GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 50,000 Max Cl/Cd: 35.71 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe574-il-50000-n5.txt Download as CSV file: xf-goe574-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3390 0.10366 0.09781 -0.0314 1.0000 0.1002
-7.250 -0.3539 0.10254 0.09685 -0.0313 1.0000 0.1010
-7.000 -0.3676 0.10131 0.09577 -0.0325 1.0000 0.1015
-6.750 -0.3576 0.09622 0.09070 -0.0281 1.0000 0.1043
-6.500 -0.3603 0.09372 0.08829 -0.0261 1.0000 0.1069
-6.250 -0.3674 0.09174 0.08641 -0.0247 1.0000 0.1092
-6.000 -0.3766 0.08995 0.08471 -0.0237 1.0000 0.1118
-5.750 -0.3466 0.08471 0.07938 -0.0349 0.9877 0.1174
-5.500 -0.3209 0.07993 0.07455 -0.0380 0.9779 0.1216
-5.250 -0.2952 0.07550 0.06997 -0.0463 0.9625 0.1315
-5.000 -0.2704 0.07167 0.06596 -0.0516 0.9483 0.1450
-4.750 -0.2329 0.06254 0.05641 -0.0573 0.9369 0.0699
-4.500 -0.2079 0.05779 0.05147 -0.0601 0.9243 0.0650
-4.250 -0.1743 0.05203 0.04498 -0.0643 0.9118 0.0579
-4.000 -0.1454 0.04786 0.04038 -0.0664 0.9011 0.0579
-3.750 -0.1181 0.04470 0.03714 -0.0680 0.8910 0.0625
-3.500 -0.0899 0.04127 0.03318 -0.0689 0.8793 0.0631
-3.250 -0.0596 0.03802 0.02937 -0.0697 0.8684 0.0631
-3.000 -0.0252 0.03540 0.02618 -0.0709 0.8594 0.0682
-2.750 0.0093 0.03287 0.02297 -0.0716 0.8495 0.0707
-2.500 0.0438 0.03071 0.02020 -0.0722 0.8386 0.0719
-2.250 0.0821 0.02878 0.01788 -0.0739 0.8292 0.0754
-2.000 0.1239 0.02741 0.01617 -0.0763 0.8196 0.0834
-1.750 0.1663 0.02609 0.01440 -0.0784 0.8081 0.0859
-1.500 0.2134 0.02495 0.01292 -0.0816 0.7968 0.0894
-1.250 0.2550 0.02411 0.01184 -0.0839 0.7849 0.0948
-1.000 0.2938 0.02343 0.01093 -0.0857 0.7727 0.1034
-0.500 0.4398 0.01995 0.00949 -0.1043 0.7481 1.0000
-0.250 0.4696 0.02011 0.00924 -0.1045 0.7337 1.0000
0.000 0.4980 0.02031 0.00910 -0.1046 0.7197 1.0000
0.250 0.5251 0.02053 0.00903 -0.1044 0.7064 1.0000
0.500 0.5518 0.02078 0.00903 -0.1042 0.6939 1.0000
0.750 0.5788 0.02103 0.00906 -0.1041 0.6825 1.0000
1.000 0.6078 0.02126 0.00907 -0.1043 0.6725 1.0000
1.250 0.6310 0.02161 0.00928 -0.1036 0.6617 1.0000
1.500 0.6557 0.02194 0.00949 -0.1031 0.6520 1.0000
1.750 0.6844 0.02221 0.00961 -0.1033 0.6439 1.0000
2.000 0.7056 0.02263 0.00998 -0.1023 0.6345 1.0000
2.250 0.7326 0.02297 0.01022 -0.1022 0.6273 1.0000
2.500 0.7546 0.02341 0.01065 -0.1014 0.6194 1.0000
2.750 0.7817 0.02378 0.01098 -0.1014 0.6132 1.0000
3.000 0.8014 0.02430 0.01153 -0.1001 0.6058 1.0000
3.250 0.8293 0.02465 0.01185 -0.1003 0.6003 1.0000
3.500 0.8463 0.02527 0.01255 -0.0986 0.5933 1.0000
3.750 0.8706 0.02575 0.01308 -0.0982 0.5880 1.0000
4.000 0.8924 0.02631 0.01371 -0.0973 0.5828 1.0000
4.250 0.9100 0.02698 0.01449 -0.0958 0.5769 1.0000
4.500 0.9352 0.02746 0.01507 -0.0955 0.5722 1.0000
4.750 0.9509 0.02822 0.01597 -0.0936 0.5667 1.0000
5.000 0.9686 0.02895 0.01684 -0.0922 0.5614 1.0000
5.250 0.9942 0.02946 0.01747 -0.0919 0.5572 1.0000
5.500 1.0047 0.03044 0.01868 -0.0893 0.5515 1.0000
5.750 1.0217 0.03123 0.01965 -0.0877 0.5462 1.0000
6.000 1.0493 0.03170 0.02028 -0.0877 0.5420 1.0000
6.250 1.0515 0.03297 0.02178 -0.0839 0.5352 1.0000
6.500 1.0754 0.03343 0.02245 -0.0832 0.5292 1.0000
6.750 1.0830 0.03442 0.02366 -0.0800 0.5214 1.0000
7.000 1.1074 0.03427 0.02375 -0.0787 0.5095 1.0000
7.250 1.1244 0.03225 0.02163 -0.0740 0.4744 1.0000
7.500 1.1394 0.03191 0.02141 -0.0708 0.4561 1.0000
7.750 1.1379 0.03194 0.02154 -0.0651 0.4335 1.0000
8.000 1.1334 0.03196 0.02157 -0.0588 0.4077 1.0000
8.250 1.1205 0.03248 0.02213 -0.0518 0.3797 1.0000
8.500 1.1079 0.03356 0.02336 -0.0459 0.3466 1.0000
8.750 1.0974 0.03463 0.02414 -0.0405 0.2643 1.0000
9.250 1.0495 0.04102 0.02918 -0.0313 0.0969 1.0000
9.500 1.0294 0.04499 0.03288 -0.0290 0.0757 1.0000
9.750 1.0135 0.04899 0.03683 -0.0273 0.0630 1.0000
10.000 1.0029 0.05270 0.04061 -0.0262 0.0568 1.0000
10.250 0.9940 0.05641 0.04447 -0.0255 0.0518 1.0000
10.500 0.9875 0.05995 0.04817 -0.0249 0.0486 1.0000
10.750 0.9799 0.06372 0.05205 -0.0245 0.0455 1.0000
11.000 0.9711 0.06770 0.05609 -0.0243 0.0430 1.0000
11.250 0.9675 0.07112 0.05968 -0.0240 0.0411 1.0000
11.500 0.9635 0.07461 0.06333 -0.0238 0.0397 1.0000
11.750 0.9599 0.07806 0.06692 -0.0236 0.0383 1.0000
12.000 0.9567 0.08148 0.07045 -0.0234 0.0371 1.0000
12.250 0.9549 0.08468 0.07373 -0.0231 0.0360 1.0000
12.500 0.9544 0.08760 0.07671 -0.0226 0.0350 1.0000
12.750 0.9591 0.08982 0.07905 -0.0217 0.0336 1.0000
13.000 0.9674 0.09154 0.08092 -0.0205 0.0319 1.0000
13.250 0.9786 0.09283 0.08236 -0.0190 0.0304 1.0000
13.500 0.9973 0.09305 0.08271 -0.0164 0.0291 1.0000
13.750 1.0378 0.09096 0.08086 -0.0114 0.0279 1.0000
14.000 1.0918 0.08992 0.08000 -0.0066 0.0265 1.0000
14.250 1.0939 0.09338 0.08380 -0.0064 0.0262 1.0000
14.500 1.0919 0.09729 0.08803 -0.0067 0.0259 1.0000
14.750 1.0876 0.10148 0.09250 -0.0074 0.0258 1.0000
15.000 1.0786 0.10619 0.09749 -0.0086 0.0255 1.0000
15.250 1.0687 0.11118 0.10274 -0.0103 0.0254 1.0000
15.500 1.0594 0.11628 0.10805 -0.0121 0.0255 1.0000
15.750 1.0495 0.12157 0.11354 -0.0143 0.0256 1.0000
16.000 1.0371 0.12750 0.11966 -0.0171 0.0257 1.0000
16.250 1.0248 0.13366 0.12599 -0.0203 0.0258 1.0000
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Polar data table (+)
Polar graphs
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