GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 50,000 Max Cl/Cd: 31.57 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe701-il-50000-n5.txt Download as CSV file: xf-goe701-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3289 0.12586 0.11869 -0.0401 1.0000 0.1339
-10.000 -0.3382 0.12386 0.11678 -0.0395 1.0000 0.1341
-9.750 -0.3481 0.12181 0.11482 -0.0386 1.0000 0.1342
-9.250 -0.3624 0.11141 0.10446 -0.0383 1.0000 0.1029
-9.000 -0.3602 0.10890 0.10199 -0.0361 1.0000 0.1019
-8.750 -0.3687 0.10676 0.09992 -0.0344 1.0000 0.1015
-8.500 -0.3817 0.10476 0.09801 -0.0327 1.0000 0.1014
-8.250 -0.3981 0.10287 0.09621 -0.0309 1.0000 0.1015
-8.000 -0.4035 0.09970 0.09308 -0.0327 0.9960 0.1016
-7.750 -0.3988 0.09539 0.08875 -0.0374 0.9879 0.1015
-7.500 -0.3890 0.09081 0.08411 -0.0421 0.9803 0.1011
-7.250 -0.3790 0.08594 0.07917 -0.0475 0.9723 0.1009
-7.000 -0.3744 0.08036 0.07349 -0.0534 0.9623 0.1019
-6.750 -0.3689 0.07411 0.06703 -0.0597 0.9532 0.1028
-6.500 -0.3582 0.06855 0.06127 -0.0643 0.9453 0.1034
-6.250 -0.3440 0.06536 0.05797 -0.0656 0.9380 0.1041
-6.000 -0.3255 0.06282 0.05533 -0.0669 0.9311 0.1056
-5.750 -0.3046 0.06050 0.05288 -0.0684 0.9250 0.1082
-5.500 -0.2905 0.05745 0.04963 -0.0695 0.9167 0.1107
-5.250 -0.2667 0.05323 0.04500 -0.0729 0.9114 0.1126
-5.000 -0.2554 0.04991 0.04129 -0.0730 0.9026 0.1141
-4.750 -0.2317 0.04561 0.03623 -0.0754 0.8970 0.1183
-4.500 -0.2123 0.04472 0.03534 -0.0747 0.8897 0.1208
-4.250 -0.1870 0.04332 0.03376 -0.0752 0.8834 0.1237
-4.000 -0.1574 0.04141 0.03150 -0.0765 0.8786 0.1273
-3.750 -0.1401 0.03983 0.02946 -0.0755 0.8703 0.1322
-3.500 -0.1089 0.03857 0.02797 -0.0766 0.8654 0.1371
-3.250 -0.0885 0.03784 0.02710 -0.0758 0.8577 0.1411
-3.000 -0.0600 0.03673 0.02563 -0.0762 0.8518 0.1474
-2.750 -0.0254 0.03590 0.02466 -0.0776 0.8476 0.1546
-2.500 -0.0089 0.03552 0.02413 -0.0759 0.8384 0.1605
-2.250 0.0252 0.03473 0.02312 -0.0770 0.8336 0.1684
-2.000 0.0462 0.03451 0.02281 -0.0761 0.8256 0.1763
-1.750 0.0760 0.03406 0.02222 -0.0765 0.8195 0.1854
-1.250 0.1297 0.03352 0.02153 -0.0764 0.8057 0.2045
-1.000 0.1659 0.03310 0.02096 -0.0777 0.8010 0.2164
-0.750 0.1903 0.03302 0.02084 -0.0772 0.7930 0.2251
-0.500 0.2220 0.03278 0.02055 -0.0779 0.7866 0.2369
-0.250 0.2626 0.03231 0.02002 -0.0798 0.7827 0.2509
0.000 0.2786 0.03251 0.02024 -0.0780 0.7725 0.2605
0.250 0.3147 0.03210 0.01988 -0.0792 0.7675 0.2785
0.500 0.3353 0.03219 0.02005 -0.0781 0.7588 0.2968
0.750 0.3654 0.03190 0.01991 -0.0783 0.7523 0.3235
1.000 0.4045 0.03118 0.01947 -0.0799 0.7485 0.3750
1.250 0.4590 0.02996 0.01994 -0.0854 0.7400 1.0000
1.500 0.4938 0.02994 0.01965 -0.0861 0.7340 1.0000
1.750 0.5091 0.03043 0.01999 -0.0839 0.7236 1.0000
2.000 0.5436 0.03035 0.01973 -0.0845 0.7172 1.0000
2.250 0.5582 0.03083 0.02012 -0.0823 0.7062 1.0000
2.500 0.5968 0.03052 0.01968 -0.0833 0.6998 1.0000
2.750 0.6113 0.03087 0.01995 -0.0809 0.6873 1.0000
3.000 0.6458 0.03048 0.01947 -0.0810 0.6783 1.0000
3.250 0.6745 0.03024 0.01915 -0.0803 0.6673 1.0000
3.500 0.6911 0.03042 0.01929 -0.0780 0.6543 1.0000
3.750 0.7182 0.03027 0.01909 -0.0772 0.6436 1.0000
4.250 0.7635 0.03034 0.01909 -0.0744 0.6209 1.0000
4.500 0.7856 0.03042 0.01917 -0.0730 0.6096 1.0000
4.750 0.8207 0.02998 0.01870 -0.0733 0.6000 1.0000
5.000 0.8336 0.03038 0.01911 -0.0706 0.5863 1.0000
5.250 0.8510 0.03063 0.01937 -0.0686 0.5731 1.0000
5.500 0.8731 0.03068 0.01941 -0.0672 0.5602 1.0000
5.750 0.8998 0.03055 0.01925 -0.0663 0.5475 1.0000
6.000 0.9253 0.03048 0.01919 -0.0653 0.5341 1.0000
6.250 0.9419 0.03079 0.01949 -0.0632 0.5188 1.0000
6.500 0.9595 0.03108 0.01978 -0.0613 0.5033 1.0000
6.750 0.9776 0.03139 0.02008 -0.0595 0.4876 1.0000
7.000 0.9955 0.03176 0.02045 -0.0577 0.4718 1.0000
7.250 1.0133 0.03216 0.02082 -0.0560 0.4558 1.0000
7.500 1.0304 0.03264 0.02128 -0.0542 0.4400 1.0000
7.750 1.0472 0.03320 0.02182 -0.0525 0.4248 1.0000
8.000 1.0639 0.03382 0.02241 -0.0508 0.4104 1.0000
8.250 1.0813 0.03445 0.02301 -0.0493 0.3968 1.0000
8.500 1.1006 0.03504 0.02355 -0.0480 0.3842 1.0000
8.750 1.1169 0.03582 0.02434 -0.0465 0.3722 1.0000
9.000 1.1299 0.03683 0.02539 -0.0448 0.3608 1.0000
9.250 1.1480 0.03760 0.02614 -0.0436 0.3505 1.0000
9.500 1.1648 0.03845 0.02701 -0.0422 0.3404 1.0000
9.750 1.1772 0.03961 0.02826 -0.0407 0.3312 1.0000
10.000 1.2009 0.04020 0.02882 -0.0400 0.3226 1.0000
10.250 1.2064 0.04173 0.03050 -0.0380 0.3139 1.0000
10.500 1.2326 0.04226 0.03099 -0.0376 0.3063 1.0000
10.750 1.2340 0.04407 0.03302 -0.0353 0.2987 1.0000
11.000 1.2557 0.04482 0.03378 -0.0346 0.2915 1.0000
11.250 1.2598 0.04660 0.03574 -0.0327 0.2849 1.0000
11.500 1.2711 0.04799 0.03725 -0.0314 0.2784 1.0000
11.750 1.2904 0.04900 0.03831 -0.0306 0.2724 1.0000
12.000 1.2850 0.05147 0.04104 -0.0284 0.2666 1.0000
12.250 1.3000 0.05271 0.04238 -0.0275 0.2609 1.0000
12.500 1.3114 0.05431 0.04410 -0.0264 0.2558 1.0000
12.750 1.2962 0.05771 0.04776 -0.0243 0.2508 1.0000
13.000 1.3055 0.05926 0.04941 -0.0232 0.2450 1.0000
13.250 1.3111 0.06114 0.05139 -0.0220 0.2396 1.0000
13.500 1.2784 0.06662 0.05716 -0.0206 0.2354 1.0000
13.750 1.2693 0.07014 0.06084 -0.0198 0.2304 1.0000
14.000 1.2880 0.07051 0.06125 -0.0189 0.2239 1.0000
14.250 1.2172 0.08217 0.07319 -0.0203 0.2221 1.0000
14.500 1.0486 0.11391 0.10495 -0.0328 0.2131 1.0000
14.750 1.0704 0.11357 0.10476 -0.0314 0.2107 1.0000
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