GOE 738 AIRFOIL (goe738-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 738 AIRFOIL (goe738-il) Reynolds number: 50,000 Max Cl/Cd: 23.36 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe738-il-50000-n5.txt Download as CSV file: xf-goe738-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 738 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5294 0.10237 0.09483 -0.0171 1.0000 0.0935
-11.250 -0.5475 0.09390 0.08639 -0.0222 1.0000 0.0935
-11.000 -0.5954 0.08002 0.07248 -0.0323 1.0000 0.0933
-10.750 -0.6465 0.06969 0.06203 -0.0394 1.0000 0.0929
-10.500 -0.6866 0.06327 0.05544 -0.0415 1.0000 0.0928
-10.250 -0.7179 0.05876 0.05071 -0.0404 1.0000 0.0932
-10.000 -0.7394 0.05463 0.04625 -0.0390 1.0000 0.0940
-9.750 -0.7392 0.05185 0.04332 -0.0380 1.0000 0.0954
-9.500 -0.7270 0.05009 0.04156 -0.0375 1.0000 0.0972
-9.250 -0.7196 0.04794 0.03930 -0.0366 1.0000 0.0989
-9.000 -0.7142 0.04574 0.03692 -0.0354 1.0000 0.1007
-8.750 -0.7131 0.04378 0.03474 -0.0333 1.0000 0.1024
-8.500 -0.6930 0.04092 0.03131 -0.0348 0.9660 0.1060
-8.250 -0.6583 0.03949 0.02992 -0.0372 0.9474 0.1096
-8.000 -0.6275 0.03781 0.02802 -0.0389 0.9313 0.1138
-7.750 -0.6005 0.03596 0.02569 -0.0398 0.9164 0.1189
-7.500 -0.5711 0.03500 0.02478 -0.0406 0.9027 0.1234
-7.250 -0.5459 0.03388 0.02344 -0.0406 0.8894 0.1291
-7.000 -0.5225 0.03288 0.02229 -0.0401 0.8762 0.1350
-6.750 -0.4994 0.03213 0.02146 -0.0395 0.8641 0.1416
-6.500 -0.4756 0.03126 0.02041 -0.0387 0.8534 0.1493
-6.250 -0.4535 0.03060 0.01974 -0.0379 0.8417 0.1577
-6.000 -0.4304 0.02990 0.01896 -0.0371 0.8313 0.1674
-5.750 -0.4075 0.02928 0.01821 -0.0361 0.8213 0.1799
-5.500 -0.3851 0.02869 0.01769 -0.0353 0.8113 0.1925
-5.250 -0.3627 0.02814 0.01713 -0.0342 0.8023 0.2078
-5.000 -0.3404 0.02763 0.01666 -0.0334 0.7923 0.2252
-4.750 -0.3181 0.02716 0.01617 -0.0324 0.7842 0.2452
-4.500 -0.2958 0.02676 0.01579 -0.0316 0.7745 0.2671
-4.250 -0.2741 0.02632 0.01544 -0.0304 0.7667 0.2905
-4.000 -0.2526 0.02595 0.01518 -0.0295 0.7576 0.3176
-3.750 -0.2317 0.02555 0.01493 -0.0282 0.7499 0.3504
-3.500 -0.2116 0.02519 0.01478 -0.0269 0.7417 0.3908
-3.250 -0.1918 0.02483 0.01469 -0.0254 0.7336 0.4391
-3.000 -0.1715 0.02453 0.01465 -0.0235 0.7270 0.4948
-2.750 -0.1502 0.02443 0.01482 -0.0220 0.7183 0.5539
-2.500 -0.1261 0.02435 0.01490 -0.0202 0.7120 0.6138
-2.250 -0.1000 0.02451 0.01520 -0.0192 0.7040 0.6674
-2.000 -0.0727 0.02469 0.01541 -0.0181 0.6968 0.7154
-1.750 -0.0405 0.02485 0.01551 -0.0174 0.6915 0.7567
-1.500 -0.0095 0.02528 0.01594 -0.0176 0.6825 0.7927
-1.250 0.0275 0.02556 0.01611 -0.0181 0.6762 0.8248
-1.000 0.0684 0.02594 0.01640 -0.0195 0.6697 0.8530
-0.750 0.1132 0.02638 0.01675 -0.0220 0.6617 0.8792
-0.500 0.1585 0.02661 0.01681 -0.0241 0.6561 0.9038
-0.250 0.2098 0.02701 0.01714 -0.0284 0.6480 0.9244
0.000 0.2582 0.02715 0.01717 -0.0321 0.6409 0.9437
0.250 0.3046 0.02710 0.01698 -0.0353 0.6353 0.9615
0.500 0.3491 0.02738 0.01724 -0.0395 0.6261 0.9780
0.750 0.3938 0.02719 0.01694 -0.0428 0.6199 0.9918
1.000 0.4277 0.02736 0.01709 -0.0451 0.6113 1.0000
1.250 0.4439 0.02745 0.01712 -0.0436 0.6039 1.0000
1.500 0.4599 0.02754 0.01714 -0.0420 0.5962 1.0000
1.750 0.4753 0.02772 0.01728 -0.0404 0.5868 1.0000
2.000 0.4923 0.02768 0.01715 -0.0385 0.5793 1.0000
2.250 0.5071 0.02798 0.01744 -0.0369 0.5693 1.0000
2.500 0.5262 0.02781 0.01716 -0.0349 0.5633 1.0000
2.750 0.5392 0.02844 0.01783 -0.0334 0.5526 1.0000
3.000 0.5592 0.02832 0.01761 -0.0316 0.5468 1.0000
3.250 0.5717 0.02904 0.01838 -0.0300 0.5365 1.0000
3.500 0.5918 0.02902 0.01829 -0.0283 0.5301 1.0000
3.750 0.6050 0.02970 0.01900 -0.0267 0.5206 1.0000
4.000 0.6245 0.02980 0.01905 -0.0250 0.5134 1.0000
4.250 0.6392 0.03036 0.01964 -0.0233 0.5045 1.0000
4.500 0.6575 0.03064 0.01990 -0.0217 0.4966 1.0000
4.750 0.6744 0.03106 0.02032 -0.0200 0.4885 1.0000
5.000 0.6905 0.03153 0.02080 -0.0183 0.4795 1.0000
5.250 0.7092 0.03181 0.02108 -0.0167 0.4717 1.0000
5.500 0.7237 0.03242 0.02171 -0.0150 0.4620 1.0000
5.750 0.7427 0.03272 0.02200 -0.0134 0.4541 1.0000
6.000 0.7555 0.03349 0.02282 -0.0116 0.4446 1.0000
6.250 0.7763 0.03372 0.02303 -0.0102 0.4374 1.0000
6.500 0.7856 0.03472 0.02409 -0.0082 0.4272 1.0000
6.750 0.8071 0.03491 0.02427 -0.0069 0.4200 1.0000
7.000 0.8134 0.03612 0.02555 -0.0048 0.4099 1.0000
7.250 0.8392 0.03608 0.02547 -0.0037 0.4037 1.0000
7.500 0.8362 0.03798 0.02746 -0.0012 0.3933 1.0000
7.750 0.8712 0.03730 0.02676 -0.0006 0.3880 1.0000
8.000 0.8551 0.03999 0.02955 0.0024 0.3766 1.0000
8.250 0.8909 0.03912 0.02863 0.0032 0.3704 1.0000
8.500 0.8701 0.04201 0.03161 0.0064 0.3596 1.0000
8.750 0.8949 0.04177 0.03136 0.0077 0.3522 1.0000
9.000 0.8772 0.04453 0.03417 0.0103 0.3426 1.0000
9.250 0.8944 0.04491 0.03455 0.0116 0.3354 1.0000
9.500 0.8814 0.04794 0.03764 0.0130 0.3261 1.0000
9.750 0.9018 0.04814 0.03785 0.0142 0.3197 1.0000
10.000 0.8816 0.05234 0.04213 0.0147 0.3100 1.0000
10.250 0.9259 0.05009 0.03988 0.0164 0.3051 1.0000
10.500 0.8807 0.05731 0.04720 0.0158 0.2938 1.0000
10.750 0.9314 0.05393 0.04380 0.0180 0.2888 1.0000
11.000 0.8861 0.06168 0.05166 0.0167 0.2772 1.0000
11.250 0.8812 0.06488 0.05490 0.0166 0.2681 1.0000
11.500 0.9089 0.06358 0.05360 0.0183 0.2598 1.0000
11.750 0.8781 0.07040 0.06049 0.0166 0.2486 1.0000
12.000 0.9366 0.06466 0.05470 0.0202 0.2416 1.0000
12.250 0.8863 0.07446 0.06462 0.0171 0.2299 1.0000
12.500 0.9404 0.06929 0.05939 0.0205 0.2242 1.0000
12.750 0.8781 0.08146 0.07170 0.0159 0.2120 1.0000
13.000 0.9263 0.07692 0.06713 0.0192 0.2075 1.0000
13.250 0.8597 0.09070 0.08103 0.0135 0.1947 1.0000
13.500 0.9049 0.08621 0.07655 0.0167 0.1911 1.0000
13.750 0.8409 0.10073 0.09114 0.0103 0.1784 1.0000
14.000 0.8803 0.09689 0.08733 0.0132 0.1755 1.0000
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