GOE 738 AIRFOIL (goe738-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 738 AIRFOIL (goe738-il) Reynolds number: 50,000 Max Cl/Cd: 10.11 at α=-1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe738-il-50000.txt Download as CSV file: xf-goe738-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3810 0.11120 0.10437 0.0024 1.0000 0.3556
-9.250 -0.3413 0.10528 0.09843 0.0019 1.0000 0.3633
-9.000 -0.3594 0.10387 0.09715 0.0009 1.0000 0.3754
-8.750 -0.3265 0.09944 0.09271 0.0005 1.0000 0.3884
-8.500 -0.5882 0.06774 0.06097 -0.0326 1.0000 0.1926
-8.250 -0.5974 0.06452 0.05776 -0.0312 1.0000 0.1917
-8.000 -0.6206 0.06272 0.05599 -0.0268 1.0000 0.1908
-7.750 -0.6452 0.06088 0.05411 -0.0223 1.0000 0.1898
-7.500 -0.6674 0.05860 0.05172 -0.0182 1.0000 0.1889
-7.250 -0.6856 0.05602 0.04896 -0.0146 1.0000 0.1882
-7.000 -0.6994 0.05332 0.04601 -0.0112 1.0000 0.1878
-6.750 -0.7090 0.05066 0.04304 -0.0081 1.0000 0.1883
-6.500 -0.7151 0.04814 0.04014 -0.0052 1.0000 0.1899
-6.250 -0.6959 0.04488 0.03632 -0.0066 0.9917 0.1939
-6.000 -0.6576 0.04292 0.03438 -0.0098 0.9816 0.2007
-5.750 -0.6321 0.04070 0.03157 -0.0111 0.9712 0.2085
-5.500 -0.5987 0.03901 0.02985 -0.0132 0.9615 0.2174
-5.250 -0.5633 0.03732 0.02777 -0.0156 0.9522 0.2297
-5.000 -0.5365 0.03625 0.02660 -0.0162 0.9418 0.2423
-4.750 -0.5035 0.03517 0.02547 -0.0178 0.9326 0.2585
-4.500 -0.4715 0.03420 0.02441 -0.0191 0.9232 0.2788
-4.250 -0.4455 0.03339 0.02358 -0.0193 0.9139 0.3016
-4.000 -0.4090 0.03262 0.02296 -0.0210 0.9053 0.3353
-3.750 -0.3884 0.03212 0.02268 -0.0202 0.8962 0.3660
-3.500 -0.3521 0.03160 0.02234 -0.0217 0.8878 0.4133
-3.250 -0.3376 0.03140 0.02238 -0.0197 0.8791 0.4516
-3.000 -0.3048 0.03116 0.02257 -0.0202 0.8712 0.5141
-2.750 -0.2927 0.03116 0.02294 -0.0172 0.8631 0.5762
-2.500 -0.2669 0.03134 0.02368 -0.0150 0.8553 0.6720
-2.250 -0.2278 0.03234 0.02504 -0.0136 0.8479 0.7775
-2.000 -0.0349 0.03534 0.02761 -0.0348 0.8381 0.8785
-1.750 0.1345 0.03606 0.02788 -0.0565 0.8286 0.9296
-1.500 0.2716 0.03519 0.02670 -0.0752 0.8193 0.9754
-1.250 0.3433 0.03457 0.02594 -0.0854 0.8092 1.0000
-1.000 0.3537 0.03499 0.02626 -0.0844 0.8006 1.0000
-0.750 0.3487 0.03603 0.02726 -0.0821 0.7913 1.0000
-0.500 0.3585 0.03658 0.02773 -0.0807 0.7830 1.0000
-0.250 0.3485 0.03777 0.02888 -0.0774 0.7739 1.0000
0.000 0.3555 0.03847 0.02951 -0.0755 0.7655 1.0000
0.250 0.3422 0.03971 0.03070 -0.0715 0.7566 1.0000
0.500 0.3501 0.04039 0.03131 -0.0694 0.7473 1.0000
0.750 0.3325 0.04163 0.03250 -0.0645 0.7380 1.0000
1.000 0.3543 0.04206 0.03285 -0.0635 0.7276 1.0000
1.250 0.3224 0.04350 0.03422 -0.0568 0.7180 1.0000
1.500 0.3651 0.04367 0.03431 -0.0578 0.7069 1.0000
1.750 0.3178 0.04535 0.03592 -0.0495 0.6974 1.0000
2.000 0.3479 0.04594 0.03644 -0.0493 0.6863 1.0000
2.250 0.3236 0.04725 0.03765 -0.0433 0.6764 1.0000
2.500 0.3369 0.04822 0.03855 -0.0415 0.6656 1.0000
2.750 0.3546 0.04906 0.03933 -0.0401 0.6541 1.0000
3.000 0.3373 0.05056 0.04074 -0.0352 0.6437 1.0000
3.250 0.3860 0.05107 0.04123 -0.0369 0.6319 1.0000
3.500 0.3566 0.05287 0.04295 -0.0313 0.6206 1.0000
3.750 0.3693 0.05412 0.04414 -0.0296 0.6093 1.0000
4.000 0.3909 0.05518 0.04518 -0.0288 0.5984 1.0000
4.250 0.3768 0.05725 0.04718 -0.0255 0.5881 1.0000
4.500 0.4200 0.05783 0.04775 -0.0261 0.5770 1.0000
4.750 0.3924 0.06044 0.05030 -0.0225 0.5673 1.0000
5.000 0.4212 0.06160 0.05144 -0.0222 0.5579 1.0000
5.250 0.4004 0.06456 0.05435 -0.0200 0.5522 1.0000
5.500 0.4270 0.06590 0.05569 -0.0198 0.5437 1.0000
5.750 0.4190 0.06857 0.05831 -0.0185 0.5379 1.0000
6.000 0.4114 0.07140 0.06112 -0.0176 0.5349 1.0000
6.250 0.4092 0.07443 0.06415 -0.0174 0.5359 1.0000
6.500 0.4111 0.07746 0.06718 -0.0174 0.5379 1.0000
6.750 0.4236 0.08062 0.07036 -0.0181 0.5408 1.0000
7.000 0.3464 0.08692 0.07670 -0.0198 0.6202 1.0000
7.250 0.3723 0.09047 0.08026 -0.0210 0.6133 1.0000
7.500 0.3722 0.09145 0.08124 -0.0196 0.6005 1.0000
7.750 0.3870 0.09440 0.08420 -0.0199 0.5937 1.0000
8.000 0.4025 0.09648 0.08630 -0.0197 0.5802 1.0000
8.250 0.4006 0.09826 0.08808 -0.0188 0.5715 1.0000
8.500 0.4431 0.10291 0.09280 -0.0206 0.5598 1.0000
8.750 0.4227 0.10291 0.09279 -0.0186 0.5488 1.0000
9.000 0.4504 0.10704 0.09696 -0.0196 0.5408 1.0000
9.250 0.4507 0.10832 0.09826 -0.0188 0.5272 1.0000
9.500 0.4546 0.11101 0.10098 -0.0187 0.5197 1.0000
9.750 0.4777 0.11430 0.10432 -0.0192 0.5076 1.0000
10.000 0.4692 0.11597 0.10600 -0.0186 0.4980 1.0000
10.250 0.5074 0.12124 0.11134 -0.0199 0.4881 1.0000
10.500 0.4874 0.12152 0.11162 -0.0189 0.4776 1.0000
10.750 0.5082 0.12568 0.11584 -0.0195 0.4691 1.0000
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Polar data table (+)
Polar graphs
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