GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 500,000 Max Cl/Cd: 99.58 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe92-il-500000.txt Download as CSV file: xf-goe92-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2954 0.10718 0.10512 -0.0204 1.0000 0.0116
-8.750 -0.2904 0.10428 0.10225 -0.0228 1.0000 0.0116
-8.500 -0.2859 0.10137 0.09937 -0.0251 1.0000 0.0116
-8.250 -0.2772 0.09669 0.09470 -0.0239 1.0000 0.0118
-8.000 -0.2704 0.09365 0.09169 -0.0240 1.0000 0.0121
-7.750 -0.2652 0.09105 0.08913 -0.0248 0.9992 0.0123
-7.500 -0.2468 0.08731 0.08539 -0.0296 0.9806 0.0128
-7.250 -0.2281 0.08345 0.08151 -0.0347 0.9593 0.0133
-7.000 -0.2116 0.07978 0.07780 -0.0393 0.9407 0.0137
-6.750 -0.1972 0.07636 0.07432 -0.0431 0.9252 0.0141
-6.500 -0.1812 0.07292 0.07081 -0.0473 0.9132 0.0146
-6.250 -0.1573 0.06923 0.06706 -0.0541 0.9026 0.0152
-6.000 -0.1297 0.06526 0.06300 -0.0616 0.8934 0.0153
-5.750 -0.1035 0.06130 0.05891 -0.0670 0.8852 0.0154
-5.500 -0.0781 0.05743 0.05493 -0.0709 0.8765 0.0154
-5.250 -0.0603 0.05255 0.04997 -0.0735 0.8687 0.0157
-5.000 -0.0457 0.04957 0.04696 -0.0739 0.8596 0.0160
-4.750 -0.0249 0.04678 0.04411 -0.0753 0.8501 0.0165
-4.500 -0.0003 0.04388 0.04109 -0.0774 0.8405 0.0173
-4.250 0.0275 0.04084 0.03790 -0.0795 0.8297 0.0186
-4.000 0.0700 0.03833 0.03504 -0.0818 0.8185 0.0202
-3.750 0.0981 0.03557 0.03204 -0.0826 0.8061 0.0203
-3.500 0.1228 0.03095 0.02716 -0.0837 0.7925 0.0206
-3.250 0.1442 0.02816 0.02427 -0.0843 0.7743 0.0212
-3.000 0.1682 0.02630 0.02224 -0.0845 0.7502 0.0219
-2.750 0.1938 0.02460 0.02026 -0.0844 0.7169 0.0234
-2.500 0.2251 0.02421 0.01936 -0.0831 0.6767 0.0268
-2.250 0.2522 0.02313 0.01777 -0.0824 0.6432 0.0271
-2.000 0.2757 0.01917 0.01351 -0.0828 0.6196 0.0285
-1.750 0.3012 0.01810 0.01223 -0.0827 0.5981 0.0301
-1.500 0.3288 0.01738 0.01125 -0.0823 0.5794 0.0338
0.500 0.5463 0.01202 0.00419 -0.0799 0.4290 0.0492
0.750 0.5728 0.01192 0.00395 -0.0795 0.4098 0.0484
1.000 0.5993 0.01160 0.00356 -0.0792 0.3948 0.0463
1.250 0.6258 0.01136 0.00324 -0.0790 0.3827 0.0454
1.500 0.6527 0.01124 0.00305 -0.0788 0.3731 0.0456
1.750 0.6795 0.01121 0.00295 -0.0786 0.3656 0.0461
2.000 0.7066 0.01118 0.00289 -0.0785 0.3594 0.0466
2.250 0.7334 0.01124 0.00289 -0.0783 0.3540 0.0480
2.500 0.7607 0.01126 0.00287 -0.0783 0.3495 0.0487
2.750 0.7879 0.01131 0.00289 -0.0782 0.3450 0.0505
3.000 0.8147 0.01143 0.00296 -0.0780 0.3406 0.0561
3.250 0.8407 0.00977 0.00324 -0.0782 0.3366 1.0000
3.500 0.8678 0.00990 0.00334 -0.0781 0.3326 1.0000
3.750 0.8944 0.01008 0.00348 -0.0779 0.3290 1.0000
4.000 0.9207 0.01031 0.00364 -0.0777 0.3257 1.0000
4.250 0.9472 0.01052 0.00382 -0.0776 0.3227 1.0000
4.500 0.9741 0.01066 0.00397 -0.0775 0.3197 1.0000
4.750 1.0008 0.01081 0.00415 -0.0774 0.3160 1.0000
5.000 1.0270 0.01103 0.00433 -0.0772 0.3119 1.0000
5.250 1.0536 0.01115 0.00446 -0.0772 0.3046 1.0000
5.500 1.0797 0.01132 0.00459 -0.0770 0.2972 1.0000
5.750 1.1062 0.01146 0.00477 -0.0769 0.2912 1.0000
6.000 1.1323 0.01162 0.00491 -0.0768 0.2820 1.0000
6.250 1.1589 0.01172 0.00504 -0.0767 0.2718 1.0000
6.500 1.1850 0.01190 0.00520 -0.0766 0.2597 1.0000
6.750 1.2090 0.01227 0.00539 -0.0763 0.2225 1.0000
7.000 1.2203 0.01419 0.00656 -0.0744 0.1168 1.0000
7.250 1.2306 0.01620 0.00804 -0.0724 0.0242 1.0000
7.500 1.2528 0.01678 0.00864 -0.0716 0.0186 1.0000
7.750 1.2752 0.01730 0.00928 -0.0709 0.0168 1.0000
8.000 1.2965 0.01792 0.01005 -0.0700 0.0154 1.0000
8.250 1.3163 0.01866 0.01092 -0.0690 0.0144 1.0000
8.500 1.3338 0.01959 0.01199 -0.0677 0.0136 1.0000
8.750 1.3482 0.02075 0.01329 -0.0659 0.0129 1.0000
9.000 1.3577 0.02220 0.01490 -0.0636 0.0125 1.0000
9.250 1.3571 0.02412 0.01700 -0.0600 0.0120 1.0000
9.500 1.3706 0.02487 0.01784 -0.0582 0.0115 1.0000
9.750 1.3762 0.02616 0.01923 -0.0557 0.0112 1.0000
10.000 1.3784 0.02780 0.02099 -0.0533 0.0110 1.0000
10.250 1.3787 0.02975 0.02305 -0.0511 0.0109 1.0000
10.500 1.3779 0.03197 0.02539 -0.0493 0.0107 1.0000
10.750 1.3759 0.03448 0.02802 -0.0478 0.0106 1.0000
11.000 1.3729 0.03728 0.03092 -0.0467 0.0105 1.0000
11.250 1.3694 0.04031 0.03406 -0.0458 0.0104 1.0000
11.500 1.3660 0.04350 0.03735 -0.0452 0.0104 1.0000
11.750 1.3630 0.04671 0.04067 -0.0446 0.0104 1.0000
12.000 1.3612 0.04978 0.04381 -0.0438 0.0106 1.0000
12.250 1.3613 0.05244 0.04653 -0.0424 0.0109 1.0000
12.500 1.3770 0.05318 0.04724 -0.0395 0.0129 1.0000
12.750 1.1644 0.06133 0.05622 -0.0341 0.0107 1.0000
13.000 1.1603 0.06512 0.06007 -0.0333 0.0108 1.0000
13.250 1.1604 0.06809 0.06310 -0.0319 0.0109 1.0000
13.500 1.1879 0.06655 0.06147 -0.0276 0.0128 1.0000
14.250 1.2225 0.07178 0.06713 -0.0210 0.0163 1.0000
14.500 1.2157 0.07567 0.07115 -0.0211 0.0159 1.0000
14.750 1.2084 0.07954 0.07515 -0.0212 0.0156 1.0000
15.000 1.1980 0.08358 0.07932 -0.0215 0.0152 1.0000
15.250 1.1876 0.08749 0.08336 -0.0220 0.0149 1.0000
15.500 1.1742 0.09139 0.08739 -0.0225 0.0146 1.0000
15.750 1.1532 0.09486 0.09102 -0.0227 0.0145 1.0000
16.000 1.1367 0.09848 0.09478 -0.0236 0.0144 1.0000
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Polar data table (+)
Polar graphs
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