GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 500,000 Max Cl/Cd: 99.96 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe574-il-500000.txt Download as CSV file: xf-goe574-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3423 0.10399 0.10193 -0.0292 1.0000 0.0158
-8.500 -0.3437 0.10106 0.09904 -0.0294 1.0000 0.0158
-8.250 -0.3463 0.09834 0.09635 -0.0293 1.0000 0.0158
-8.000 -0.3314 0.09355 0.09157 -0.0353 0.9972 0.0159
-7.750 -0.3232 0.08741 0.08544 -0.0398 0.9944 0.0162
-7.500 -0.3070 0.08395 0.08199 -0.0423 0.9909 0.0166
-7.250 -0.2889 0.07982 0.07784 -0.0479 0.9867 0.0170
-7.000 -0.2681 0.07539 0.07340 -0.0538 0.9816 0.0175
-6.750 -0.2437 0.07034 0.06832 -0.0611 0.9760 0.0183
-6.500 -0.2246 0.06557 0.06350 -0.0667 0.9678 0.0194
-6.250 -0.1961 0.05977 0.05758 -0.0749 0.9559 0.0213
-5.750 -0.1632 0.05072 0.04829 -0.0786 0.9181 0.0216
-5.500 -0.1366 0.04518 0.04254 -0.0821 0.9056 0.0217
-5.250 -0.1160 0.03712 0.03423 -0.0865 0.8942 0.0227
-5.000 -0.0721 0.03391 0.03084 -0.0925 0.8825 0.0237
-4.750 -0.0180 0.02999 0.02658 -0.1001 0.8673 0.0272
-4.500 0.0423 0.02697 0.02285 -0.1065 0.8473 0.0299
-4.250 0.0690 0.02111 0.01647 -0.1091 0.8257 0.0325
-4.000 0.0963 0.01993 0.01504 -0.1096 0.8042 0.0348
-3.750 0.1193 0.01881 0.01357 -0.1084 0.7854 0.0384
-3.000 0.1782 0.01423 0.00794 -0.1023 0.7351 0.0377
-2.750 0.1997 0.01321 0.00665 -0.1006 0.7179 0.0373
-2.500 0.2219 0.01270 0.00595 -0.0992 0.7006 0.0388
-2.250 0.2441 0.01219 0.00526 -0.0978 0.6835 0.0395
-2.000 0.2661 0.01173 0.00465 -0.0964 0.6662 0.0399
-1.750 0.2879 0.01132 0.00412 -0.0950 0.6487 0.0401
-1.500 0.3096 0.01108 0.00375 -0.0936 0.6311 0.0406
-1.250 0.3306 0.01078 0.00334 -0.0920 0.6139 0.0414
-1.000 0.3509 0.01047 0.00291 -0.0903 0.5975 0.0420
-0.750 0.3715 0.01025 0.00257 -0.0887 0.5816 0.0433
-0.500 0.3931 0.01014 0.00237 -0.0874 0.5663 0.0444
-0.250 0.4153 0.01009 0.00223 -0.0861 0.5521 0.0462
0.000 0.4382 0.01008 0.00213 -0.0851 0.5394 0.0478
0.250 0.4617 0.01007 0.00205 -0.0841 0.5285 0.0509
0.500 0.4853 0.01008 0.00201 -0.0832 0.5195 0.0574
0.750 0.5066 0.00988 0.00204 -0.0820 0.5116 0.1568
1.000 0.5009 0.00835 0.00217 -0.0752 0.5063 0.7419
1.250 0.7347 0.00902 0.00302 -0.1221 0.4908 1.0000
1.500 0.7576 0.00912 0.00307 -0.1211 0.4858 1.0000
1.750 0.7802 0.00927 0.00314 -0.1201 0.4812 1.0000
2.000 0.8035 0.00936 0.00322 -0.1192 0.4770 1.0000
2.250 0.8266 0.00946 0.00331 -0.1183 0.4732 1.0000
2.500 0.8496 0.00959 0.00340 -0.1174 0.4694 1.0000
2.750 0.8731 0.00976 0.00352 -0.1166 0.4660 1.0000
3.000 0.8957 0.00983 0.00362 -0.1156 0.4621 1.0000
3.250 0.9179 0.00993 0.00373 -0.1145 0.4572 1.0000
3.500 0.9405 0.01011 0.00386 -0.1135 0.4525 1.0000
3.750 0.9610 0.01016 0.00395 -0.1120 0.4456 1.0000
4.000 0.9809 0.01031 0.00405 -0.1104 0.4370 1.0000
4.250 1.0016 0.01036 0.00415 -0.1090 0.4307 1.0000
4.500 1.0218 0.01052 0.00429 -0.1075 0.4239 1.0000
4.750 1.0413 0.01057 0.00439 -0.1058 0.4148 1.0000
5.000 1.0602 0.01068 0.00451 -0.1040 0.4048 1.0000
5.250 1.0776 0.01078 0.00459 -0.1018 0.3882 1.0000
5.500 1.0932 0.01095 0.00470 -0.0993 0.3587 1.0000
5.750 1.0890 0.01222 0.00523 -0.0932 0.2283 1.0000
6.000 1.0708 0.01430 0.00648 -0.0846 0.0783 1.0000
6.250 1.0696 0.01523 0.00720 -0.0789 0.0253 1.0000
6.500 1.0804 0.01565 0.00768 -0.0754 0.0213 1.0000
6.750 1.0907 0.01611 0.00824 -0.0720 0.0196 1.0000
7.000 1.1018 0.01655 0.00876 -0.0687 0.0187 1.0000
7.250 1.1113 0.01710 0.00940 -0.0653 0.0176 1.0000
7.500 1.1203 0.01768 0.01005 -0.0618 0.0165 1.0000
7.750 1.1273 0.01837 0.01083 -0.0580 0.0158 1.0000
8.000 1.1321 0.01918 0.01173 -0.0540 0.0152 1.0000
8.250 1.1345 0.02014 0.01278 -0.0497 0.0147 1.0000
8.500 1.1315 0.02140 0.01414 -0.0448 0.0142 1.0000
8.750 1.1314 0.02260 0.01544 -0.0406 0.0141 1.0000
9.000 1.1270 0.02415 0.01709 -0.0362 0.0140 1.0000
9.250 1.1120 0.02659 0.01965 -0.0309 0.0135 1.0000
9.500 1.1139 0.02818 0.02130 -0.0282 0.0135 1.0000
9.750 1.1145 0.03010 0.02329 -0.0254 0.0134 1.0000
10.000 1.1310 0.03059 0.02389 -0.0247 0.0125 1.0000
10.250 1.1357 0.03227 0.02564 -0.0226 0.0123 1.0000
10.500 1.1412 0.03408 0.02751 -0.0204 0.0125 1.0000
10.750 1.1513 0.03555 0.02904 -0.0187 0.0122 1.0000
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Polar data table (+)
Polar graphs
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