GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 200,000 Max Cl/Cd: 73.73 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe176-il-200000.txt Download as CSV file: xf-goe176-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3071 0.10011 0.09682 -0.0338 1.0000 0.0447
-8.250 -0.3136 0.09782 0.09461 -0.0344 1.0000 0.0449
-8.000 -0.3209 0.09562 0.09250 -0.0339 1.0000 0.0450
-7.750 -0.3179 0.09061 0.08753 -0.0316 1.0000 0.0462
-7.500 -0.3121 0.08858 0.08555 -0.0292 1.0000 0.0473
-7.250 -0.3155 0.08698 0.08402 -0.0268 1.0000 0.0483
-7.000 -0.3249 0.08560 0.08275 -0.0243 1.0000 0.0492
-6.750 -0.3210 0.08309 0.08028 -0.0258 0.9976 0.0510
-6.500 -0.2695 0.07136 0.06849 -0.0558 0.9860 0.0574
-6.250 -0.2533 0.07068 0.06783 -0.0491 0.9826 0.0601
-6.000 -0.1349 0.04829 0.04557 -0.0638 0.9485 0.0746
-5.750 -0.1818 0.05992 0.05697 -0.0686 0.9640 0.0726
-5.500 -0.0795 0.03768 0.03485 -0.0791 0.9323 0.0881
-5.250 -0.0679 0.02718 0.02230 -0.1104 0.9480 0.0435
-5.000 -0.0296 0.02260 0.01707 -0.1140 0.9397 0.0406
-4.750 0.0134 0.02024 0.01420 -0.1172 0.9343 0.0422
-4.500 0.0530 0.01839 0.01195 -0.1194 0.9250 0.0434
-4.250 0.0957 0.01679 0.01003 -0.1219 0.9163 0.0445
-4.000 0.1370 0.01486 0.00797 -0.1245 0.9058 0.0479
-3.750 0.1755 0.01387 0.00692 -0.1264 0.8922 0.0534
-3.500 0.2113 0.01306 0.00597 -0.1276 0.8771 0.0586
-3.250 0.2441 0.01244 0.00526 -0.1283 0.8610 0.0711
-3.000 0.2745 0.01163 0.00483 -0.1287 0.8446 0.1625
-2.750 0.3034 0.01212 0.00514 -0.1283 0.8277 0.2212
-2.500 0.3310 0.01243 0.00528 -0.1278 0.8110 0.2421
-2.250 0.3583 0.01258 0.00530 -0.1273 0.7948 0.2567
-2.000 0.3854 0.01269 0.00529 -0.1268 0.7788 0.2704
-1.750 0.4123 0.01270 0.00524 -0.1263 0.7633 0.2828
-1.500 0.4391 0.01268 0.00516 -0.1259 0.7477 0.2953
-1.250 0.4660 0.01260 0.00497 -0.1254 0.7315 0.3042
-1.000 0.4930 0.01254 0.00481 -0.1249 0.7163 0.3123
-0.750 0.5201 0.01245 0.00463 -0.1245 0.7018 0.3197
-0.500 0.5472 0.01240 0.00451 -0.1241 0.6877 0.3279
-0.250 0.5741 0.01233 0.00440 -0.1237 0.6737 0.3368
0.000 0.6011 0.01232 0.00431 -0.1233 0.6595 0.3470
0.250 0.6278 0.01227 0.00425 -0.1229 0.6449 0.3570
0.500 0.6544 0.01223 0.00419 -0.1225 0.6296 0.3672
0.750 0.6809 0.01221 0.00416 -0.1220 0.6134 0.3797
1.000 0.7071 0.01221 0.00417 -0.1215 0.5955 0.3959
1.250 0.7330 0.01221 0.00419 -0.1210 0.5756 0.4180
1.500 0.7582 0.01221 0.00422 -0.1203 0.5533 0.4557
1.750 0.7784 0.01153 0.00429 -0.1186 0.5288 0.7266
2.000 0.8013 0.01140 0.00422 -0.1170 0.5011 1.0000
2.250 0.8263 0.01168 0.00429 -0.1163 0.4727 1.0000
2.500 0.8514 0.01196 0.00437 -0.1157 0.4472 1.0000
2.750 0.8768 0.01224 0.00449 -0.1152 0.4266 1.0000
3.000 0.9022 0.01254 0.00466 -0.1147 0.4114 1.0000
3.250 0.9278 0.01285 0.00486 -0.1142 0.4001 1.0000
3.500 0.9531 0.01319 0.00507 -0.1137 0.3910 1.0000
3.750 0.9787 0.01351 0.00531 -0.1133 0.3811 1.0000
4.000 1.0040 0.01386 0.00559 -0.1128 0.3725 1.0000
4.250 1.0295 0.01421 0.00588 -0.1124 0.3654 1.0000
4.500 1.0550 0.01457 0.00619 -0.1120 0.3594 1.0000
4.750 1.0806 0.01489 0.00651 -0.1116 0.3526 1.0000
5.000 1.1055 0.01533 0.00687 -0.1111 0.3459 1.0000
5.250 1.1310 0.01561 0.00721 -0.1107 0.3392 1.0000
5.500 1.1561 0.01602 0.00757 -0.1103 0.3336 1.0000
5.750 1.1815 0.01636 0.00797 -0.1099 0.3286 1.0000
6.000 1.2067 0.01666 0.00834 -0.1094 0.3231 1.0000
6.250 1.2315 0.01708 0.00873 -0.1090 0.3181 1.0000
6.500 1.2564 0.01741 0.00914 -0.1085 0.3132 1.0000
6.750 1.2810 0.01770 0.00955 -0.1079 0.3075 1.0000
7.000 1.3049 0.01814 0.00996 -0.1073 0.3016 1.0000
7.250 1.3284 0.01833 0.01033 -0.1066 0.2938 1.0000
7.500 1.3507 0.01866 0.01069 -0.1057 0.2849 1.0000
7.750 1.3730 0.01882 0.01098 -0.1048 0.2731 1.0000
8.000 1.3961 0.01903 0.01133 -0.1040 0.2625 1.0000
8.250 1.4186 0.01927 0.01167 -0.1032 0.2497 1.0000
8.500 1.4406 0.01954 0.01202 -0.1023 0.2307 1.0000
8.750 1.4598 0.02001 0.01243 -0.1010 0.1972 1.0000
9.000 1.4700 0.02121 0.01330 -0.0986 0.1571 1.0000
9.250 1.4807 0.02246 0.01442 -0.0963 0.1346 1.0000
9.500 1.4933 0.02351 0.01544 -0.0943 0.1168 1.0000
9.750 1.5052 0.02452 0.01643 -0.0921 0.0964 1.0000
10.000 1.5057 0.02610 0.01780 -0.0884 0.0667 1.0000
10.250 1.5065 0.02772 0.01942 -0.0849 0.0586 1.0000
10.500 1.5059 0.02950 0.02129 -0.0815 0.0528 1.0000
10.750 1.5107 0.03099 0.02297 -0.0791 0.0467 1.0000
11.000 1.5115 0.03289 0.02501 -0.0766 0.0408 1.0000
11.250 1.5171 0.03454 0.02675 -0.0747 0.0337 1.0000
11.500 1.5220 0.03634 0.02865 -0.0732 0.0286 1.0000
11.750 1.5227 0.03864 0.03100 -0.0717 0.0261 1.0000
12.000 1.5219 0.04125 0.03372 -0.0705 0.0247 1.0000
12.250 1.5189 0.04422 0.03682 -0.0696 0.0237 1.0000
12.500 1.5138 0.04761 0.04037 -0.0690 0.0229 1.0000
12.750 1.5061 0.05148 0.04437 -0.0688 0.0223 1.0000
13.000 1.4961 0.05583 0.04887 -0.0689 0.0218 1.0000
13.250 1.4836 0.06067 0.05386 -0.0694 0.0214 1.0000
13.500 1.4699 0.06580 0.05915 -0.0702 0.0211 1.0000
13.750 1.4570 0.07097 0.06444 -0.0710 0.0209 1.0000
14.000 1.4457 0.07597 0.06960 -0.0719 0.0206 1.0000
14.250 1.4350 0.08100 0.07476 -0.0729 0.0203 1.0000
14.500 1.4254 0.08594 0.07982 -0.0739 0.0200 1.0000
14.750 1.4169 0.09069 0.08469 -0.0749 0.0197 1.0000
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Polar data table (+)
Polar graphs
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