0.04473 -0.0353 0.0060 1.0000
14.250 1.3972 0.05402 0.04800 -0.0350 0.0059 1.0000
14.500 1.3914 0.05776 0.05185 -0.0350 0.0058 1.0000
14.750 1.3912 0.06093 0.05510 -0.0353 0.0056 1.0000
15.000 1.3857 0.06497 0.05924 -0.0358 0.0055 1.0000
15.250 1.3757 0.06981 0.06421 -0.0367 0.0055 1.0000
15.500 1.3669 0.07466 0.06918 -0.0379 0.0053 1.0000
15.750 1.3607 0.07932 0.07397 -0.0392 0.0052 1.0000
16.000 1.3532 0.08427 0.07905 -0.0407 0.0052 1.0000
16.250 1.3454 0.08933 0.08423 -0.0423 0.0051 1.0000
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