GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 50,000 Max Cl/Cd: 40.21 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe176-il-50000-n5.txt Download as CSV file: xf-goe176-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2718 0.10560 0.09933 -0.0305 1.0000 0.1103
-7.750 -0.2784 0.10008 0.09387 -0.0320 1.0000 0.0679
-7.500 -0.3006 0.09742 0.09142 -0.0335 1.0000 0.0582
-7.250 -0.2996 0.09477 0.08887 -0.0320 1.0000 0.0574
-7.000 -0.3020 0.09236 0.08657 -0.0309 1.0000 0.0567
-6.750 -0.3065 0.09010 0.08443 -0.0299 1.0000 0.0559
-6.500 -0.3121 0.08789 0.08234 -0.0291 1.0000 0.0552
-6.250 -0.3176 0.08561 0.08016 -0.0286 1.0000 0.0543
-6.000 -0.3157 0.08252 0.07713 -0.0303 0.9983 0.0532
-5.750 -0.2847 0.07624 0.07080 -0.0402 0.9886 0.0511
-5.500 -0.2495 0.06879 0.06326 -0.0521 0.9784 0.0490
-5.250 -0.1975 0.05493 0.04899 -0.0733 0.9686 0.0459
-5.000 -0.1543 0.04731 0.04092 -0.0844 0.9598 0.0465
-4.750 -0.1145 0.04320 0.03650 -0.0908 0.9515 0.0497
-4.500 -0.0657 0.03716 0.02965 -0.0996 0.9443 0.0522
-4.250 -0.0205 0.03295 0.02459 -0.1052 0.9371 0.0544
-4.000 0.0232 0.03018 0.02115 -0.1091 0.9296 0.0600
-3.750 0.0626 0.02843 0.01915 -0.1118 0.9204 0.0666
-3.500 0.1070 0.02676 0.01721 -0.1151 0.9128 0.0773
-3.250 0.1472 0.02545 0.01574 -0.1174 0.9021 0.0944
-3.000 0.1913 0.02440 0.01490 -0.1203 0.8928 0.1445
-2.750 0.2322 0.02464 0.01502 -0.1221 0.8816 0.2213
-2.500 0.2659 0.02518 0.01548 -0.1228 0.8680 0.2729
-2.250 0.2992 0.02507 0.01519 -0.1235 0.8549 0.3032
-2.000 0.3334 0.02462 0.01446 -0.1243 0.8424 0.3174
-1.750 0.3677 0.02420 0.01377 -0.1250 0.8299 0.3301
-1.500 0.4018 0.02382 0.01312 -0.1257 0.8174 0.3428
-1.250 0.4347 0.02350 0.01257 -0.1261 0.8045 0.3560
-1.000 0.4648 0.02325 0.01213 -0.1260 0.7899 0.3685
-0.750 0.4940 0.02300 0.01175 -0.1257 0.7748 0.3809
-0.500 0.5224 0.02279 0.01143 -0.1253 0.7599 0.3933
-0.250 0.5502 0.02264 0.01118 -0.1249 0.7457 0.4070
0.000 0.5777 0.02252 0.01101 -0.1245 0.7319 0.4230
0.250 0.6051 0.02239 0.01085 -0.1241 0.7182 0.4410
0.500 0.6323 0.02225 0.01072 -0.1236 0.7041 0.4640
0.750 0.6590 0.02204 0.01060 -0.1231 0.6899 0.4970
1.000 0.6843 0.02164 0.01050 -0.1222 0.6755 0.5602
1.250 0.7051 0.02093 0.01033 -0.1200 0.6609 1.0000
1.500 0.7325 0.02115 0.01030 -0.1195 0.6457 1.0000
1.750 0.7594 0.02139 0.01033 -0.1190 0.6303 1.0000
2.000 0.7860 0.02165 0.01042 -0.1185 0.6149 1.0000
2.250 0.8123 0.02193 0.01054 -0.1179 0.5990 1.0000
2.500 0.8383 0.02224 0.01072 -0.1173 0.5830 1.0000
2.750 0.8642 0.02258 0.01092 -0.1167 0.5670 1.0000
3.000 0.8899 0.02295 0.01118 -0.1161 0.5515 1.0000
3.250 0.9155 0.02337 0.01152 -0.1156 0.5367 1.0000
3.500 0.9411 0.02382 0.01190 -0.1151 0.5231 1.0000
3.750 0.9671 0.02431 0.01231 -0.1147 0.5112 1.0000
4.000 0.9930 0.02481 0.01279 -0.1143 0.5003 1.0000
4.250 1.0175 0.02541 0.01341 -0.1139 0.4894 1.0000
4.500 1.0430 0.02597 0.01396 -0.1135 0.4803 1.0000
4.750 1.0679 0.02656 0.01458 -0.1130 0.4714 1.0000
5.000 1.0923 0.02721 0.01532 -0.1126 0.4633 1.0000
5.250 1.1174 0.02783 0.01598 -0.1122 0.4563 1.0000
5.500 1.1419 0.02854 0.01679 -0.1118 0.4501 1.0000
5.750 1.1657 0.02928 0.01769 -0.1113 0.4437 1.0000
6.000 1.1900 0.02987 0.01833 -0.1108 0.4368 1.0000
6.250 1.2114 0.03046 0.01902 -0.1098 0.4271 1.0000
6.500 1.2317 0.03101 0.01967 -0.1086 0.4162 1.0000
6.750 1.2522 0.03144 0.02017 -0.1074 0.4047 1.0000
7.000 1.2726 0.03181 0.02055 -0.1060 0.3926 1.0000
7.250 1.2925 0.03225 0.02100 -0.1047 0.3807 1.0000
7.500 1.3099 0.03296 0.02185 -0.1032 0.3694 1.0000
7.750 1.3297 0.03369 0.02273 -0.1021 0.3606 1.0000
8.000 1.3503 0.03445 0.02364 -0.1011 0.3532 1.0000
8.250 1.3704 0.03532 0.02469 -0.1001 0.3467 1.0000
8.500 1.3889 0.03627 0.02587 -0.0989 0.3398 1.0000
8.750 1.4109 0.03708 0.02681 -0.0981 0.3337 1.0000
9.000 1.4251 0.03829 0.02836 -0.0966 0.3268 1.0000
9.250 1.4468 0.03914 0.02943 -0.0957 0.3208 1.0000
9.500 1.4571 0.04046 0.03109 -0.0937 0.3128 1.0000
9.750 1.4682 0.04130 0.03206 -0.0915 0.3013 1.0000
10.000 1.4697 0.04227 0.03317 -0.0882 0.2871 1.0000
10.250 1.4638 0.04355 0.03464 -0.0843 0.2740 1.0000
10.500 1.4534 0.04550 0.03688 -0.0807 0.2621 1.0000
10.750 1.4452 0.04770 0.03935 -0.0780 0.2508 1.0000
11.000 1.4378 0.05022 0.04212 -0.0759 0.2399 1.0000
11.250 1.4293 0.05319 0.04535 -0.0746 0.2284 1.0000
11.500 1.4184 0.05688 0.04931 -0.0739 0.2170 1.0000
11.750 1.4053 0.06123 0.05392 -0.0738 0.2059 1.0000
12.000 1.3934 0.06561 0.05847 -0.0740 0.1945 1.0000
12.250 1.3842 0.06970 0.06263 -0.0743 0.1825 1.0000
12.500 1.3759 0.07374 0.06670 -0.0746 0.1712 1.0000
12.750 1.3661 0.07810 0.07105 -0.0751 0.1600 1.0000
13.250 1.3381 0.08885 0.08190 -0.0773 0.1406 1.0000
13.500 1.3238 0.09447 0.08756 -0.0788 0.1307 1.0000
13.750 1.3100 0.10021 0.09334 -0.0804 0.1206 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)