GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 100,000 Max Cl/Cd: 58.85 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe331-il-100000.txt Download as CSV file: xf-goe331-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2590 0.13089 0.12623 -0.0314 1.0000 0.0430
-10.000 -0.2756 0.13145 0.12688 -0.0289 1.0000 0.0432
-9.750 -0.2933 0.13214 0.12767 -0.0268 1.0000 0.0433
-9.250 -0.2972 0.12690 0.12253 -0.0222 1.0000 0.0441
-9.000 -0.3020 0.12520 0.12088 -0.0202 1.0000 0.0447
-8.750 -0.2884 0.12184 0.11752 -0.0231 0.9967 0.0458
-8.500 -0.2720 0.11839 0.11406 -0.0273 0.9922 0.0472
-8.250 -0.2575 0.11529 0.11096 -0.0318 0.9866 0.0485
-8.000 -0.2481 0.11327 0.10893 -0.0370 0.9800 0.0496
-7.750 -0.2425 0.11224 0.10792 -0.0449 0.9712 0.0500
-7.500 -0.2312 0.10817 0.10386 -0.0460 0.9646 0.0505
-7.250 -0.2120 0.10349 0.09917 -0.0460 0.9609 0.0516
-7.000 -0.1890 0.09970 0.09536 -0.0505 0.9566 0.0534
-6.750 -0.1828 0.09740 0.09308 -0.0523 0.9472 0.0550
-6.500 -0.1574 0.09488 0.09050 -0.0629 0.9394 0.0577
-6.250 -0.1399 0.09297 0.08851 -0.0719 0.9288 0.0583
-6.000 -0.1242 0.08779 0.08338 -0.0691 0.9266 0.0594
-5.750 -0.1188 0.08541 0.08102 -0.0683 0.9184 0.0606
-5.500 -0.0957 0.08219 0.07777 -0.0721 0.9127 0.0628
-5.250 -0.0741 0.07955 0.07507 -0.0766 0.9058 0.0655
-5.000 -0.0331 0.07767 0.07291 -0.0889 0.8972 0.0681
-4.750 -0.0148 0.07283 0.06817 -0.0882 0.8946 0.0696
-4.500 -0.0121 0.07108 0.06645 -0.0862 0.8849 0.0712
-4.250 0.0541 0.06998 0.06482 -0.1003 0.8798 0.0791
-3.750 0.0725 0.06299 0.05806 -0.0975 0.8667 0.0823
-3.500 0.1412 0.06157 0.05609 -0.1086 0.8630 0.0920
-3.250 0.1409 0.05849 0.05317 -0.1056 0.8528 0.0932
-3.000 0.1783 0.05478 0.04948 -0.1089 0.8486 0.0987
-2.750 0.2405 0.05101 0.04545 -0.1171 0.8461 0.1099
-2.500 0.2515 0.05000 0.04439 -0.1153 0.8338 0.1167
-2.250 0.3146 0.04703 0.04105 -0.1229 0.8311 0.1386
-2.000 0.3273 0.04514 0.03925 -0.1213 0.8204 0.1464
-1.750 0.3781 0.04213 0.03605 -0.1261 0.8164 0.1734
-1.500 0.4272 0.03953 0.03326 -0.1303 0.8136 0.2203
-1.250 0.4383 0.03802 0.03188 -0.1282 0.8022 0.2437
-1.000 0.4728 0.03539 0.02930 -0.1295 0.7984 0.3121
-0.750 0.4951 0.03377 0.02774 -0.1287 0.7908 0.3649
-0.500 0.5236 0.03203 0.02599 -0.1286 0.7835 0.4129
-0.250 0.5647 0.02978 0.02371 -0.1300 0.7797 0.4552
0.000 0.5923 0.02922 0.02297 -0.1301 0.7689 0.4595
0.250 0.6550 0.02834 0.02130 -0.1352 0.7637 0.3585
0.500 0.6972 0.02857 0.02080 -0.1353 0.7542 0.2309
0.750 0.7397 0.02771 0.01944 -0.1352 0.7473 0.1621
1.000 0.7699 0.02726 0.01867 -0.1340 0.7379 0.1340
1.250 0.8052 0.02625 0.01743 -0.1338 0.7301 0.1188
1.500 0.8312 0.02554 0.01668 -0.1327 0.7195 0.1137
1.750 0.8675 0.02442 0.01541 -0.1328 0.7118 0.1107
2.000 0.8916 0.02408 0.01499 -0.1313 0.6991 0.1070
2.250 0.9198 0.02337 0.01426 -0.1304 0.6879 0.1052
2.500 0.9522 0.02239 0.01320 -0.1301 0.6780 0.1045
2.750 0.9772 0.02196 0.01271 -0.1288 0.6635 0.1050
3.000 1.0038 0.02150 0.01215 -0.1279 0.6484 0.1073
3.250 1.0311 0.02104 0.01161 -0.1270 0.6319 0.1161
3.500 1.0588 0.02065 0.01109 -0.1262 0.6140 0.1284
3.750 1.0835 0.01897 0.01081 -0.1250 0.5952 1.0000
4.000 1.1059 0.01913 0.01071 -0.1234 0.5726 1.0000
4.250 1.1306 0.01933 0.01060 -0.1224 0.5517 1.0000
4.500 1.1555 0.01964 0.01060 -0.1215 0.5325 1.0000
4.750 1.1799 0.02005 0.01076 -0.1208 0.5150 1.0000
5.000 1.2034 0.02054 0.01107 -0.1200 0.4991 1.0000
5.250 1.2262 0.02108 0.01149 -0.1192 0.4849 1.0000
5.500 1.2496 0.02166 0.01196 -0.1185 0.4730 1.0000
5.750 1.2758 0.02221 0.01237 -0.1183 0.4634 1.0000
6.000 1.2987 0.02283 0.01296 -0.1177 0.4537 1.0000
6.250 1.3238 0.02345 0.01350 -0.1174 0.4457 1.0000
6.500 1.3470 0.02408 0.01414 -0.1168 0.4375 1.0000
6.750 1.3730 0.02474 0.01471 -0.1168 0.4307 1.0000
7.000 1.3944 0.02547 0.01552 -0.1160 0.4238 1.0000
7.250 1.4220 0.02613 0.01610 -0.1162 0.4182 1.0000
7.500 1.4439 0.02697 0.01705 -0.1156 0.4127 1.0000
7.750 1.4653 0.02776 0.01793 -0.1148 0.4068 1.0000
8.000 1.4940 0.02846 0.01854 -0.1153 0.4017 1.0000
8.250 1.5132 0.02944 0.01970 -0.1143 0.3968 1.0000
8.500 1.5327 0.03038 0.02079 -0.1134 0.3918 1.0000
8.750 1.5591 0.03114 0.02153 -0.1135 0.3868 1.0000
9.000 1.5788 0.03212 0.02262 -0.1126 0.3812 1.0000
9.250 1.5947 0.03304 0.02373 -0.1111 0.3750 1.0000
9.500 1.6245 0.03372 0.02432 -0.1117 0.3693 1.0000
9.750 1.6368 0.03495 0.02579 -0.1098 0.3643 1.0000
10.000 1.6511 0.03608 0.02712 -0.1082 0.3592 1.0000
10.250 1.6770 0.03693 0.02801 -0.1083 0.3543 1.0000
10.500 1.6943 0.03823 0.02947 -0.1073 0.3497 1.0000
10.750 1.7003 0.03971 0.03124 -0.1046 0.3450 1.0000
11.000 1.7180 0.04085 0.03252 -0.1036 0.3402 1.0000
11.250 1.7531 0.04186 0.03349 -0.1052 0.3355 1.0000
11.500 1.7411 0.04387 0.03593 -0.1001 0.3310 1.0000
11.750 1.7484 0.04519 0.03744 -0.0978 0.3253 1.0000
12.000 1.7797 0.04552 0.03772 -0.0984 0.3175 1.0000
12.250 1.7640 0.04736 0.03988 -0.0930 0.3117 1.0000
12.500 1.7967 0.04654 0.03891 -0.0934 0.3005 1.0000
12.750 1.7765 0.04823 0.04087 -0.0873 0.2949 1.0000
13.000 1.8047 0.04731 0.03980 -0.0871 0.2843 1.0000
13.250 1.7785 0.04943 0.04223 -0.0809 0.2796 1.0000
13.500 1.8111 0.04817 0.04079 -0.0810 0.2695 1.0000
13.750 1.7775 0.05103 0.04401 -0.0749 0.2656 1.0000
14.000 1.7654 0.05274 0.04589 -0.0714 0.2596 1.0000
14.250 1.7756 0.05291 0.04607 -0.0697 0.2522 1.0000
14.500 1.7467 0.05652 0.04998 -0.0660 0.2476 1.0000
14.750 1.7691 0.05542 0.04879 -0.0651 0.2389 1.0000
15.000 1.7323 0.06037 0.05411 -0.0620 0.2350 1.0000
15.250 1.7125 0.06389 0.05784 -0.0602 0.2292 1.0000
15.500 1.7106 0.06547 0.05950 -0.0590 0.2218 1.0000
15.750 1.6767 0.07144 0.06575 -0.0581 0.2171 1.0000
16.000 1.6763 0.07311 0.06745 -0.0576 0.2082 1.0000
16.250 1.6368 0.08092 0.07555 -0.0580 0.2039 1.0000
16.500 1.6295 0.08415 0.07885 -0.0584 0.1941 1.0000
16.750 1.5844 0.09401 0.08896 -0.0606 0.1909 1.0000
17.000 1.5723 0.09871 0.09372 -0.0620 0.1803 1.0000
17.250 1.5189 0.11109 0.10628 -0.0660 0.1789 1.0000
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Polar data table (+)
Polar graphs
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