GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 100,000 Max Cl/Cd: 34.28 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe54-il-100000.txt Download as CSV file: xf-goe54-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5667 0.11954 0.11472 0.0417 1.0000 0.0433
-8.750 -0.5648 0.11711 0.11234 0.0378 1.0000 0.0438
-8.500 -0.5646 0.11488 0.11017 0.0326 1.0000 0.0440
-8.250 -0.5577 0.11054 0.10588 0.0313 1.0000 0.0443
-8.000 -0.5452 0.10539 0.10073 0.0343 1.0000 0.0452
-7.750 -0.5376 0.10175 0.09713 0.0336 1.0000 0.0463
-7.500 -0.5304 0.09834 0.09376 0.0316 1.0000 0.0476
-7.250 -0.5203 0.09474 0.09019 0.0278 1.0000 0.0492
-7.000 -0.5046 0.09114 0.08657 0.0191 1.0000 0.0508
-6.750 -0.4802 0.08743 0.08271 0.0061 1.0000 0.0515
-6.500 -0.4748 0.08252 0.07793 0.0110 1.0000 0.0523
-6.250 -0.4624 0.07868 0.07414 0.0110 1.0000 0.0536
-6.000 -0.4453 0.07493 0.07037 0.0083 1.0000 0.0554
-5.750 -0.4222 0.07113 0.06650 0.0033 1.0000 0.0580
-5.500 -0.3898 0.06714 0.06226 -0.0051 1.0000 0.0606
-5.250 -0.3783 0.06316 0.05841 -0.0037 1.0000 0.0625
-5.000 -0.3561 0.05984 0.05504 -0.0059 1.0000 0.0663
-4.750 -0.3195 0.05662 0.05146 -0.0121 1.0000 0.0710
-4.500 -0.3037 0.05275 0.04773 -0.0119 1.0000 0.0734
-4.250 -0.2768 0.04996 0.04484 -0.0139 1.0000 0.0793
-4.000 -0.2480 0.04667 0.04138 -0.0165 1.0000 0.0846
-3.750 -0.2194 0.04463 0.03919 -0.0181 1.0000 0.0939
-3.500 -0.1959 0.04109 0.03569 -0.0193 1.0000 0.1002
-3.250 -0.1675 0.03860 0.03309 -0.0209 1.0000 0.1131
-3.000 -0.1398 0.03617 0.03062 -0.0223 1.0000 0.1278
-2.750 -0.1130 0.03381 0.02832 -0.0235 1.0000 0.1460
-2.500 -0.0761 0.03152 0.02601 -0.0272 0.8774 0.1897
-2.250 -0.0594 0.03019 0.02412 -0.0248 0.7157 0.2268
-2.000 -0.0375 0.02950 0.02303 -0.0241 0.6648 0.2842
-1.750 -0.0183 0.02721 0.02080 -0.0228 0.6316 0.3305
-1.500 0.0042 0.02567 0.01919 -0.0217 0.6039 0.3841
-1.250 0.0267 0.02394 0.01746 -0.0202 0.5807 0.4266
-1.000 0.0618 0.02277 0.01591 -0.0215 0.5574 0.4291
-0.750 0.1021 0.02194 0.01448 -0.0236 0.5360 0.3952
-0.500 0.1466 0.02169 0.01332 -0.0252 0.5160 0.3102
-0.250 0.1861 0.02192 0.01276 -0.0249 0.4971 0.2318
0.000 0.2203 0.02212 0.01239 -0.0239 0.4796 0.1860
0.250 0.2507 0.02156 0.01160 -0.0233 0.4634 0.1665
0.500 0.2808 0.02130 0.01109 -0.0226 0.4484 0.1495
0.750 0.3103 0.02119 0.01073 -0.0218 0.4352 0.1350
1.000 0.3400 0.02137 0.01067 -0.0211 0.4226 0.1236
1.250 0.3685 0.02085 0.01024 -0.0207 0.4116 0.1176
1.500 0.3967 0.02085 0.01010 -0.0201 0.4027 0.1116
1.750 0.4249 0.02086 0.01013 -0.0197 0.3924 0.1089
2.000 0.4522 0.02077 0.01006 -0.0192 0.3840 0.1096
2.250 0.4798 0.02069 0.00995 -0.0187 0.3750 0.1098
2.500 0.5082 0.02078 0.01000 -0.0185 0.3658 0.1093
2.750 0.5364 0.02082 0.00990 -0.0182 0.3575 0.1099
3.000 0.5651 0.02103 0.01011 -0.0181 0.3487 0.1122
3.250 0.5932 0.02120 0.01017 -0.0178 0.3416 0.1184
3.500 0.6220 0.02151 0.01066 -0.0178 0.3342 0.1463
3.750 0.6455 0.02008 0.01095 -0.0167 0.3276 1.0000
4.000 0.6732 0.02063 0.01141 -0.0164 0.3209 1.0000
4.250 0.7008 0.02113 0.01185 -0.0162 0.3130 1.0000
4.500 0.7280 0.02165 0.01224 -0.0159 0.3065 1.0000
4.750 0.7555 0.02228 0.01292 -0.0158 0.2983 1.0000
5.000 0.7823 0.02282 0.01327 -0.0154 0.2930 1.0000
5.250 0.8095 0.02381 0.01451 -0.0156 0.2850 1.0000
5.500 0.8362 0.02443 0.01503 -0.0153 0.2794 1.0000
5.750 0.8626 0.02568 0.01647 -0.0154 0.2730 1.0000
6.000 0.8889 0.02670 0.01762 -0.0154 0.2671 1.0000
6.250 0.9152 0.02746 0.01826 -0.0150 0.2627 1.0000
6.500 0.9399 0.02930 0.02053 -0.0155 0.2560 1.0000
6.750 0.9652 0.03049 0.02185 -0.0154 0.2511 1.0000
7.000 0.9908 0.03151 0.02285 -0.0151 0.2477 1.0000
7.250 1.0128 0.03421 0.02598 -0.0158 0.2436 1.0000
7.500 1.0333 0.03715 0.02937 -0.0167 0.2384 1.0000
7.750 1.0608 0.03657 0.02861 -0.0155 0.2331 1.0000
8.000 1.0798 0.03891 0.03133 -0.0161 0.2251 1.0000
8.250 1.1077 0.03791 0.03016 -0.0148 0.2182 1.0000
8.500 1.1276 0.03974 0.03226 -0.0150 0.2116 1.0000
8.750 1.1498 0.04063 0.03334 -0.0147 0.2045 1.0000
9.000 1.1778 0.03992 0.03242 -0.0135 0.1989 1.0000
9.250 1.1933 0.04220 0.03521 -0.0139 0.1900 1.0000
9.500 1.2220 0.04103 0.03388 -0.0126 0.1832 1.0000
9.750 1.2445 0.04102 0.03406 -0.0120 0.1734 1.0000
10.000 1.2643 0.04158 0.03483 -0.0116 0.1629 1.0000
10.250 1.2901 0.04057 0.03378 -0.0105 0.1518 1.0000
10.500 1.3158 0.03958 0.03270 -0.0095 0.1403 1.0000
10.750 1.3404 0.03910 0.03201 -0.0086 0.1294 1.0000
11.000 1.3571 0.04020 0.03325 -0.0081 0.1191 1.0000
11.250 1.3645 0.04320 0.03663 -0.0079 0.1111 1.0000
11.500 1.3850 0.04382 0.03702 -0.0070 0.1037 1.0000
11.750 1.3817 0.04785 0.04164 -0.0073 0.0986 1.0000
12.000 1.4046 0.04810 0.04153 -0.0061 0.0922 1.0000
12.250 1.3900 0.05301 0.04702 -0.0069 0.0899 1.0000
12.500 1.3667 0.05849 0.05284 -0.0086 0.0889 1.0000
12.750 1.3312 0.06752 0.06216 -0.0158 0.0897 1.0000
13.000 1.2858 0.07985 0.07467 -0.0253 0.0915 1.0000
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Polar data table (+)
Polar graphs
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