GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 1,000,000 Max Cl/Cd: 44.04 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe780-il-1000000-n5.txt Download as CSV file: xf-goe780-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4074 0.08487 0.08265 -0.0777 0.8372 0.0017
-10.750 -0.4144 0.07966 0.07740 -0.0805 0.8284 0.0017
-10.500 -0.4301 0.07240 0.07013 -0.0861 0.8208 0.0016
-10.250 -0.4391 0.06853 0.06620 -0.0885 0.8147 0.0016
-10.000 -0.4702 0.06273 0.06032 -0.0885 0.8084 0.0017
-9.500 -0.5047 0.05679 0.05420 -0.0831 0.7992 0.0016
-9.250 -0.5117 0.05517 0.05251 -0.0800 0.7953 0.0015
-9.000 -0.5384 0.05185 0.04905 -0.0731 0.7912 0.0015
-8.750 -0.5506 0.04877 0.04584 -0.0683 0.7880 0.0015
-8.500 -0.5602 0.04537 0.04228 -0.0635 0.7850 0.0014
-8.250 -0.5711 0.04120 0.03789 -0.0578 0.7818 0.0014
-8.000 -0.5796 0.03666 0.03308 -0.0519 0.7789 0.0013
-7.750 -0.6191 0.02229 0.01761 -0.0376 0.7761 0.0013
-7.500 -0.6032 0.01917 0.01403 -0.0354 0.7742 0.0017
-7.250 -0.5815 0.01660 0.01105 -0.0345 0.7725 0.0015
-7.000 -0.5578 0.01595 0.01026 -0.0340 0.7705 0.0020
-6.750 -0.5341 0.01476 0.00887 -0.0335 0.7685 0.0021
-6.500 -0.5112 0.01375 0.00769 -0.0328 0.7664 0.0021
-6.250 -0.4894 0.01297 0.00678 -0.0320 0.7643 0.0024
-6.000 -0.4669 0.01262 0.00640 -0.0313 0.7622 0.0026
-5.750 -0.4452 0.01212 0.00579 -0.0303 0.7602 0.0030
-5.500 -0.4238 0.01160 0.00519 -0.0293 0.7585 0.0029
-5.250 -0.4027 0.01112 0.00463 -0.0281 0.7566 0.0035
-5.000 -0.3809 0.01076 0.00420 -0.0271 0.7547 0.0038
-4.750 -0.3599 0.01033 0.00369 -0.0259 0.7526 0.0041
-4.500 -0.3379 0.01003 0.00336 -0.0250 0.7506 0.0055
-4.250 -0.3152 0.00980 0.00306 -0.0242 0.7486 0.0064
-4.000 -0.2933 0.00952 0.00272 -0.0232 0.7467 0.0091
-3.750 -0.2701 0.00931 0.00249 -0.0224 0.7451 0.0144
-3.500 -0.2470 0.00910 0.00235 -0.0217 0.7433 0.0299
-3.250 -0.2231 0.00894 0.00220 -0.0212 0.7414 0.0361
-3.000 -0.1986 0.00884 0.00207 -0.0208 0.7393 0.0395
-2.750 -0.1751 0.00867 0.00192 -0.0201 0.7372 0.0482
-2.500 -0.1506 0.00858 0.00178 -0.0197 0.7354 0.0521
-2.250 -0.1267 0.00845 0.00167 -0.0191 0.7337 0.0638
-2.000 -0.1036 0.00827 0.00159 -0.0184 0.7318 0.1005
-1.750 -0.0789 0.00817 0.00151 -0.0181 0.7300 0.1102
-1.500 -0.0544 0.00806 0.00143 -0.0176 0.7280 0.1222
-1.250 -0.0416 0.00734 0.00126 -0.0149 0.7258 0.2932
-1.000 -0.0265 0.00682 0.00114 -0.0126 0.7237 0.4126
-0.750 -0.0303 0.00585 0.00096 -0.0060 0.7212 0.6317
-0.500 -0.0168 0.00558 0.00089 -0.0030 0.7190 0.6945
-0.250 -0.0057 0.00526 0.00084 0.0006 0.7160 0.7568
0.000 0.0084 0.00506 0.00093 0.0038 0.7130 0.8343
0.250 0.0309 0.00505 0.00096 0.0048 0.7087 0.8582
0.500 0.0551 0.00506 0.00100 0.0055 0.7048 0.8741
0.750 0.0796 0.00508 0.00104 0.0061 0.7014 0.8849
1.000 0.1079 0.00508 0.00107 0.0057 0.6976 0.8888
1.250 0.1358 0.00510 0.00108 0.0054 0.6920 0.8925
1.500 0.1617 0.00511 0.00112 0.0056 0.6873 0.8958
1.750 0.1853 0.00512 0.00113 0.0063 0.6805 0.8994
2.000 0.2100 0.00518 0.00113 0.0068 0.6509 0.9023
2.250 0.2343 0.00532 0.00119 0.0073 0.6141 0.9053
2.500 0.2225 0.00663 0.00160 0.0154 0.3808 0.9117
2.750 0.2135 0.00817 0.00218 0.0223 0.0921 0.9182
3.000 0.2370 0.00842 0.00235 0.0228 0.0601 0.9213
3.250 0.2546 0.00874 0.00253 0.0246 0.0148 0.9265
3.500 0.2820 0.00897 0.00280 0.0243 0.0101 0.9299
3.750 0.3114 0.00923 0.00313 0.0235 0.0076 0.9331
4.000 0.3360 0.00949 0.00342 0.0238 0.0061 0.9397
4.250 0.3602 0.00989 0.00387 0.0241 0.0050 0.9429
4.500 0.3885 0.01033 0.00439 0.0234 0.0046 0.9449
4.750 0.4136 0.01089 0.00503 0.0234 0.0041 0.9469
5.000 0.4378 0.01131 0.00548 0.0236 0.0036 0.9496
5.250 0.4518 0.01159 0.00576 0.0261 0.0030 0.9552
5.500 0.4767 0.01237 0.00663 0.0260 0.0028 0.9567
5.750 0.5012 0.01305 0.00741 0.0260 0.0023 0.9584
6.000 0.5221 0.01418 0.00865 0.0269 0.0023 0.9607
6.250 0.5503 0.01554 0.01014 0.0264 0.0021 0.9616
6.500 0.5888 0.01805 0.01288 0.0245 0.0020 0.9601
6.750 0.6220 0.02100 0.01615 0.0239 0.0022 0.9599
7.000 0.6481 0.02482 0.02034 0.0248 0.0023 0.9608
7.250 0.6667 0.02827 0.02411 0.0268 0.0025 0.9633
7.500 0.6774 0.03116 0.02724 0.0299 0.0026 0.9679
7.750 0.6905 0.03446 0.03081 0.0314 0.0029 0.9693
8.250 0.7187 0.04190 0.03875 0.0356 0.0027 0.9736
8.500 0.7290 0.04366 0.04062 0.0380 0.0019 0.9782
8.750 0.7327 0.04885 0.04611 0.0406 0.0022 0.9799
9.000 0.7380 0.05221 0.04964 0.0421 0.0019 0.9823
9.500 0.7387 0.05865 0.05637 0.0457 0.0018 0.9888
11.000 0.6582 0.08590 0.08428 0.0426 0.0018 0.9996
11.250 0.6351 0.09546 0.09390 0.0364 0.0020 1.0000
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Polar data table (+)
Polar graphs
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