GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 200,000 Max Cl/Cd: 64.61 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe711-il-200000.txt Download as CSV file: xf-goe711-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1699 0.09961 0.09642 -0.0662 0.9664 0.0435
-7.750 -0.1714 0.09489 0.09170 -0.0785 0.9574 0.0447
-7.500 -0.1654 0.08894 0.08564 -0.0906 0.9452 0.0450
-7.250 -0.1462 0.08446 0.08125 -0.0874 0.9443 0.0458
-7.000 -0.1205 0.08092 0.07770 -0.0889 0.9426 0.0468
-6.750 -0.1112 0.07788 0.07465 -0.0900 0.9330 0.0479
-6.500 -0.0848 0.07321 0.06991 -0.0969 0.9292 0.0505
-6.250 -0.0643 0.06760 0.06368 -0.1103 0.9168 0.0541
-6.000 -0.0411 0.06150 0.05781 -0.1122 0.9149 0.0552
-5.750 -0.0089 0.05801 0.05432 -0.1155 0.9133 0.0567
-5.500 0.0268 0.05418 0.05037 -0.1204 0.9116 0.0596
-5.250 0.0480 0.05044 0.04597 -0.1233 0.8999 0.0658
-5.000 0.0784 0.04625 0.04194 -0.1260 0.8978 0.0676
-4.750 0.0969 0.04410 0.03976 -0.1256 0.8883 0.0699
-4.250 0.1592 0.03795 0.03303 -0.1298 0.8778 0.0811
-4.000 0.1866 0.03581 0.03085 -0.1306 0.8710 0.0850
-3.750 0.2224 0.03325 0.02793 -0.1329 0.8673 0.0962
-3.500 0.2448 0.03163 0.02630 -0.1324 0.8565 0.1015
-3.250 0.2770 0.02954 0.02395 -0.1338 0.8501 0.1135
-3.000 0.3048 0.02812 0.02230 -0.1342 0.8399 0.1284
-2.750 0.3323 0.02671 0.02075 -0.1345 0.8292 0.1450
-2.500 0.3620 0.02506 0.01906 -0.1354 0.8197 0.1637
-1.750 0.4661 0.02044 0.01273 -0.1337 0.7816 0.0784
-1.500 0.4949 0.01859 0.01074 -0.1337 0.7675 0.0749
-1.250 0.5238 0.01787 0.00983 -0.1336 0.7523 0.0751
-1.000 0.5520 0.01718 0.00896 -0.1333 0.7364 0.0745
-0.750 0.5797 0.01660 0.00823 -0.1329 0.7198 0.0739
-0.500 0.6067 0.01615 0.00766 -0.1325 0.7028 0.0742
-0.250 0.6333 0.01581 0.00721 -0.1321 0.6857 0.0751
0.000 0.6595 0.01560 0.00688 -0.1316 0.6684 0.0771
0.250 0.6852 0.01530 0.00650 -0.1312 0.6509 0.0803
0.500 0.7107 0.01512 0.00623 -0.1308 0.6334 0.0839
0.750 0.7361 0.01507 0.00607 -0.1303 0.6156 0.0887
1.000 0.7614 0.01506 0.00593 -0.1298 0.5982 0.0969
1.250 0.7860 0.01465 0.00591 -0.1295 0.5815 0.2532
1.500 0.8068 0.01313 0.00599 -0.1274 0.5659 1.0000
1.750 0.8309 0.01341 0.00603 -0.1268 0.5498 1.0000
2.000 0.8549 0.01371 0.00613 -0.1261 0.5346 1.0000
2.250 0.8790 0.01402 0.00624 -0.1255 0.5206 1.0000
2.500 0.9030 0.01432 0.00640 -0.1250 0.5070 1.0000
2.750 0.9270 0.01462 0.00658 -0.1244 0.4942 1.0000
3.000 0.9511 0.01495 0.00678 -0.1239 0.4826 1.0000
3.250 0.9754 0.01531 0.00697 -0.1235 0.4721 1.0000
3.500 0.9993 0.01561 0.00721 -0.1229 0.4615 1.0000
3.750 1.0238 0.01597 0.00746 -0.1225 0.4524 1.0000
4.000 1.0481 0.01631 0.00770 -0.1221 0.4439 1.0000
4.250 1.0727 0.01667 0.00800 -0.1218 0.4360 1.0000
4.500 1.0970 0.01702 0.00827 -0.1214 0.4284 1.0000
4.750 1.1217 0.01739 0.00858 -0.1212 0.4214 1.0000
5.000 1.1455 0.01773 0.00890 -0.1207 0.4144 1.0000
5.250 1.1714 0.01817 0.00921 -0.1207 0.4085 1.0000
5.500 1.1946 0.01850 0.00959 -0.1202 0.4023 1.0000
5.750 1.2193 0.01888 0.00993 -0.1199 0.3969 1.0000
6.000 1.2454 0.01933 0.01032 -0.1200 0.3919 1.0000
6.250 1.2682 0.01969 0.01073 -0.1195 0.3865 1.0000
6.500 1.2919 0.02007 0.01108 -0.1191 0.3813 1.0000
6.750 1.3159 0.02052 0.01149 -0.1188 0.3758 1.0000
7.000 1.3354 0.02085 0.01189 -0.1176 0.3697 1.0000
7.250 1.3581 0.02124 0.01223 -0.1170 0.3645 1.0000
7.500 1.3807 0.02170 0.01271 -0.1166 0.3596 1.0000
7.750 1.4007 0.02209 0.01319 -0.1155 0.3549 1.0000
8.000 1.4231 0.02251 0.01362 -0.1150 0.3508 1.0000
8.250 1.4511 0.02304 0.01408 -0.1156 0.3470 1.0000
8.500 1.4678 0.02347 0.01466 -0.1139 0.3428 1.0000
8.750 1.4842 0.02387 0.01513 -0.1123 0.3379 1.0000
9.000 1.5021 0.02426 0.01548 -0.1109 0.3328 1.0000
9.250 1.5135 0.02473 0.01604 -0.1083 0.3274 1.0000
9.500 1.5231 0.02516 0.01656 -0.1055 0.3218 1.0000
9.750 1.5399 0.02563 0.01698 -0.1041 0.3166 1.0000
10.000 1.5487 0.02620 0.01769 -0.1013 0.3113 1.0000
10.250 1.5576 0.02675 0.01834 -0.0986 0.3055 1.0000
10.500 1.5727 0.02733 0.01885 -0.0971 0.3001 1.0000
10.750 1.5791 0.02804 0.01977 -0.0942 0.2948 1.0000
11.000 1.5887 0.02874 0.02055 -0.0920 0.2894 1.0000
11.250 1.6014 0.02947 0.02125 -0.0903 0.2845 1.0000
11.500 1.6090 0.03033 0.02234 -0.0880 0.2792 1.0000
11.750 1.6152 0.03128 0.02334 -0.0856 0.2726 1.0000
12.000 1.6214 0.03234 0.02451 -0.0834 0.2658 1.0000
12.250 1.6263 0.03353 0.02578 -0.0812 0.2582 1.0000
12.500 1.6320 0.03481 0.02718 -0.0793 0.2503 1.0000
12.750 1.6349 0.03633 0.02876 -0.0772 0.2420 1.0000
13.000 1.6378 0.03801 0.03055 -0.0754 0.2305 1.0000
13.250 1.6378 0.04004 0.03263 -0.0735 0.2170 1.0000
13.500 1.6316 0.04279 0.03536 -0.0715 0.1984 1.0000
13.750 1.6186 0.04641 0.03889 -0.0694 0.1717 1.0000
14.000 1.5958 0.05130 0.04363 -0.0674 0.1425 1.0000
14.250 1.5700 0.05688 0.04911 -0.0657 0.1201 1.0000
14.500 1.5434 0.06291 0.05511 -0.0647 0.0967 1.0000
14.750 1.5138 0.06968 0.06184 -0.0642 0.0645 1.0000
15.000 1.4868 0.07648 0.06868 -0.0643 0.0583 1.0000
15.250 1.4635 0.08304 0.07538 -0.0647 0.0528 1.0000
15.500 1.4411 0.08970 0.08219 -0.0655 0.0492 1.0000
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Polar data table (+)
Polar graphs
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