GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 500,000 Max Cl/Cd: 107.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe124-il-500000-n5.txt Download as CSV file: xf-goe124-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2852 0.09012 0.08769 -0.0278 0.8806 0.0144
-7.750 -0.2785 0.08708 0.08459 -0.0295 0.8636 0.0147
-7.500 -0.2715 0.08400 0.08145 -0.0315 0.8482 0.0150
-7.250 -0.2598 0.07765 0.07503 -0.0401 0.8340 0.0161
-7.000 -0.2452 0.07588 0.07321 -0.0409 0.8212 0.0165
-6.750 -0.2284 0.07383 0.07110 -0.0431 0.8084 0.0170
-6.500 -0.2098 0.07078 0.06800 -0.0470 0.7962 0.0177
-6.250 -0.1889 0.06699 0.06413 -0.0522 0.7852 0.0180
-6.000 -0.1656 0.06301 0.06006 -0.0578 0.7746 0.0184
-5.750 -0.1316 0.05672 0.05363 -0.0682 0.7644 0.0201
-5.500 -0.1122 0.05562 0.05249 -0.0687 0.7543 0.0209
-5.000 -0.0548 0.04898 0.04564 -0.0778 0.7356 0.0222
-4.750 -0.0223 0.04500 0.04150 -0.0831 0.7263 0.0223
-4.500 0.0125 0.04101 0.03732 -0.0882 0.7163 0.0230
-4.250 0.0515 0.03622 0.03227 -0.0938 0.7069 0.0237
-4.000 0.0869 0.03214 0.02791 -0.0977 0.6976 0.0238
-3.750 0.1255 0.02691 0.02226 -0.1017 0.6889 0.0248
-3.500 0.1518 0.02620 0.02148 -0.1026 0.6796 0.0253
-3.250 0.1797 0.02524 0.02042 -0.1035 0.6698 0.0261
-3.000 0.2155 0.02159 0.01632 -0.1057 0.6608 0.0257
-2.750 0.2468 0.01978 0.01422 -0.1068 0.6510 0.0259
-2.500 0.2780 0.01817 0.01235 -0.1077 0.6424 0.0260
-2.250 0.3089 0.01682 0.01072 -0.1085 0.6355 0.0262
-2.000 0.3389 0.01595 0.00968 -0.1090 0.6284 0.0267
-1.750 0.3691 0.01505 0.00856 -0.1095 0.6211 0.0271
-1.500 0.3996 0.01404 0.00734 -0.1100 0.6139 0.0270
-1.250 0.4295 0.01328 0.00638 -0.1103 0.6067 0.0272
-1.000 0.4591 0.01267 0.00563 -0.1106 0.6003 0.0276
-0.750 0.4885 0.01218 0.00502 -0.1109 0.5932 0.0280
-0.500 0.5176 0.01178 0.00452 -0.1111 0.5867 0.0285
-0.250 0.5467 0.01143 0.00411 -0.1112 0.5790 0.0289
0.000 0.5756 0.01116 0.00376 -0.1114 0.5715 0.0292
0.250 0.6045 0.01099 0.00354 -0.1115 0.5627 0.0299
0.500 0.6331 0.01088 0.00340 -0.1117 0.5546 0.0304
0.750 0.6620 0.01069 0.00318 -0.1118 0.5458 0.0306
1.000 0.6911 0.01037 0.00284 -0.1121 0.5374 0.0310
1.250 0.7201 0.01019 0.00264 -0.1124 0.5281 0.0318
1.500 0.7489 0.01010 0.00254 -0.1126 0.5165 0.0326
1.750 0.7773 0.01009 0.00248 -0.1127 0.5021 0.0336
2.000 0.8057 0.01011 0.00247 -0.1128 0.4875 0.0347
2.250 0.8339 0.01015 0.00247 -0.1129 0.4736 0.0358
2.500 0.8619 0.01025 0.00250 -0.1130 0.4573 0.0376
2.750 0.8895 0.01040 0.00257 -0.1130 0.4366 0.0393
3.000 0.9172 0.01054 0.00262 -0.1130 0.4164 0.0425
3.250 0.9448 0.01070 0.00272 -0.1131 0.3993 0.0489
3.750 0.9939 0.00944 0.00319 -0.1123 0.3751 1.0000
4.000 1.0212 0.00967 0.00334 -0.1122 0.3630 1.0000
4.250 1.0486 0.00989 0.00351 -0.1122 0.3534 1.0000
4.750 1.1030 0.01033 0.00389 -0.1122 0.3361 1.0000
5.000 1.1299 0.01059 0.00411 -0.1121 0.3269 1.0000
5.250 1.1569 0.01081 0.00432 -0.1120 0.3189 1.0000
5.500 1.1837 0.01106 0.00455 -0.1119 0.3117 1.0000
5.750 1.2104 0.01129 0.00478 -0.1119 0.3026 1.0000
6.000 1.2368 0.01156 0.00504 -0.1117 0.2919 1.0000
6.250 1.2630 0.01185 0.00530 -0.1116 0.2810 1.0000
6.500 1.2888 0.01216 0.00558 -0.1114 0.2660 1.0000
6.750 1.3123 0.01275 0.00597 -0.1110 0.2234 1.0000
7.250 1.3517 0.01484 0.00745 -0.1092 0.1254 1.0000
7.500 1.3752 0.01533 0.00793 -0.1087 0.1158 1.0000
7.750 1.3987 0.01580 0.00841 -0.1082 0.1079 1.0000
8.000 1.4211 0.01637 0.00894 -0.1076 0.0981 1.0000
8.250 1.4446 0.01678 0.00938 -0.1071 0.0917 1.0000
8.500 1.4667 0.01732 0.00990 -0.1064 0.0836 1.0000
8.750 1.4880 0.01790 0.01045 -0.1057 0.0724 1.0000
9.000 1.5072 0.01865 0.01111 -0.1046 0.0563 1.0000
9.250 1.5240 0.01956 0.01193 -0.1033 0.0409 1.0000
9.500 1.5371 0.02074 0.01298 -0.1015 0.0231 1.0000
9.750 1.5513 0.02172 0.01396 -0.0997 0.0177 1.0000
10.000 1.5663 0.02256 0.01486 -0.0980 0.0154 1.0000
10.250 1.5790 0.02344 0.01580 -0.0961 0.0140 1.0000
10.500 1.5871 0.02444 0.01687 -0.0934 0.0129 1.0000
10.750 1.5963 0.02545 0.01796 -0.0910 0.0123 1.0000
11.000 1.6057 0.02653 0.01914 -0.0890 0.0117 1.0000
11.250 1.6141 0.02777 0.02049 -0.0871 0.0112 1.0000
11.500 1.6214 0.02918 0.02199 -0.0853 0.0107 1.0000
11.750 1.6274 0.03080 0.02370 -0.0836 0.0102 1.0000
12.000 1.6313 0.03271 0.02569 -0.0821 0.0097 1.0000
12.250 1.6331 0.03492 0.02801 -0.0806 0.0093 1.0000
12.500 1.6387 0.03685 0.03004 -0.0796 0.0090 1.0000
12.750 1.6429 0.03900 0.03230 -0.0786 0.0087 1.0000
13.000 1.6453 0.04140 0.03482 -0.0778 0.0085 1.0000
13.250 1.6465 0.04402 0.03755 -0.0771 0.0083 1.0000
13.500 1.6467 0.04682 0.04046 -0.0765 0.0080 1.0000
13.750 1.6456 0.04982 0.04358 -0.0760 0.0078 1.0000
14.000 1.6435 0.05301 0.04687 -0.0757 0.0077 1.0000
14.250 1.6401 0.05644 0.05041 -0.0755 0.0075 1.0000
14.500 1.6348 0.06014 0.05422 -0.0754 0.0073 1.0000
14.750 1.6282 0.06415 0.05835 -0.0756 0.0072 1.0000
15.000 1.6201 0.06853 0.06284 -0.0760 0.0071 1.0000
15.250 1.6102 0.07325 0.06769 -0.0766 0.0070 1.0000
15.500 1.5991 0.07830 0.07286 -0.0774 0.0069 1.0000
15.750 1.5905 0.08310 0.07778 -0.0783 0.0068 1.0000
16.000 1.5830 0.08783 0.08264 -0.0793 0.0067 1.0000
16.250 1.5749 0.09270 0.08764 -0.0804 0.0067 1.0000
16.500 1.5667 0.09770 0.09276 -0.0817 0.0066 1.0000
16.750 1.5586 0.10276 0.09795 -0.0831 0.0065 1.0000
17.000 1.5500 0.10796 0.10327 -0.0847 0.0064 1.0000
17.250 1.5416 0.11316 0.10859 -0.0864 0.0063 1.0000
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