GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.58 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe121-il-1000000.txt Download as CSV file: xf-goe121-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 121 (MVA H.1) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3732 0.09088 0.08927 -0.0239 1.0000 0.0182
-8.000 -0.3765 0.08805 0.08647 -0.0236 1.0000 0.0183
-7.750 -0.3839 0.08391 0.08237 -0.0235 1.0000 0.0187
-7.500 -0.3774 0.08214 0.08061 -0.0231 1.0000 0.0189
-7.250 -0.3723 0.08030 0.07879 -0.0231 0.9999 0.0192
-7.000 -0.3456 0.07699 0.07547 -0.0288 0.9977 0.0198
-6.750 -0.3156 0.07282 0.07128 -0.0366 0.9948 0.0215
-6.500 -0.2729 0.06520 0.06360 -0.0522 0.9883 0.0231
-6.250 -0.2371 0.05877 0.05710 -0.0625 0.9831 0.0232
-5.750 -0.1792 0.04988 0.04811 -0.0750 0.9622 0.0249
-5.500 -0.1419 0.04701 0.04517 -0.0808 0.9487 0.0264
-5.250 -0.0933 0.04182 0.03978 -0.0898 0.9314 0.0294
-5.000 -0.0484 0.01910 0.01599 -0.1077 0.9191 0.0284
-4.750 -0.0203 0.01495 0.01120 -0.1094 0.9054 0.0282
-4.500 0.0069 0.01339 0.00929 -0.1097 0.8930 0.0283
-4.250 0.0343 0.01237 0.00803 -0.1097 0.8816 0.0286
-4.000 0.0616 0.01198 0.00748 -0.1094 0.8689 0.0291
-3.750 0.0890 0.01183 0.00722 -0.1091 0.8563 0.0295
-3.500 0.1166 0.01060 0.00573 -0.1092 0.8433 0.0299
-3.250 0.1440 0.00961 0.00453 -0.1091 0.8280 0.0303
-3.000 0.1713 0.00902 0.00379 -0.1089 0.8094 0.0306
-2.750 0.1983 0.00863 0.00324 -0.1085 0.7848 0.0309
-2.500 0.2252 0.00834 0.00280 -0.1082 0.7614 0.0313
-2.250 0.2525 0.00811 0.00245 -0.1079 0.7432 0.0317
-2.000 0.2802 0.00791 0.00216 -0.1078 0.7298 0.0323
-1.750 0.3080 0.00776 0.00195 -0.1076 0.7182 0.0333
-1.500 0.3359 0.00762 0.00174 -0.1075 0.7067 0.0343
-1.250 0.3640 0.00749 0.00157 -0.1073 0.6948 0.0353
-1.000 0.3919 0.00740 0.00142 -0.1072 0.6820 0.0363
-0.750 0.4198 0.00734 0.00130 -0.1071 0.6655 0.0372
-0.500 0.4474 0.00732 0.00120 -0.1068 0.6430 0.0380
-0.250 0.4741 0.00738 0.00107 -0.1065 0.5932 0.0411
0.000 0.5000 0.00758 0.00106 -0.1060 0.5382 0.0484
0.250 0.5268 0.00770 0.00120 -0.1058 0.5099 0.0905
0.500 0.5539 0.00790 0.00132 -0.1055 0.4862 0.0973
0.750 0.5811 0.00800 0.00136 -0.1053 0.4644 0.1030
1.000 0.6084 0.00812 0.00140 -0.1052 0.4426 0.1067
1.250 0.6355 0.00826 0.00146 -0.1050 0.4189 0.1090
1.500 0.6625 0.00839 0.00148 -0.1048 0.3923 0.1115
1.750 0.6895 0.00852 0.00152 -0.1046 0.3679 0.1151
2.250 0.7434 0.00881 0.00168 -0.1041 0.3309 0.1231
2.500 0.7708 0.00889 0.00174 -0.1040 0.3195 0.1285
2.750 0.7980 0.00898 0.00183 -0.1038 0.3079 0.1344
3.000 0.8253 0.00907 0.00193 -0.1037 0.2965 0.1485
3.250 0.8526 0.00907 0.00211 -0.1037 0.2840 0.2596
3.500 0.8793 0.00897 0.00233 -0.1038 0.2553 0.4850
4.000 0.9236 0.00891 0.00288 -0.1017 0.1687 1.0000
4.250 0.9499 0.00916 0.00307 -0.1014 0.1589 1.0000
4.500 0.9768 0.00934 0.00324 -0.1012 0.1527 1.0000
4.750 1.0030 0.00961 0.00344 -0.1009 0.1421 1.0000
5.000 1.0290 0.00989 0.00364 -0.1006 0.1222 1.0000
5.250 1.0526 0.01051 0.00402 -0.0999 0.0821 1.0000
5.500 1.0784 0.01082 0.00433 -0.0996 0.0747 1.0000
5.750 1.1037 0.01118 0.00465 -0.0991 0.0588 1.0000
6.000 1.1263 0.01195 0.00522 -0.0982 0.0254 1.0000
6.250 1.1510 0.01240 0.00569 -0.0976 0.0213 1.0000
6.500 1.1761 0.01276 0.00608 -0.0971 0.0196 1.0000
6.750 1.2005 0.01322 0.00655 -0.0965 0.0177 1.0000
7.000 1.2239 0.01381 0.00719 -0.0957 0.0161 1.0000
7.250 1.2484 0.01419 0.00760 -0.0952 0.0153 1.0000
7.500 1.2724 0.01463 0.00808 -0.0945 0.0144 1.0000
7.750 1.2959 0.01511 0.00859 -0.0938 0.0136 1.0000
8.000 1.3175 0.01583 0.00936 -0.0928 0.0127 1.0000
8.250 1.3364 0.01685 0.01048 -0.0914 0.0121 1.0000
8.500 1.3596 0.01728 0.01094 -0.0907 0.0117 1.0000
8.750 1.3818 0.01780 0.01152 -0.0898 0.0111 1.0000
9.000 1.4030 0.01841 0.01217 -0.0888 0.0106 1.0000
9.250 1.4236 0.01905 0.01285 -0.0878 0.0102 1.0000
9.500 1.4433 0.01975 0.01359 -0.0866 0.0098 1.0000
9.750 1.4593 0.02078 0.01468 -0.0849 0.0094 1.0000
10.000 1.4633 0.02293 0.01698 -0.0815 0.0089 1.0000
10.250 1.4814 0.02360 0.01773 -0.0801 0.0088 1.0000
10.500 1.4972 0.02443 0.01863 -0.0784 0.0086 1.0000
10.750 1.5103 0.02544 0.01972 -0.0764 0.0084 1.0000
11.000 1.5199 0.02648 0.02085 -0.0737 0.0082 1.0000
11.250 1.5270 0.02763 0.02209 -0.0708 0.0080 1.0000
11.500 1.5340 0.02881 0.02335 -0.0681 0.0078 1.0000
11.750 1.5412 0.02999 0.02463 -0.0657 0.0076 1.0000
12.000 1.5482 0.03125 0.02598 -0.0636 0.0074 1.0000
12.250 1.5555 0.03254 0.02734 -0.0617 0.0072 1.0000
12.500 1.5617 0.03401 0.02887 -0.0600 0.0071 1.0000
12.750 1.5654 0.03581 0.03076 -0.0584 0.0069 1.0000
13.000 1.5664 0.03797 0.03301 -0.0568 0.0068 1.0000
13.250 1.5631 0.04076 0.03591 -0.0552 0.0067 1.0000
13.500 1.5524 0.04455 0.03985 -0.0536 0.0065 1.0000
13.750 1.5323 0.04976 0.04530 -0.0518 0.0064 1.0000
14.000 1.5302 0.05287 0.04853 -0.0516 0.0063 1.0000
14.250 1.5267 0.05628 0.05209 -0.0517 0.0063 1.0000
14.500 1.5207 0.06015 0.05610 -0.0520 0.0063 1.0000
14.750 1.5127 0.06445 0.06055 -0.0527 0.0062 1.0000
15.000 1.5039 0.06908 0.06533 -0.0538 0.0062 1.0000
15.250 1.4929 0.07427 0.07067 -0.0553 0.0062 1.0000
15.500 1.4811 0.07988 0.07644 -0.0573 0.0061 1.0000
15.750 1.4679 0.08590 0.08261 -0.0596 0.0061 1.0000
16.000 1.4533 0.09231 0.08917 -0.0623 0.0061 1.0000
16.250 1.4374 0.09921 0.09622 -0.0653 0.0061 1.0000
16.500 1.4201 0.10657 0.10374 -0.0688 0.0061 1.0000
16.750 1.4034 0.11402 0.11134 -0.0725 0.0061 1.0000
17.000 1.3844 0.12220 0.11966 -0.0768 0.0061 1.0000
17.250 1.3667 0.13041 0.12802 -0.0813 0.0061 1.0000
17.500 1.3465 0.13946 0.13721 -0.0864 0.0061 1.0000
17.750 1.3270 0.14877 0.14667 -0.0920 0.0061 1.0000
18.000 1.3047 0.15934 0.15738 -0.0985 0.0062 1.0000
18.250 1.2819 0.17087 0.16905 -0.1059 0.0062 1.0000
18.500 1.2456 0.18746 0.18582 -0.1165 0.0063 1.0000
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