GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 500,000 Max Cl/Cd: 98.68 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe374-il-500000.txt Download as CSV file: xf-goe374-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3421 0.08785 0.08573 -0.0157 1.0000 0.0113
-7.250 -0.3431 0.08551 0.08343 -0.0156 1.0000 0.0117
-7.000 -0.3404 0.08289 0.08085 -0.0169 1.0000 0.0125
-6.750 -0.3348 0.08019 0.07817 -0.0189 1.0000 0.0126
-6.500 -0.3274 0.07756 0.07555 -0.0219 1.0000 0.0128
-6.250 -0.3193 0.07497 0.07296 -0.0251 1.0000 0.0129
-6.000 -0.3127 0.07240 0.07039 -0.0265 0.9999 0.0129
-5.750 -0.2754 0.06735 0.06526 -0.0345 0.9964 0.0130
-5.500 -0.2575 0.06175 0.05967 -0.0371 0.9929 0.0133
-5.250 -0.2301 0.05767 0.05555 -0.0414 0.9883 0.0135
-5.000 -0.1965 0.05365 0.05147 -0.0469 0.9844 0.0139
-4.750 -0.1631 0.04982 0.04754 -0.0519 0.9790 0.0145
-4.500 -0.1271 0.04595 0.04357 -0.0568 0.9737 0.0153
-4.250 -0.0816 0.04220 0.03963 -0.0622 0.9700 0.0169
-4.000 -0.0394 0.03920 0.03636 -0.0652 0.9615 0.0173
-3.750 -0.0018 0.03575 0.03266 -0.0679 0.9550 0.0174
-2.250 0.1595 0.02245 0.01803 -0.0683 0.8657 0.0233
-2.000 0.1807 0.01860 0.01389 -0.0675 0.8470 0.0242
-1.750 0.2038 0.01728 0.01243 -0.0670 0.8255 0.0255
-1.500 0.2287 0.01647 0.01140 -0.0661 0.8011 0.0288
-1.250 0.2567 0.01699 0.01152 -0.0646 0.7731 0.0312
-1.000 0.2789 0.01413 0.00838 -0.0638 0.7428 0.0335
-0.750 0.3031 0.01346 0.00750 -0.0629 0.7065 0.0364
0.750 0.1968 0.00728 0.00105 -0.0311 0.6601 0.0403
1.000 0.4811 0.01017 0.00298 -0.0576 0.5380 0.0496
1.250 0.5059 0.00989 0.00256 -0.0568 0.5102 0.0464
1.500 0.5309 0.00979 0.00233 -0.0561 0.4857 0.0456
1.750 0.5562 0.00973 0.00219 -0.0556 0.4674 0.0464
2.000 0.5819 0.00972 0.00209 -0.0550 0.4526 0.0449
2.250 0.6076 0.00975 0.00204 -0.0545 0.4385 0.0442
2.500 0.6334 0.00979 0.00201 -0.0541 0.4258 0.0444
2.750 0.6595 0.00985 0.00201 -0.0537 0.4145 0.0456
3.000 0.6857 0.00991 0.00203 -0.0533 0.4030 0.0484
3.250 0.7119 0.01000 0.00208 -0.0530 0.3920 0.0517
3.500 0.7334 0.00928 0.00229 -0.0521 0.3828 0.5570
3.750 0.7873 0.00851 0.00247 -0.0582 0.3696 1.0000
4.000 0.8130 0.00864 0.00258 -0.0577 0.3597 1.0000
4.250 0.8385 0.00880 0.00270 -0.0572 0.3499 1.0000
4.500 0.8638 0.00898 0.00283 -0.0567 0.3397 1.0000
4.750 0.8891 0.00915 0.00299 -0.0563 0.3287 1.0000
5.000 0.9145 0.00932 0.00315 -0.0558 0.3172 1.0000
5.250 0.9394 0.00953 0.00331 -0.0553 0.3015 1.0000
5.500 0.9641 0.00977 0.00349 -0.0548 0.2833 1.0000
5.750 0.9886 0.01004 0.00370 -0.0542 0.2635 1.0000
6.000 1.0123 0.01038 0.00397 -0.0536 0.2400 1.0000
6.250 1.0359 0.01075 0.00425 -0.0530 0.2173 1.0000
6.500 1.0585 0.01124 0.00458 -0.0522 0.1855 1.0000
6.750 1.0798 0.01189 0.00500 -0.0514 0.1478 1.0000
7.000 1.1013 0.01251 0.00548 -0.0505 0.1218 1.0000
7.250 1.1229 0.01312 0.00595 -0.0497 0.0964 1.0000
7.500 1.1362 0.01473 0.00706 -0.0477 0.0228 1.0000
7.750 1.1568 0.01547 0.00783 -0.0465 0.0169 1.0000
8.000 1.1781 0.01613 0.00867 -0.0454 0.0147 1.0000
8.250 1.1988 0.01680 0.00949 -0.0443 0.0140 1.0000
8.500 1.2183 0.01760 0.01043 -0.0430 0.0133 1.0000
8.750 1.2362 0.01852 0.01148 -0.0415 0.0125 1.0000
9.000 1.2525 0.01954 0.01261 -0.0399 0.0116 1.0000
9.250 1.2668 0.02069 0.01387 -0.0380 0.0110 1.0000
9.500 1.2776 0.02205 0.01534 -0.0358 0.0104 1.0000
9.750 1.2844 0.02366 0.01709 -0.0330 0.0100 1.0000
10.000 1.2879 0.02544 0.01898 -0.0298 0.0097 1.0000
10.250 1.2870 0.02732 0.02096 -0.0260 0.0096 1.0000
10.500 1.2820 0.03013 0.02387 -0.0220 0.0093 1.0000
10.750 1.2882 0.03238 0.02622 -0.0197 0.0093 1.0000
11.000 1.2975 0.03450 0.02844 -0.0178 0.0093 1.0000
11.250 1.3069 0.03654 0.03059 -0.0161 0.0093 1.0000
11.500 1.3137 0.03805 0.03221 -0.0142 0.0094 1.0000
11.750 1.3207 0.04071 0.03503 -0.0126 0.0094 1.0000
12.000 1.3249 0.04351 0.03799 -0.0110 0.0094 1.0000
12.250 1.3241 0.04772 0.04245 -0.0095 0.0093 1.0000
12.500 1.3237 0.04914 0.04398 -0.0080 0.0094 1.0000
12.750 1.3209 0.05130 0.04629 -0.0070 0.0095 1.0000
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Polar data table (+)
Polar graphs
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