GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.56 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe118-il-1000000-n5.txt Download as CSV file: xf-goe118-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 118 (MVA MK.7) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2826 0.12154 0.11977 -0.0354 0.9071 0.0022
-10.250 -0.2772 0.11866 0.11676 -0.0361 0.8788 0.0023
-10.000 -0.2711 0.11570 0.11370 -0.0371 0.8553 0.0024
-9.750 -0.2646 0.11268 0.11059 -0.0382 0.8344 0.0025
-9.500 -0.2578 0.10962 0.10745 -0.0395 0.8159 0.0026
-9.250 -0.2509 0.10653 0.10429 -0.0408 0.7990 0.0027
-9.000 -0.2437 0.10342 0.10111 -0.0422 0.7841 0.0029
-8.750 -0.2359 0.10013 0.09778 -0.0438 0.7712 0.0034
-8.500 -0.2280 0.09676 0.09436 -0.0457 0.7599 0.0035
-8.250 -0.2206 0.09343 0.09100 -0.0477 0.7498 0.0036
-8.000 -0.2131 0.09014 0.08768 -0.0496 0.7409 0.0036
-7.750 -0.2052 0.08689 0.08441 -0.0516 0.7323 0.0036
-7.500 -0.1970 0.08362 0.08113 -0.0537 0.7242 0.0036
-7.250 -0.1886 0.08039 0.07786 -0.0561 0.7169 0.0036
-7.000 -0.1771 0.07695 0.07440 -0.0595 0.7100 0.0037
-6.500 -0.1474 0.06815 0.06557 -0.0700 0.6980 0.0038
-5.000 0.0106 0.04143 0.03843 -0.1066 0.6636 0.0034
-4.750 0.0450 0.03590 0.03274 -0.1130 0.6585 0.0031
-4.500 0.0817 0.02906 0.02563 -0.1189 0.6532 0.0029
-4.250 0.1192 0.01865 0.01446 -0.1237 0.6490 0.0025
-4.000 0.1502 0.01420 0.00927 -0.1247 0.6440 0.0024
-3.750 0.1795 0.01203 0.00664 -0.1250 0.6379 0.0025
-3.500 0.2081 0.01086 0.00517 -0.1252 0.6321 0.0028
-3.250 0.2367 0.01007 0.00419 -0.1254 0.6257 0.0032
-3.000 0.2650 0.00960 0.00355 -0.1255 0.6193 0.0036
-2.750 0.2934 0.00912 0.00297 -0.1258 0.6124 0.0042
-2.500 0.3215 0.00892 0.00269 -0.1260 0.6040 0.0049
-2.250 0.3499 0.00859 0.00223 -0.1261 0.5939 0.0055
-2.000 0.3781 0.00841 0.00195 -0.1263 0.5844 0.0063
-1.750 0.4063 0.00819 0.00162 -0.1265 0.5766 0.0089
-1.500 0.4347 0.00810 0.00147 -0.1267 0.5704 0.0110
-1.250 0.4629 0.00798 0.00127 -0.1268 0.5640 0.0193
-1.000 0.4911 0.00778 0.00119 -0.1271 0.5570 0.0745
-0.750 0.5189 0.00783 0.00116 -0.1272 0.5456 0.0819
-0.250 0.5747 0.00790 0.00115 -0.1276 0.5256 0.0917
0.000 0.6025 0.00794 0.00112 -0.1277 0.5169 0.0923
0.250 0.6303 0.00797 0.00111 -0.1279 0.5080 0.0946
0.500 0.6583 0.00799 0.00112 -0.1280 0.5010 0.0980
0.750 0.6859 0.00804 0.00115 -0.1282 0.4919 0.1017
1.000 0.7137 0.00809 0.00117 -0.1283 0.4825 0.1058
1.250 0.7413 0.00815 0.00122 -0.1285 0.4734 0.1127
1.750 0.7963 0.00828 0.00135 -0.1288 0.4520 0.1361
2.250 0.8501 0.00821 0.00165 -0.1292 0.4152 0.3781
2.750 0.8982 0.00745 0.00207 -0.1284 0.3750 1.0000
3.000 0.9242 0.00774 0.00225 -0.1283 0.3511 1.0000
3.250 0.9459 0.00852 0.00265 -0.1276 0.2825 1.0000
3.500 0.9609 0.01010 0.00355 -0.1259 0.1355 1.0000
3.750 0.9831 0.01079 0.00401 -0.1253 0.0688 1.0000
4.000 1.0065 0.01133 0.00441 -0.1247 0.0197 1.0000
4.250 1.0317 0.01165 0.00470 -0.1245 0.0095 1.0000
4.500 1.0570 0.01195 0.00505 -0.1242 0.0069 1.0000
4.750 1.0813 0.01234 0.00545 -0.1237 0.0050 1.0000
5.000 1.1058 0.01268 0.00582 -0.1234 0.0040 1.0000
5.250 1.1295 0.01310 0.00627 -0.1229 0.0034 1.0000
5.500 1.1513 0.01372 0.00699 -0.1220 0.0029 1.0000
5.750 1.1726 0.01436 0.00772 -0.1210 0.0026 1.0000
6.000 1.1929 0.01504 0.00849 -0.1198 0.0024 1.0000
6.250 1.2149 0.01550 0.00898 -0.1191 0.0020 1.0000
6.500 1.2347 0.01613 0.00966 -0.1181 0.0018 1.0000
6.750 1.2471 0.01733 0.01099 -0.1157 0.0016 1.0000
7.000 1.2609 0.01831 0.01208 -0.1135 0.0015 1.0000
7.250 1.2704 0.01953 0.01342 -0.1107 0.0014 1.0000
7.500 1.2720 0.02100 0.01503 -0.1064 0.0013 1.0000
7.750 1.2718 0.02286 0.01704 -0.1020 0.0011 1.0000
8.000 1.2802 0.02592 0.02020 -0.0983 0.0010 1.0000
8.250 1.3391 0.03154 0.02598 -0.1015 0.0011 1.0000
8.500 1.3661 0.03528 0.02995 -0.1006 0.0011 1.0000
8.750 1.3852 0.03863 0.03354 -0.0988 0.0012 1.0000
9.000 1.3989 0.04186 0.03700 -0.0965 0.0013 1.0000
9.250 1.4079 0.04501 0.04039 -0.0938 0.0014 1.0000
9.500 1.4119 0.04817 0.04376 -0.0909 0.0015 1.0000
9.750 1.4002 0.05251 0.04835 -0.0871 0.0016 1.0000
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Polar data table (+)
Polar graphs
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