GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 200,000 Max Cl/Cd: 82.3 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610bm-il-200000-n5.txt Download as CSV file: xf-goe610bm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2782 0.10181 0.09851 -0.0283 1.0000 0.0205
-7.750 -0.2742 0.09947 0.09623 -0.0296 1.0000 0.0214
-7.500 -0.2765 0.09786 0.09469 -0.0295 1.0000 0.0219
-7.250 -0.2612 0.09449 0.09134 -0.0350 0.9881 0.0222
-7.000 -0.2404 0.09042 0.08727 -0.0418 0.9776 0.0223
-6.750 -0.2187 0.08616 0.08300 -0.0482 0.9677 0.0224
-6.500 -0.1966 0.08177 0.07857 -0.0540 0.9582 0.0224
-6.000 -0.1524 0.07306 0.06979 -0.0647 0.9376 0.0224
-5.750 -0.1381 0.06890 0.06560 -0.0663 0.9268 0.0217
-5.500 -0.1217 0.06481 0.06148 -0.0689 0.9156 0.0196
-5.250 -0.0962 0.06017 0.05676 -0.0749 0.9044 0.0182
-5.000 -0.0665 0.05526 0.05175 -0.0815 0.8947 0.0176
-4.750 -0.0343 0.05047 0.04683 -0.0881 0.8846 0.0175
-4.500 -0.0010 0.04626 0.04247 -0.0937 0.8751 0.0186
-4.250 0.0375 0.04136 0.03735 -0.1001 0.8666 0.0206
-4.000 0.0790 0.03551 0.03115 -0.1065 0.8573 0.0212
-3.750 0.1237 0.02858 0.02360 -0.1123 0.8495 0.0236
-3.500 0.1479 0.02810 0.02308 -0.1128 0.8391 0.0258
-3.250 0.1815 0.02512 0.01971 -0.1149 0.8291 0.0275
-3.000 0.2148 0.02259 0.01671 -0.1163 0.8192 0.0308
-2.750 0.2472 0.02065 0.01422 -0.1170 0.8092 0.0331
-2.500 0.2784 0.01901 0.01208 -0.1178 0.7982 0.0350
-2.250 0.3074 0.01760 0.01043 -0.1184 0.7873 0.0378
-2.000 0.3367 0.01659 0.00913 -0.1186 0.7763 0.0387
-1.500 0.3944 0.01514 0.00719 -0.1187 0.7537 0.0406
-1.250 0.4228 0.01472 0.00660 -0.1187 0.7420 0.0427
-1.000 0.4512 0.01428 0.00598 -0.1186 0.7302 0.0438
-0.750 0.4795 0.01381 0.00539 -0.1186 0.7184 0.0435
-0.250 0.5361 0.01312 0.00450 -0.1186 0.6930 0.0435
0.000 0.5645 0.01287 0.00418 -0.1186 0.6790 0.0438
0.250 0.5928 0.01268 0.00392 -0.1187 0.6643 0.0443
0.500 0.6211 0.01256 0.00370 -0.1187 0.6487 0.0452
0.750 0.6491 0.01249 0.00352 -0.1187 0.6317 0.0466
1.000 0.6772 0.01244 0.00337 -0.1187 0.6141 0.0493
1.250 0.7051 0.01241 0.00327 -0.1187 0.5974 0.0569
1.500 0.7332 0.01218 0.00331 -0.1190 0.5823 0.1950
2.000 0.7812 0.01085 0.00338 -0.1175 0.5576 1.0000
2.250 0.8087 0.01105 0.00347 -0.1174 0.5471 1.0000
2.500 0.8363 0.01127 0.00358 -0.1174 0.5376 1.0000
3.000 0.8912 0.01171 0.00388 -0.1174 0.5212 1.0000
3.500 0.9460 0.01216 0.00424 -0.1174 0.5063 1.0000
3.750 0.9730 0.01242 0.00446 -0.1173 0.4975 1.0000
4.000 0.9999 0.01266 0.00467 -0.1172 0.4862 1.0000
4.250 1.0267 0.01288 0.00488 -0.1171 0.4748 1.0000
4.500 1.0535 0.01312 0.00514 -0.1170 0.4656 1.0000
4.750 1.0803 0.01334 0.00538 -0.1169 0.4566 1.0000
5.000 1.1071 0.01356 0.00565 -0.1168 0.4479 1.0000
5.250 1.1332 0.01380 0.00589 -0.1166 0.4339 1.0000
5.500 1.1579 0.01407 0.00612 -0.1162 0.4048 1.0000
5.750 1.1819 0.01443 0.00636 -0.1157 0.3690 1.0000
6.000 1.2049 0.01495 0.00669 -0.1152 0.3239 1.0000
6.250 1.2222 0.01617 0.00735 -0.1140 0.2293 1.0000
6.500 1.2366 0.01786 0.00848 -0.1125 0.1427 1.0000
6.750 1.2543 0.01907 0.00940 -0.1114 0.0960 1.0000
7.000 1.2657 0.02092 0.01077 -0.1093 0.0221 1.0000
7.250 1.2845 0.02185 0.01177 -0.1080 0.0175 1.0000
7.500 1.3038 0.02268 0.01277 -0.1067 0.0148 1.0000
7.750 1.3219 0.02359 0.01387 -0.1053 0.0136 1.0000
8.000 1.3394 0.02449 0.01499 -0.1038 0.0130 1.0000
8.250 1.3551 0.02549 0.01615 -0.1021 0.0119 1.0000
8.500 1.3686 0.02661 0.01743 -0.1001 0.0109 1.0000
8.750 1.3791 0.02787 0.01886 -0.0977 0.0103 1.0000
9.000 1.3852 0.02926 0.02041 -0.0947 0.0099 1.0000
9.250 1.3870 0.03086 0.02215 -0.0913 0.0096 1.0000
9.500 1.3868 0.03277 0.02420 -0.0881 0.0094 1.0000
9.750 1.3848 0.03500 0.02654 -0.0852 0.0092 1.0000
10.000 1.3812 0.03755 0.02919 -0.0825 0.0090 1.0000
10.250 1.3770 0.04038 0.03209 -0.0800 0.0088 1.0000
10.500 1.3783 0.04284 0.03463 -0.0780 0.0086 1.0000
10.750 1.3860 0.04465 0.03665 -0.0768 0.0082 1.0000
11.000 1.3917 0.04672 0.03887 -0.0755 0.0077 1.0000
11.250 1.3957 0.04907 0.04134 -0.0741 0.0074 1.0000
11.500 1.3996 0.05153 0.04391 -0.0727 0.0072 1.0000
11.750 1.4038 0.05401 0.04651 -0.0713 0.0070 1.0000
12.000 1.4084 0.05653 0.04916 -0.0700 0.0069 1.0000
12.250 1.4128 0.05914 0.05190 -0.0687 0.0068 1.0000
12.500 1.4164 0.06189 0.05479 -0.0675 0.0067 1.0000
12.750 1.4187 0.06484 0.05791 -0.0664 0.0066 1.0000
13.000 1.4195 0.06803 0.06128 -0.0656 0.0065 1.0000
13.250 1.4182 0.07149 0.06493 -0.0649 0.0065 1.0000
13.500 1.4151 0.07521 0.06885 -0.0645 0.0064 1.0000
13.750 1.4100 0.07924 0.07309 -0.0644 0.0064 1.0000
14.000 1.4031 0.08360 0.07767 -0.0647 0.0064 1.0000
14.250 1.3944 0.08829 0.08259 -0.0654 0.0064 1.0000
14.500 1.3845 0.09338 0.08790 -0.0665 0.0064 1.0000
14.750 1.3735 0.09886 0.09360 -0.0681 0.0064 1.0000
15.000 1.3615 0.10471 0.09968 -0.0703 0.0064 1.0000
15.250 1.3487 0.11094 0.10613 -0.0730 0.0065 1.0000
15.500 1.3357 0.11749 0.11289 -0.0761 0.0065 1.0000
15.750 1.3225 0.12439 0.12001 -0.0798 0.0065 1.0000
16.000 1.3092 0.13168 0.12749 -0.0839 0.0065 1.0000
16.250 1.2957 0.13941 0.13542 -0.0887 0.0066 1.0000
16.500 1.2823 0.14751 0.14370 -0.0938 0.0066 1.0000
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Polar data table (+)
Polar graphs
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