GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.75 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe363-il-1000000-n5.txt Download as CSV file: xf-goe363-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3166 0.14273 0.14104 -0.0268 1.0000 0.0048
-13.000 -0.3143 0.13797 0.13629 -0.0284 1.0000 0.0050
-11.500 -0.6269 0.02532 0.02230 -0.1157 0.8991 0.0070
-11.250 -0.6096 0.02191 0.01854 -0.1171 0.8847 0.0073
-10.750 -0.5646 0.01879 0.01499 -0.1177 0.8618 0.0078
-10.500 -0.5401 0.01776 0.01380 -0.1177 0.8535 0.0081
-10.250 -0.5150 0.01688 0.01276 -0.1177 0.8454 0.0084
-10.000 -0.4894 0.01610 0.01183 -0.1177 0.8389 0.0087
-9.750 -0.4633 0.01540 0.01100 -0.1177 0.8331 0.0090
-9.500 -0.4370 0.01478 0.01023 -0.1176 0.8282 0.0093
-9.250 -0.4103 0.01415 0.00949 -0.1176 0.8236 0.0097
-9.000 -0.3834 0.01360 0.00884 -0.1175 0.8184 0.0103
-8.750 -0.3564 0.01315 0.00831 -0.1174 0.8135 0.0109
-8.500 -0.3289 0.01275 0.00783 -0.1174 0.8098 0.0116
-8.250 -0.3012 0.01235 0.00734 -0.1173 0.8062 0.0122
-8.000 -0.2735 0.01199 0.00693 -0.1173 0.8021 0.0130
-7.750 -0.2456 0.01176 0.00666 -0.1172 0.7978 0.0139
-7.500 -0.2175 0.01153 0.00639 -0.1171 0.7942 0.0148
-7.250 -0.1894 0.01126 0.00605 -0.1171 0.7898 0.0156
-7.000 -0.1613 0.01100 0.00573 -0.1170 0.7849 0.0163
-6.750 -0.1331 0.01089 0.00559 -0.1169 0.7796 0.0171
-6.500 -0.1046 0.01079 0.00550 -0.1169 0.7733 0.0180
-6.250 -0.0763 0.01068 0.00534 -0.1168 0.7673 0.0189
-6.000 -0.0480 0.01052 0.00511 -0.1167 0.7618 0.0196
-5.750 -0.0196 0.01035 0.00489 -0.1167 0.7553 0.0201
-5.500 0.0083 0.01013 0.00459 -0.1165 0.7483 0.0208
-5.250 0.0366 0.00990 0.00435 -0.1165 0.7405 0.0216
-5.000 0.0646 0.00978 0.00417 -0.1164 0.7300 0.0223
-4.750 0.0925 0.00966 0.00399 -0.1162 0.7164 0.0230
-4.500 0.1203 0.00955 0.00380 -0.1161 0.6996 0.0239
-4.250 0.1476 0.00945 0.00359 -0.1158 0.6755 0.0246
-4.000 0.1741 0.00947 0.00342 -0.1154 0.6394 0.0252
-3.750 0.1991 0.00962 0.00331 -0.1147 0.5820 0.0257
-3.500 0.2248 0.00974 0.00320 -0.1142 0.5391 0.0259
-3.250 0.2517 0.00979 0.00311 -0.1139 0.5142 0.0262
-3.000 0.2789 0.00956 0.00277 -0.1138 0.4995 0.0272
-2.750 0.3067 0.00943 0.00257 -0.1136 0.4884 0.0279
-2.500 0.3345 0.00935 0.00242 -0.1135 0.4779 0.0285
-2.250 0.3623 0.00930 0.00231 -0.1134 0.4661 0.0292
-2.000 0.3899 0.00927 0.00221 -0.1132 0.4524 0.0300
-1.750 0.4175 0.00928 0.00213 -0.1131 0.4354 0.0308
-1.500 0.4446 0.00934 0.00208 -0.1128 0.4114 0.0318
-1.250 0.4708 0.00948 0.00207 -0.1125 0.3780 0.0326
-1.000 0.4968 0.00968 0.00208 -0.1121 0.3448 0.0332
-0.750 0.5232 0.00984 0.00211 -0.1118 0.3188 0.0338
-0.500 0.5499 0.00997 0.00214 -0.1115 0.2999 0.0352
-0.250 0.5768 0.01007 0.00216 -0.1113 0.2841 0.0387
0.250 0.6304 0.01009 0.00227 -0.1110 0.2571 0.1128
0.500 0.6574 0.01019 0.00235 -0.1108 0.2461 0.1263
0.750 0.6845 0.01031 0.00242 -0.1106 0.2378 0.1349
1.000 0.7120 0.01038 0.00249 -0.1105 0.2330 0.1425
1.250 0.7393 0.01046 0.00255 -0.1104 0.2285 0.1482
1.500 0.7665 0.01056 0.00263 -0.1102 0.2239 0.1553
1.750 0.7938 0.01064 0.00271 -0.1101 0.2202 0.1621
2.000 0.8212 0.01070 0.00279 -0.1100 0.2176 0.1713
2.250 0.8484 0.01077 0.00288 -0.1099 0.2147 0.1852
2.500 0.8754 0.01078 0.00301 -0.1098 0.2116 0.2486
2.750 0.9023 0.01079 0.00315 -0.1098 0.2083 0.3166
3.000 0.9291 0.01075 0.00330 -0.1097 0.2051 0.4143
3.500 0.9803 0.00984 0.00365 -0.1090 0.2012 1.0000
3.750 1.0070 0.00999 0.00377 -0.1088 0.1984 1.0000
4.000 1.0335 0.01016 0.00390 -0.1086 0.1952 1.0000
4.250 1.0597 0.01036 0.00406 -0.1084 0.1909 1.0000
4.500 1.0862 0.01051 0.00419 -0.1082 0.1876 1.0000
4.750 1.1124 0.01069 0.00435 -0.1080 0.1836 1.0000
5.000 1.1380 0.01091 0.00452 -0.1077 0.1778 1.0000
5.250 1.1638 0.01111 0.00469 -0.1074 0.1723 1.0000
5.500 1.1882 0.01142 0.00491 -0.1069 0.1593 1.0000
5.750 1.2076 0.01214 0.00540 -0.1057 0.1252 1.0000
6.000 1.2316 0.01246 0.00568 -0.1051 0.1196 1.0000
6.250 1.2553 0.01279 0.00597 -0.1046 0.1151 1.0000
6.500 1.2793 0.01309 0.00626 -0.1040 0.1102 1.0000
6.750 1.3036 0.01335 0.00651 -0.1036 0.1083 1.0000
7.000 1.3273 0.01363 0.00679 -0.1030 0.1059 1.0000
7.250 1.3501 0.01398 0.00712 -0.1023 0.1027 1.0000
7.500 1.3726 0.01433 0.00746 -0.1016 0.0990 1.0000
7.750 1.3955 0.01463 0.00776 -0.1009 0.0959 1.0000
8.000 1.4179 0.01495 0.00808 -0.1002 0.0914 1.0000
8.250 1.4195 0.01669 0.00946 -0.0963 0.0343 1.0000
8.500 1.4315 0.01758 0.01030 -0.0940 0.0142 1.0000
8.750 1.4497 0.01805 0.01079 -0.0926 0.0123 1.0000
9.000 1.4669 0.01858 0.01135 -0.0911 0.0108 1.0000
9.250 1.4841 0.01910 0.01191 -0.0897 0.0099 1.0000
9.500 1.5010 0.01964 0.01249 -0.0883 0.0092 1.0000
9.750 1.5171 0.02024 0.01312 -0.0868 0.0085 1.0000
10.000 1.5320 0.02093 0.01384 -0.0853 0.0078 1.0000
10.250 1.5470 0.02162 0.01457 -0.0838 0.0073 1.0000
10.500 1.5618 0.02233 0.01532 -0.0824 0.0069 1.0000
10.750 1.5758 0.02311 0.01614 -0.0809 0.0065 1.0000
11.000 1.5890 0.02396 0.01704 -0.0794 0.0061 1.0000
11.250 1.6010 0.02493 0.01805 -0.0779 0.0058 1.0000
11.500 1.6117 0.02602 0.01920 -0.0763 0.0055 1.0000
11.750 1.6232 0.02706 0.02030 -0.0749 0.0053 1.0000
12.000 1.6338 0.02821 0.02150 -0.0735 0.0051 1.0000
12.250 1.6437 0.02944 0.02280 -0.0722 0.0049 1.0000
12.500 1.6530 0.03075 0.02417 -0.0709 0.0046 1.0000
12.750 1.6613 0.03217 0.02565 -0.0696 0.0044 1.0000
13.000 1.6685 0.03373 0.02726 -0.0684 0.0042 1.0000
13.250 1.6734 0.03552 0.02913 -0.0671 0.0041 1.0000
13.500 1.6752 0.03765 0.03135 -0.0658 0.0039 1.0000
13.750 1.6791 0.03965 0.03343 -0.0647 0.0038 1.0000
14.000 1.6817 0.04186 0.03572 -0.0638 0.0038 1.0000
14.250 1.6826 0.04429 0.03824 -0.0629 0.0037 1.0000
14.500 1.6822 0.04698 0.04103 -0.0623 0.0036 1.0000
14.750 1.6809 0.04991 0.04406 -0.0618 0.0035 1.0000
15.000 1.6777 0.05318 0.04744 -0.0615 0.0034 1.0000
15.250 1.6729 0.05680 0.05116 -0.0615 0.0034 1.0000
15.500 1.6670 0.06072 0.05520 -0.0618 0.0033 1.0000
15.750 1.6589 0.06511 0.05970 -0.0624 0.0032 1.0000
16.000 1.6488 0.06991 0.06462 -0.0632 0.0032 1.0000
16.250 1.6360 0.07517 0.07001 -0.0642 0.0032 1.0000
16.500 1.6209 0.08088 0.07585 -0.0655 0.0031 1.0000
16.750 1.6032 0.08712 0.08222 -0.0671 0.0031 1.0000
17.000 1.5826 0.09386 0.08910 -0.0689 0.0031 1.0000
17.250 1.5597 0.10120 0.09659 -0.0712 0.0031 1.0000
17.500 1.5361 0.10886 0.10440 -0.0737 0.0031 1.0000
17.750 1.5107 0.11690 0.11259 -0.0765 0.0031 1.0000
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