GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 298 AIRFOIL (goe298-il) Reynolds number: 50,000 Max Cl/Cd: 27.64 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe298-il-50000.txt Download as CSV file: xf-goe298-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 298 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2694 0.12047 0.11293 -0.0203 1.0000 0.1999
-9.000 -0.2846 0.12120 0.11377 -0.0231 1.0000 0.2050
-8.750 -0.2779 0.11737 0.11002 -0.0239 1.0000 0.2074
-8.500 -0.2515 0.11220 0.10487 -0.0227 1.0000 0.2133
-8.250 -0.2496 0.11041 0.10317 -0.0234 1.0000 0.2208
-8.000 -0.2842 0.11301 0.10598 -0.0251 1.0000 0.2247
-7.750 -0.2465 0.10555 0.09852 -0.0237 1.0000 0.2298
-7.500 -0.2416 0.10335 0.09641 -0.0224 1.0000 0.2360
-7.250 -0.2629 0.10365 0.09689 -0.0197 1.0000 0.2411
-7.000 -0.3041 0.10573 0.09917 -0.0148 1.0000 0.2430
-6.750 -0.3485 0.10786 0.10148 -0.0104 1.0000 0.2439
-6.500 -0.3484 0.10455 0.09826 -0.0076 1.0000 0.2465
-6.250 -0.3315 0.10113 0.09488 -0.0049 1.0000 0.2526
-6.000 -0.3502 0.10075 0.09460 -0.0016 1.0000 0.2574
-5.750 -0.3837 0.10155 0.09552 -0.0009 1.0000 0.2627
-5.500 -0.3988 0.09985 0.09391 -0.0005 1.0000 0.2662
-5.250 -0.3884 0.09697 0.09109 0.0040 1.0000 0.2726
-5.000 -0.4050 0.09648 0.09065 0.0032 1.0000 0.2823
-4.750 -0.4102 0.09400 0.08824 0.0040 1.0000 0.2878
-4.250 -0.3756 0.08818 0.08243 0.0009 0.9898 0.3131
-4.000 -0.3575 0.08529 0.07953 -0.0032 0.9828 0.3302
-3.750 -0.3401 0.08266 0.07691 -0.0054 0.9760 0.3498
-3.500 -0.3211 0.08007 0.07433 -0.0064 0.9694 0.3716
-3.250 -0.3054 0.07778 0.07205 -0.0068 0.9631 0.3953
-3.000 -0.2953 0.07577 0.07006 -0.0080 0.9572 0.4261
-2.750 -0.2790 0.07341 0.06775 -0.0054 0.9528 0.4533
-2.500 -0.2755 0.07168 0.06608 -0.0017 0.9486 0.4906
-2.250 -0.2728 0.07005 0.06453 0.0043 0.9439 0.5343
-1.500 -0.0521 0.05969 0.05415 0.0042 0.9247 0.8461
-1.250 -0.0754 0.05910 0.05361 0.0080 0.9170 0.8315
-1.000 0.0671 0.05196 0.04398 -0.0792 0.8955 0.2891
-0.750 0.1315 0.04984 0.04140 -0.0867 0.8813 0.2788
-0.500 0.1714 0.04856 0.03984 -0.0898 0.8678 0.2765
-0.250 0.2074 0.04779 0.03881 -0.0922 0.8566 0.2769
0.000 0.2619 0.04676 0.03746 -0.0969 0.8461 0.2789
0.250 0.2844 0.04671 0.03720 -0.0970 0.8342 0.2818
0.500 0.3319 0.04609 0.03633 -0.1001 0.8232 0.2853
0.750 0.3632 0.04574 0.03601 -0.1008 0.8102 0.2918
1.000 0.3922 0.04575 0.03593 -0.1012 0.7964 0.2977
1.250 0.4389 0.04531 0.03529 -0.1033 0.7837 0.3056
1.500 0.4809 0.04478 0.03478 -0.1046 0.7695 0.3170
1.750 0.5093 0.04492 0.03480 -0.1042 0.7529 0.3256
2.000 0.5423 0.04475 0.03470 -0.1041 0.7365 0.3394
2.250 0.5821 0.04422 0.03423 -0.1043 0.7210 0.3598
2.500 0.6322 0.04265 0.03287 -0.1048 0.7087 0.3943
2.750 0.6579 0.04214 0.03284 -0.1035 0.6905 0.4546
3.000 0.6758 0.04110 0.03279 -0.0999 0.6729 1.0000
3.250 0.7032 0.04150 0.03281 -0.0985 0.6552 1.0000
3.500 0.7309 0.04179 0.03290 -0.0972 0.6388 1.0000
3.750 0.7783 0.04041 0.03129 -0.0964 0.6292 1.0000
4.000 0.7975 0.04130 0.03210 -0.0949 0.6118 1.0000
4.250 0.8159 0.04232 0.03305 -0.0935 0.5952 1.0000
4.500 0.8352 0.04333 0.03401 -0.0922 0.5803 1.0000
4.750 0.8856 0.04128 0.03180 -0.0912 0.5724 1.0000
5.000 0.8980 0.04285 0.03337 -0.0897 0.5562 1.0000
5.250 0.9122 0.04428 0.03478 -0.0882 0.5411 1.0000
5.500 0.9740 0.04073 0.03101 -0.0872 0.5332 1.0000
5.750 0.9871 0.04205 0.03236 -0.0855 0.5168 1.0000
6.000 1.0010 0.04334 0.03366 -0.0839 0.5014 1.0000
6.250 1.0288 0.04323 0.03350 -0.0825 0.4880 1.0000
6.500 1.0770 0.04109 0.03116 -0.0816 0.4763 1.0000
6.750 1.0857 0.04287 0.03305 -0.0798 0.4611 1.0000
7.000 1.1004 0.04412 0.03434 -0.0782 0.4472 1.0000
7.250 1.1323 0.04368 0.03382 -0.0771 0.4344 1.0000
7.500 1.1731 0.04244 0.03240 -0.0764 0.4216 1.0000
7.750 1.1804 0.04437 0.03445 -0.0745 0.4076 1.0000
8.000 1.1948 0.04572 0.03584 -0.0728 0.3946 1.0000
8.250 1.2258 0.04571 0.03573 -0.0719 0.3823 1.0000
8.500 1.2606 0.04560 0.03546 -0.0714 0.3704 1.0000
8.750 1.2508 0.04944 0.03957 -0.0689 0.3598 1.0000
9.000 1.2905 0.04937 0.03928 -0.0688 0.3496 1.0000
9.250 1.2565 0.05519 0.04551 -0.0654 0.3416 1.0000
9.500 1.3153 0.05395 0.04399 -0.0662 0.3323 1.0000
9.750 1.1767 0.06916 0.05981 -0.0611 0.3304 1.0000
10.000 0.8113 0.13236 0.12335 -0.0924 0.3934 1.0000
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Polar data table (+)
Polar graphs
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