GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 200,000 Max Cl/Cd: 77.76 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe117-il-200000-n5.txt Download as CSV file: xf-goe117-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3391 0.09887 0.09540 -0.0411 1.0000 0.0138
-9.250 -0.3390 0.09569 0.09227 -0.0415 1.0000 0.0137
-9.000 -0.3408 0.09201 0.08864 -0.0425 1.0000 0.0142
-8.000 -0.3398 0.07607 0.07292 -0.0508 0.9845 0.0142
-7.750 -0.3314 0.06931 0.06620 -0.0587 0.9693 0.0143
-7.250 -0.3011 0.04757 0.04427 -0.0859 0.9428 0.0143
-7.000 -0.2828 0.03163 0.02735 -0.1019 0.9298 0.0144
-6.750 -0.2567 0.02817 0.02349 -0.1051 0.9221 0.0154
-6.500 -0.2276 0.02700 0.02212 -0.1068 0.9144 0.0169
-6.250 -0.2006 0.02436 0.01894 -0.1082 0.9066 0.0187
-6.000 -0.1736 0.02164 0.01561 -0.1091 0.8986 0.0205
-5.750 -0.1457 0.02023 0.01374 -0.1094 0.8899 0.0225
-5.500 -0.1182 0.01852 0.01176 -0.1100 0.8818 0.0253
-5.250 -0.0919 0.01757 0.01061 -0.1099 0.8720 0.0279
-5.000 -0.0646 0.01684 0.00963 -0.1099 0.8627 0.0315
-4.750 -0.0364 0.01625 0.00876 -0.1099 0.8537 0.0338
-4.500 -0.0117 0.01509 0.00748 -0.1095 0.8435 0.0369
-4.250 0.0145 0.01453 0.00683 -0.1093 0.8334 0.0400
-4.000 0.0409 0.01400 0.00616 -0.1090 0.8229 0.0417
-3.750 0.0673 0.01361 0.00560 -0.1086 0.8115 0.0441
-3.500 0.0933 0.01324 0.00510 -0.1082 0.7990 0.0454
-3.250 0.1193 0.01289 0.00462 -0.1077 0.7859 0.0463
-3.000 0.1454 0.01252 0.00411 -0.1073 0.7723 0.0487
-2.750 0.1716 0.01223 0.00370 -0.1069 0.7578 0.0528
-2.500 0.1978 0.01198 0.00335 -0.1065 0.7423 0.0604
-2.250 0.2230 0.01152 0.00309 -0.1061 0.7259 0.1259
-2.000 0.2490 0.01141 0.00291 -0.1057 0.7089 0.1592
-1.750 0.2749 0.01132 0.00276 -0.1053 0.6925 0.1801
-1.500 0.3007 0.01124 0.00270 -0.1049 0.6783 0.2079
-1.250 0.3267 0.01124 0.00267 -0.1045 0.6662 0.2374
-1.000 0.3529 0.01125 0.00264 -0.1042 0.6554 0.2609
-0.750 0.3792 0.01127 0.00262 -0.1039 0.6456 0.2846
-0.500 0.4053 0.01128 0.00259 -0.1036 0.6371 0.3056
-0.250 0.4316 0.01128 0.00257 -0.1033 0.6292 0.3207
0.000 0.4580 0.01129 0.00256 -0.1031 0.6228 0.3359
0.500 0.5104 0.01128 0.00261 -0.1025 0.6105 0.3789
0.750 0.5360 0.01118 0.00268 -0.1022 0.6046 0.4305
1.000 0.5585 0.01070 0.00278 -0.1013 0.5995 0.6200
1.250 0.6073 0.01020 0.00286 -0.1054 0.5944 1.0000
1.500 0.6333 0.01033 0.00296 -0.1051 0.5890 1.0000
1.750 0.6593 0.01048 0.00307 -0.1047 0.5841 1.0000
2.000 0.6854 0.01065 0.00319 -0.1044 0.5793 1.0000
2.250 0.7113 0.01079 0.00333 -0.1041 0.5737 1.0000
2.500 0.7372 0.01096 0.00349 -0.1037 0.5685 1.0000
2.750 0.7632 0.01112 0.00366 -0.1034 0.5636 1.0000
3.000 0.7891 0.01127 0.00385 -0.1031 0.5585 1.0000
3.250 0.8152 0.01145 0.00406 -0.1028 0.5541 1.0000
3.500 0.8411 0.01163 0.00428 -0.1024 0.5495 1.0000
3.750 0.8656 0.01177 0.00445 -0.1018 0.5391 1.0000
4.000 0.8890 0.01190 0.00458 -0.1009 0.5243 1.0000
4.250 0.9128 0.01203 0.00478 -0.1000 0.5106 1.0000
4.500 0.9362 0.01218 0.00497 -0.0991 0.4953 1.0000
4.750 0.9588 0.01233 0.00517 -0.0981 0.4741 1.0000
5.000 0.9778 0.01258 0.00531 -0.0964 0.4254 1.0000
5.250 0.9833 0.01382 0.00582 -0.0926 0.2941 1.0000
5.500 0.9759 0.01654 0.00741 -0.0875 0.0802 1.0000
5.750 0.9913 0.01746 0.00820 -0.0856 0.0492 1.0000
6.000 1.0080 0.01822 0.00899 -0.0838 0.0374 1.0000
6.250 1.0248 0.01893 0.00980 -0.0821 0.0305 1.0000
6.500 1.0382 0.01981 0.01075 -0.0798 0.0256 1.0000
6.750 1.0510 0.02067 0.01175 -0.0775 0.0228 1.0000
7.000 1.0616 0.02156 0.01277 -0.0748 0.0202 1.0000
7.250 1.0694 0.02252 0.01378 -0.0717 0.0180 1.0000
7.500 1.0674 0.02413 0.01545 -0.0674 0.0164 1.0000
7.750 1.0747 0.02529 0.01672 -0.0646 0.0158 1.0000
8.000 1.0812 0.02663 0.01817 -0.0618 0.0151 1.0000
8.250 1.0885 0.02809 0.01973 -0.0593 0.0145 1.0000
8.500 1.0986 0.02947 0.02120 -0.0572 0.0135 1.0000
8.750 1.1102 0.03078 0.02259 -0.0555 0.0125 1.0000
9.000 1.1220 0.03202 0.02391 -0.0539 0.0116 1.0000
9.250 1.1346 0.03356 0.02552 -0.0524 0.0110 1.0000
9.500 1.1505 0.03551 0.02761 -0.0510 0.0105 1.0000
9.750 1.1794 0.03869 0.03100 -0.0507 0.0100 1.0000
10.000 1.2000 0.04110 0.03369 -0.0498 0.0097 1.0000
10.250 1.2161 0.04370 0.03659 -0.0486 0.0094 1.0000
10.500 1.2270 0.04630 0.03950 -0.0469 0.0090 1.0000
10.750 1.2332 0.04881 0.04229 -0.0449 0.0083 1.0000
11.000 1.2357 0.05177 0.04553 -0.0429 0.0080 1.0000
11.250 1.2337 0.05518 0.04923 -0.0408 0.0079 1.0000
11.500 1.2279 0.05886 0.05319 -0.0388 0.0078 1.0000
11.750 1.2187 0.06276 0.05735 -0.0370 0.0078 1.0000
12.000 1.2064 0.06709 0.06195 -0.0356 0.0078 1.0000
12.250 1.1925 0.07151 0.06661 -0.0348 0.0078 1.0000
12.500 1.1762 0.07641 0.07174 -0.0346 0.0078 1.0000
12.750 1.1587 0.08165 0.07719 -0.0351 0.0078 1.0000
13.000 1.1399 0.08739 0.08314 -0.0363 0.0078 1.0000
13.250 1.1205 0.09350 0.08943 -0.0383 0.0079 1.0000
13.500 1.1006 0.10008 0.09619 -0.0410 0.0080 1.0000
13.750 1.0800 0.10731 0.10358 -0.0444 0.0080 1.0000
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Polar data table (+)
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