GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 100,000 Max Cl/Cd: 54.37 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe630-il-100000-n5.txt Download as CSV file: xf-goe630-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0512 0.09794 0.09283 -0.0985 0.9041 0.0590
-9.000 0.0640 0.09543 0.09027 -0.1038 0.8964 0.0610
-8.750 0.0665 0.09392 0.08875 -0.1079 0.8841 0.0616
-8.500 0.0697 0.09205 0.08686 -0.1117 0.8729 0.0618
-8.250 0.0985 0.08668 0.08145 -0.1103 0.8688 0.0631
-8.000 0.1186 0.08363 0.07834 -0.1116 0.8625 0.0653
-7.750 0.1264 0.08159 0.07630 -0.1121 0.8521 0.0677
-7.500 0.1340 0.07946 0.07412 -0.1140 0.8434 0.0699
-7.250 0.1284 0.07845 0.07312 -0.1153 0.8318 0.0714
-7.000 0.1263 0.07721 0.07185 -0.1202 0.8208 0.0722
-6.750 0.1370 0.07440 0.06899 -0.1240 0.8131 0.0725
-6.500 0.1488 0.07114 0.06574 -0.1204 0.8061 0.0733
-6.250 0.1630 0.06871 0.06329 -0.1187 0.7992 0.0750
-6.000 0.1760 0.06662 0.06115 -0.1190 0.7922 0.0777
-5.750 0.1859 0.06470 0.05920 -0.1213 0.7836 0.0816
-5.500 0.2065 0.06227 0.05650 -0.1327 0.7757 0.0846
-5.250 0.2153 0.05931 0.05360 -0.1301 0.7682 0.0854
-5.000 0.2312 0.05680 0.05106 -0.1293 0.7625 0.0865
-4.750 0.2447 0.05479 0.04903 -0.1290 0.7549 0.0878
-4.500 0.2630 0.05256 0.04671 -0.1301 0.7480 0.0894
-4.000 0.3164 0.04235 0.03571 -0.1402 0.7345 0.0615
-3.750 0.3387 0.04029 0.03355 -0.1406 0.7286 0.0606
-3.500 0.3584 0.03817 0.03129 -0.1407 0.7210 0.0595
-3.250 0.3825 0.03567 0.02854 -0.1415 0.7142 0.0584
-3.000 0.4083 0.03315 0.02567 -0.1423 0.7080 0.0577
-2.750 0.4305 0.03117 0.02339 -0.1421 0.6999 0.0584
-2.500 0.4586 0.02912 0.02089 -0.1425 0.6941 0.0596
-2.250 0.4800 0.02766 0.01911 -0.1417 0.6857 0.0599
-2.000 0.5065 0.02622 0.01729 -0.1415 0.6788 0.0601
-1.750 0.5301 0.02509 0.01583 -0.1406 0.6708 0.0606
-1.500 0.5558 0.02410 0.01450 -0.1400 0.6631 0.0613
-1.250 0.5803 0.02333 0.01355 -0.1394 0.6554 0.0630
-1.000 0.6045 0.02281 0.01295 -0.1387 0.6470 0.0651
-0.750 0.6294 0.02228 0.01227 -0.1380 0.6389 0.0671
-0.500 0.6540 0.02173 0.01156 -0.1372 0.6303 0.0687
-0.250 0.6786 0.02127 0.01095 -0.1363 0.6219 0.0706
0.000 0.7032 0.02086 0.01044 -0.1355 0.6133 0.0732
0.250 0.7264 0.02060 0.01020 -0.1347 0.6043 0.0773
0.500 0.7517 0.02031 0.00982 -0.1340 0.5959 0.0816
0.750 0.7749 0.02012 0.00957 -0.1330 0.5864 0.0853
1.000 0.8004 0.01989 0.00929 -0.1324 0.5784 0.0927
1.250 0.8226 0.01983 0.00921 -0.1313 0.5685 0.1015
1.500 0.8497 0.01971 0.00899 -0.1310 0.5606 0.1163
1.750 0.8737 0.01964 0.00902 -0.1304 0.5511 0.1499
2.000 0.9004 0.01926 0.00908 -0.1304 0.5430 0.3225
2.250 0.9411 0.01830 0.00916 -0.1332 0.5333 1.0000
2.500 0.9644 0.01856 0.00921 -0.1323 0.5251 1.0000
2.750 0.9871 0.01883 0.00932 -0.1313 0.5168 1.0000
3.000 1.0104 0.01911 0.00945 -0.1305 0.5096 1.0000
3.250 1.0324 0.01943 0.00965 -0.1295 0.5019 1.0000
3.500 1.0566 0.01971 0.00976 -0.1289 0.4954 1.0000
3.750 1.0771 0.02008 0.01009 -0.1277 0.4876 1.0000
4.000 1.1008 0.02038 0.01025 -0.1270 0.4814 1.0000
4.250 1.1215 0.02077 0.01058 -0.1258 0.4745 1.0000
4.500 1.1432 0.02114 0.01088 -0.1249 0.4682 1.0000
4.750 1.1678 0.02148 0.01109 -0.1244 0.4631 1.0000
5.000 1.1869 0.02193 0.01156 -0.1231 0.4570 1.0000
5.250 1.2085 0.02233 0.01192 -0.1222 0.4515 1.0000
5.500 1.2334 0.02270 0.01216 -0.1218 0.4470 1.0000
5.750 1.2507 0.02320 0.01272 -0.1203 0.4411 1.0000
6.000 1.2711 0.02364 0.01315 -0.1192 0.4360 1.0000
6.250 1.2952 0.02404 0.01347 -0.1188 0.4318 1.0000
6.500 1.3141 0.02457 0.01403 -0.1176 0.4273 1.0000
6.750 1.3321 0.02510 0.01461 -0.1162 0.4227 1.0000
7.000 1.3527 0.02558 0.01510 -0.1153 0.4187 1.0000
7.250 1.3776 0.02601 0.01547 -0.1150 0.4151 1.0000
7.500 1.3922 0.02663 0.01617 -0.1132 0.4109 1.0000
7.750 1.4067 0.02726 0.01688 -0.1114 0.4065 1.0000
8.000 1.4257 0.02781 0.01745 -0.1103 0.4027 1.0000
8.250 1.4493 0.02830 0.01794 -0.1099 0.3996 1.0000
8.500 1.4684 0.02893 0.01861 -0.1089 0.3965 1.0000
8.750 1.4782 0.02975 0.01959 -0.1066 0.3928 1.0000
9.000 1.4919 0.03049 0.02042 -0.1048 0.3891 1.0000
9.250 1.5104 0.03111 0.02109 -0.1038 0.3857 1.0000
9.500 1.5347 0.03161 0.02159 -0.1036 0.3828 1.0000
9.750 1.5466 0.03249 0.02260 -0.1018 0.3797 1.0000
10.000 1.5507 0.03363 0.02392 -0.0991 0.3763 1.0000
10.250 1.5601 0.03463 0.02504 -0.0971 0.3728 1.0000
10.500 1.5760 0.03539 0.02588 -0.0959 0.3696 1.0000
10.750 1.5991 0.03592 0.02646 -0.0956 0.3669 1.0000
11.000 1.6108 0.03693 0.02759 -0.0941 0.3640 1.0000
11.250 1.6014 0.03882 0.02971 -0.0904 0.3602 1.0000
11.500 1.6021 0.04038 0.03143 -0.0880 0.3566 1.0000
11.750 1.6144 0.04138 0.03253 -0.0867 0.3534 1.0000
12.000 1.6385 0.04180 0.03302 -0.0865 0.3507 1.0000
12.250 1.6391 0.04351 0.03488 -0.0843 0.3474 1.0000
12.500 1.6106 0.04714 0.03877 -0.0804 0.3431 1.0000
12.750 1.6033 0.04962 0.04141 -0.0782 0.3391 1.0000
13.000 1.6258 0.04985 0.04170 -0.0778 0.3356 1.0000
13.250 1.6321 0.05127 0.04322 -0.0765 0.3315 1.0000
13.500 1.5451 0.06165 0.05393 -0.0724 0.3262 1.0000
13.750 1.5327 0.06536 0.05777 -0.0714 0.3214 1.0000
14.000 1.6046 0.05954 0.05190 -0.0714 0.3160 1.0000
14.250 1.3635 0.09400 0.08665 -0.0733 0.2998 1.0000
14.500 1.4088 0.09023 0.08301 -0.0718 0.3008 1.0000
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Polar data table (+)
Polar graphs
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