GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 100,000 Max Cl/Cd: 44.86 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe704-il-100000.txt Download as CSV file: xf-goe704-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6071 0.09010 0.08525 -0.0301 1.0000 0.0854
-10.500 -0.6156 0.08336 0.07854 -0.0336 1.0000 0.0848
-10.250 -0.6359 0.07525 0.07044 -0.0385 1.0000 0.0836
-10.000 -0.6698 0.06752 0.06265 -0.0406 1.0000 0.0821
-9.750 -0.7098 0.06010 0.05503 -0.0396 1.0000 0.0806
-9.500 -0.7414 0.05301 0.04755 -0.0373 1.0000 0.0801
-9.250 -0.7592 0.04740 0.04148 -0.0341 1.0000 0.0812
-9.000 -0.7718 0.04247 0.03592 -0.0303 1.0000 0.0838
-8.750 -0.7687 0.03971 0.03287 -0.0274 1.0000 0.0875
-8.500 -0.7495 0.03958 0.03287 -0.0261 1.0000 0.0928
-8.250 -0.7551 0.03664 0.02928 -0.0213 1.0000 0.0975
-8.000 -0.7425 0.03614 0.02898 -0.0192 1.0000 0.1023
-7.750 -0.7385 0.03533 0.02803 -0.0155 1.0000 0.1078
-7.500 -0.7398 0.03375 0.02608 -0.0112 1.0000 0.1131
-7.250 -0.7289 0.03371 0.02621 -0.0088 1.0000 0.1187
-7.000 -0.7264 0.03244 0.02439 -0.0050 1.0000 0.1259
-6.750 -0.7122 0.03195 0.02415 -0.0034 1.0000 0.1320
-6.500 -0.7033 0.03105 0.02273 -0.0005 1.0000 0.1402
-6.250 -0.6875 0.03024 0.02211 0.0008 1.0000 0.1470
-6.000 -0.6674 0.02918 0.02064 0.0015 0.9984 0.1568
-5.750 -0.6294 0.02836 0.01979 -0.0011 0.9933 0.1682
-5.500 -0.5945 0.02742 0.01875 -0.0032 0.9875 0.1790
-5.250 -0.5561 0.02653 0.01764 -0.0058 0.9828 0.1906
-5.000 -0.5228 0.02598 0.01689 -0.0073 0.9763 0.2015
-4.750 -0.4843 0.02527 0.01619 -0.0100 0.9712 0.2118
-4.500 -0.4496 0.02466 0.01544 -0.0117 0.9655 0.2217
-4.250 -0.4142 0.02424 0.01490 -0.0136 0.9593 0.2324
-4.000 -0.3718 0.02365 0.01434 -0.0168 0.9551 0.2430
-3.750 -0.3432 0.02326 0.01387 -0.0174 0.9477 0.2527
-3.500 -0.3037 0.02284 0.01340 -0.0199 0.9424 0.2644
-3.250 -0.2650 0.02239 0.01302 -0.0224 0.9374 0.2769
-3.000 -0.2344 0.02204 0.01273 -0.0232 0.9301 0.2901
-2.750 -0.1902 0.02154 0.01230 -0.0266 0.9257 0.3092
-2.500 -0.1595 0.02121 0.01208 -0.0274 0.9186 0.3320
-2.250 -0.1229 0.02062 0.01180 -0.0293 0.9125 0.3693
-1.750 0.1604 0.01920 0.01242 -0.0680 0.9253 0.9899
-1.500 0.2174 0.01885 0.01191 -0.0738 0.9154 1.0000
-1.250 0.2455 0.01876 0.01169 -0.0737 0.9033 1.0000
-1.000 0.2714 0.01867 0.01149 -0.0731 0.8922 1.0000
-0.750 0.2931 0.01875 0.01149 -0.0719 0.8796 1.0000
-0.500 0.3152 0.01882 0.01149 -0.0708 0.8681 1.0000
-0.250 0.3377 0.01881 0.01140 -0.0693 0.8579 1.0000
0.000 0.3591 0.01887 0.01140 -0.0679 0.8461 1.0000
0.250 0.3804 0.01895 0.01144 -0.0665 0.8340 1.0000
0.500 0.4018 0.01897 0.01140 -0.0648 0.8228 1.0000
0.750 0.4231 0.01891 0.01128 -0.0629 0.8118 1.0000
1.000 0.4444 0.01896 0.01130 -0.0614 0.7984 1.0000
1.250 0.4656 0.01896 0.01127 -0.0597 0.7851 1.0000
1.500 0.4870 0.01890 0.01117 -0.0579 0.7719 1.0000
1.750 0.5085 0.01879 0.01101 -0.0559 0.7588 1.0000
2.000 0.5305 0.01862 0.01078 -0.0539 0.7460 1.0000
2.250 0.5524 0.01853 0.01067 -0.0523 0.7310 1.0000
2.500 0.5746 0.01844 0.01056 -0.0506 0.7156 1.0000
2.750 0.5970 0.01834 0.01044 -0.0490 0.6999 1.0000
3.000 0.6195 0.01821 0.01028 -0.0474 0.6836 1.0000
3.250 0.6422 0.01806 0.01009 -0.0458 0.6666 1.0000
3.500 0.6647 0.01794 0.00998 -0.0443 0.6470 1.0000
3.750 0.6871 0.01782 0.00984 -0.0428 0.6253 1.0000
4.000 0.7100 0.01765 0.00960 -0.0413 0.6039 1.0000
4.250 0.7322 0.01762 0.00954 -0.0398 0.5782 1.0000
4.500 0.7549 0.01762 0.00943 -0.0384 0.5534 1.0000
4.750 0.7771 0.01775 0.00944 -0.0370 0.5271 1.0000
5.000 0.7989 0.01801 0.00958 -0.0357 0.5008 1.0000
5.250 0.8209 0.01834 0.00973 -0.0345 0.4776 1.0000
5.500 0.8421 0.01878 0.01009 -0.0332 0.4542 1.0000
5.750 0.8636 0.01925 0.01042 -0.0320 0.4342 1.0000
6.000 0.8851 0.01978 0.01081 -0.0309 0.4163 1.0000
6.250 0.9062 0.02034 0.01130 -0.0298 0.3996 1.0000
6.500 0.9275 0.02091 0.01180 -0.0286 0.3847 1.0000
6.750 0.9481 0.02149 0.01240 -0.0275 0.3709 1.0000
7.000 0.9686 0.02211 0.01307 -0.0263 0.3586 1.0000
7.250 0.9894 0.02275 0.01373 -0.0252 0.3476 1.0000
7.500 1.0113 0.02339 0.01427 -0.0242 0.3373 1.0000
7.750 1.0299 0.02401 0.01505 -0.0227 0.3266 1.0000
8.000 1.0499 0.02471 0.01580 -0.0215 0.3173 1.0000
8.250 1.0707 0.02535 0.01642 -0.0204 0.3079 1.0000
8.500 1.0877 0.02607 0.01732 -0.0187 0.2983 1.0000
8.750 1.1088 0.02679 0.01800 -0.0176 0.2895 1.0000
9.000 1.1247 0.02750 0.01891 -0.0158 0.2799 1.0000
9.250 1.1416 0.02824 0.01974 -0.0141 0.2701 1.0000
9.500 1.1599 0.02879 0.02021 -0.0126 0.2591 1.0000
9.750 1.1717 0.02922 0.02076 -0.0102 0.2468 1.0000
10.000 1.1810 0.02968 0.02135 -0.0074 0.2341 1.0000
10.250 1.1900 0.03014 0.02189 -0.0046 0.2220 1.0000
10.500 1.1988 0.03061 0.02238 -0.0018 0.2107 1.0000
10.750 1.2081 0.03104 0.02274 0.0008 0.1997 1.0000
11.000 1.2097 0.03165 0.02356 0.0045 0.1888 1.0000
11.250 1.2123 0.03235 0.02439 0.0078 0.1786 1.0000
11.500 1.2135 0.03303 0.02507 0.0113 0.1692 1.0000
11.750 1.2083 0.03388 0.02608 0.0154 0.1594 1.0000
12.000 1.2031 0.03504 0.02737 0.0188 0.1483 1.0000
12.250 1.1960 0.03653 0.02897 0.0216 0.1352 1.0000
12.500 1.1859 0.03862 0.03108 0.0237 0.1193 1.0000
12.750 1.1723 0.04153 0.03385 0.0254 0.1040 1.0000
13.000 1.1584 0.04499 0.03717 0.0267 0.0912 1.0000
13.250 1.1480 0.04844 0.04061 0.0277 0.0817 1.0000
13.500 1.1422 0.05167 0.04388 0.0288 0.0746 1.0000
13.750 1.1396 0.05456 0.04672 0.0296 0.0696 1.0000
14.000 1.1392 0.05745 0.04972 0.0303 0.0654 1.0000
14.250 1.1379 0.06043 0.05283 0.0306 0.0619 1.0000
14.500 1.1397 0.06301 0.05538 0.0310 0.0589 1.0000
14.750 1.1405 0.06597 0.05844 0.0314 0.0565 1.0000
15.000 1.1371 0.06948 0.06218 0.0312 0.0547 1.0000
15.250 1.1350 0.07292 0.06579 0.0310 0.0531 1.0000
15.500 1.1335 0.07636 0.06935 0.0307 0.0518 1.0000
15.750 1.1338 0.07962 0.07270 0.0304 0.0506 1.0000
16.000 1.1412 0.08211 0.07517 0.0309 0.0492 1.0000
16.250 1.1347 0.08658 0.07979 0.0301 0.0485 1.0000
16.500 1.1183 0.09240 0.08588 0.0279 0.0483 1.0000
16.750 1.0994 0.09895 0.09267 0.0249 0.0482 1.0000
17.000 1.0780 0.10625 0.10020 0.0212 0.0483 1.0000
17.250 1.0543 0.11441 0.10858 0.0167 0.0484 1.0000
17.500 1.0288 0.12346 0.11781 0.0115 0.0487 1.0000
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