GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 50,000 Max Cl/Cd: 25.96 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe704-il-50000.txt Download as CSV file: xf-goe704-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4635 0.11570 0.10860 0.0005 1.0000 0.3029
-9.750 -0.4840 0.11428 0.10728 -0.0007 1.0000 0.3147
-9.500 -0.4743 0.11039 0.10339 -0.0002 1.0000 0.3308
-9.250 -0.4620 0.10630 0.09929 0.0004 1.0000 0.3464
-9.000 -0.4612 0.10315 0.09617 0.0008 1.0000 0.3633
-8.750 -0.4633 0.10016 0.09324 0.0013 1.0000 0.3803
-8.250 -0.5940 0.07553 0.06875 -0.0248 1.0000 0.2183
-8.000 -0.5889 0.07066 0.06386 -0.0245 1.0000 0.2166
-7.750 -0.5951 0.06594 0.05907 -0.0237 1.0000 0.2150
-7.500 -0.6047 0.06148 0.05449 -0.0222 1.0000 0.2133
-7.250 -0.6163 0.05755 0.05039 -0.0195 1.0000 0.2127
-7.000 -0.6278 0.05419 0.04681 -0.0160 1.0000 0.2142
-6.750 -0.6390 0.05105 0.04332 -0.0122 1.0000 0.2166
-6.500 -0.6405 0.04844 0.04052 -0.0089 1.0000 0.2209
-6.250 -0.6343 0.04668 0.03867 -0.0061 1.0000 0.2277
-6.000 -0.6360 0.04398 0.03541 -0.0030 1.0000 0.2335
-5.750 -0.6241 0.04238 0.03385 -0.0008 1.0000 0.2412
-5.500 -0.6174 0.04025 0.03119 0.0015 1.0000 0.2495
-5.250 -0.6030 0.03887 0.02983 0.0033 1.0000 0.2585
-5.000 -0.5903 0.03708 0.02760 0.0050 1.0000 0.2674
-4.750 -0.5740 0.03592 0.02637 0.0064 1.0000 0.2777
-4.500 -0.5570 0.03457 0.02479 0.0076 1.0000 0.2870
-4.250 -0.5393 0.03351 0.02337 0.0087 1.0000 0.2982
-4.000 -0.5195 0.03249 0.02236 0.0095 1.0000 0.3081
-3.750 -0.4990 0.03157 0.02123 0.0102 1.0000 0.3193
-3.500 -0.4778 0.03082 0.02021 0.0107 1.0000 0.3311
-3.250 -0.4562 0.03004 0.01943 0.0112 1.0000 0.3420
-3.000 -0.4345 0.02939 0.01871 0.0117 1.0000 0.3552
-2.750 -0.4118 0.02882 0.01803 0.0120 1.0000 0.3692
-2.500 -0.3874 0.02833 0.01749 0.0120 1.0000 0.3849
-2.250 -0.3623 0.02792 0.01711 0.0119 1.0000 0.4062
-2.000 -0.3367 0.02753 0.01677 0.0117 1.0000 0.4330
-1.750 -0.1436 0.02664 0.01811 -0.0152 1.0000 1.0000
-1.500 -0.1334 0.02696 0.01807 -0.0134 1.0000 1.0000
-1.250 -0.1238 0.02731 0.01817 -0.0114 1.0000 1.0000
-1.000 -0.1141 0.02768 0.01833 -0.0094 1.0000 1.0000
-0.750 -0.1042 0.02809 0.01855 -0.0076 1.0000 1.0000
-0.500 -0.0943 0.02853 0.01883 -0.0058 1.0000 1.0000
-0.250 -0.0414 0.02939 0.01947 -0.0122 0.9870 1.0000
0.000 0.0117 0.03025 0.02015 -0.0184 0.9725 1.0000
0.250 0.0632 0.03106 0.02083 -0.0242 0.9572 1.0000
0.500 0.1134 0.03181 0.02147 -0.0295 0.9412 1.0000
0.750 0.1633 0.03249 0.02208 -0.0345 0.9249 1.0000
1.000 0.2135 0.03310 0.02264 -0.0394 0.9081 1.0000
1.250 0.2557 0.03365 0.02316 -0.0426 0.8903 1.0000
1.500 0.2946 0.03416 0.02367 -0.0450 0.8713 1.0000
1.750 0.3387 0.03457 0.02410 -0.0481 0.8519 1.0000
2.000 0.3928 0.03475 0.02432 -0.0526 0.8325 1.0000
2.250 0.4480 0.03463 0.02426 -0.0565 0.8134 1.0000
2.500 0.4958 0.03437 0.02406 -0.0586 0.7941 1.0000
2.750 0.5167 0.03471 0.02444 -0.0569 0.7709 1.0000
3.000 0.5538 0.03439 0.02417 -0.0568 0.7506 1.0000
3.250 0.5909 0.03385 0.02368 -0.0562 0.7314 1.0000
3.500 0.6117 0.03397 0.02384 -0.0539 0.7090 1.0000
3.750 0.6363 0.03381 0.02372 -0.0518 0.6877 1.0000
4.000 0.6655 0.03330 0.02325 -0.0500 0.6684 1.0000
4.250 0.6944 0.03273 0.02268 -0.0480 0.6500 1.0000
4.500 0.7086 0.03322 0.02322 -0.0453 0.6269 1.0000
4.750 0.7331 0.03297 0.02300 -0.0432 0.6078 1.0000
5.000 0.7587 0.03266 0.02270 -0.0413 0.5898 1.0000
5.250 0.7848 0.03236 0.02238 -0.0394 0.5725 1.0000
5.500 0.8067 0.03249 0.02254 -0.0375 0.5547 1.0000
5.750 0.8258 0.03300 0.02310 -0.0356 0.5374 1.0000
6.000 0.8468 0.03346 0.02358 -0.0339 0.5216 1.0000
6.250 0.8683 0.03392 0.02408 -0.0322 0.5065 1.0000
6.500 0.8911 0.03436 0.02453 -0.0308 0.4924 1.0000
6.750 0.9120 0.03513 0.02534 -0.0293 0.4794 1.0000
7.000 0.9239 0.03664 0.02699 -0.0273 0.4664 1.0000
7.250 0.9375 0.03797 0.02844 -0.0254 0.4537 1.0000
7.500 0.9542 0.03900 0.02954 -0.0236 0.4411 1.0000
7.750 0.9750 0.03963 0.03020 -0.0219 0.4278 1.0000
8.000 0.9965 0.04009 0.03067 -0.0202 0.4133 1.0000
8.250 1.0193 0.04055 0.03114 -0.0187 0.3991 1.0000
8.500 1.0300 0.04204 0.03279 -0.0165 0.3871 1.0000
8.750 1.0295 0.04441 0.03537 -0.0135 0.3768 1.0000
9.000 1.0482 0.04563 0.03667 -0.0120 0.3661 1.0000
9.250 1.0634 0.04710 0.03824 -0.0103 0.3552 1.0000
9.500 1.0415 0.05104 0.04245 -0.0061 0.3475 1.0000
9.750 1.0656 0.05194 0.04343 -0.0049 0.3354 1.0000
10.000 1.0069 0.05861 0.05029 0.0004 0.3316 1.0000
10.250 1.0335 0.05924 0.05103 0.0017 0.3192 1.0000
10.500 0.9300 0.07076 0.06245 0.0053 0.3210 1.0000
11.000 0.7531 0.10353 0.09477 -0.0069 0.3231 1.0000
11.250 0.7319 0.11083 0.10204 -0.0093 0.3234 1.0000
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Polar data table (+)
Polar graphs
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