GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 500,000 Max Cl/Cd: 105.72 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe300-il-500000-n5.txt Download as CSV file: xf-goe300-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1826 0.08761 0.08515 -0.0472 0.8782 0.0100
-8.000 -0.1768 0.08419 0.08169 -0.0491 0.8653 0.0101
-7.750 -0.1734 0.07985 0.07731 -0.0522 0.8524 0.0105
-7.500 -0.1641 0.07491 0.07234 -0.0573 0.8404 0.0109
-7.250 -0.1491 0.07176 0.06914 -0.0609 0.8286 0.0111
-7.000 -0.1322 0.06860 0.06591 -0.0648 0.8162 0.0113
-6.750 -0.1135 0.06510 0.06234 -0.0692 0.8029 0.0115
-6.500 -0.0929 0.06096 0.05812 -0.0745 0.7890 0.0119
-6.000 -0.0276 0.02850 0.02449 -0.1095 0.7694 0.0168
-5.750 -0.0011 0.02786 0.02377 -0.1098 0.7540 0.0177
-5.500 0.0265 0.02224 0.01760 -0.1126 0.7409 0.0196
-5.250 0.0516 0.01583 0.01039 -0.1145 0.7284 0.0222
-5.000 0.0770 0.01315 0.00726 -0.1148 0.7144 0.0248
-4.750 0.1041 0.01252 0.00647 -0.1147 0.7003 0.0277
-4.500 0.1314 0.01210 0.00590 -0.1145 0.6868 0.0313
-4.250 0.1592 0.01221 0.00598 -0.1143 0.6729 0.0343
-4.000 0.1870 0.01227 0.00596 -0.1141 0.6596 0.0373
-3.750 0.2145 0.01193 0.00541 -0.1139 0.6477 0.0401
-3.500 0.2423 0.01218 0.00564 -0.1137 0.6353 0.0419
-3.250 0.2702 0.01250 0.00593 -0.1135 0.6219 0.0436
-3.000 0.2980 0.01257 0.00593 -0.1133 0.6098 0.0456
-2.750 0.3256 0.01240 0.00560 -0.1132 0.5995 0.0480
-2.500 0.3534 0.01228 0.00534 -0.1130 0.5904 0.0496
-2.250 0.3810 0.01194 0.00488 -0.1129 0.5829 0.0511
-2.000 0.4089 0.01188 0.00478 -0.1128 0.5751 0.0526
-1.750 0.4366 0.01181 0.00465 -0.1127 0.5679 0.0537
-1.500 0.4644 0.01172 0.00449 -0.1126 0.5600 0.0551
-1.250 0.4920 0.01154 0.00421 -0.1125 0.5527 0.0563
-1.000 0.5198 0.01131 0.00391 -0.1124 0.5455 0.0574
-0.750 0.5473 0.01114 0.00364 -0.1122 0.5386 0.0585
-0.500 0.5751 0.01102 0.00346 -0.1121 0.5324 0.0597
-0.250 0.6027 0.01095 0.00333 -0.1120 0.5246 0.0606
0.000 0.6301 0.01087 0.00319 -0.1118 0.5167 0.0610
0.250 0.6573 0.01065 0.00292 -0.1117 0.5078 0.0624
0.500 0.6848 0.01057 0.00282 -0.1115 0.5005 0.0635
0.750 0.7122 0.01053 0.00275 -0.1114 0.4924 0.0645
1.000 0.7396 0.01052 0.00272 -0.1113 0.4839 0.0656
1.250 0.7668 0.01053 0.00269 -0.1111 0.4737 0.0667
1.500 0.7941 0.01054 0.00267 -0.1110 0.4639 0.0681
1.750 0.8211 0.01058 0.00267 -0.1108 0.4534 0.0697
2.000 0.8480 0.01066 0.00270 -0.1106 0.4399 0.0717
2.250 0.8746 0.01075 0.00274 -0.1104 0.4248 0.0734
2.500 0.9013 0.01082 0.00278 -0.1102 0.4106 0.0767
2.750 0.9278 0.01094 0.00287 -0.1100 0.3971 0.0800
3.000 0.9541 0.01109 0.00297 -0.1097 0.3844 0.0837
3.250 0.9802 0.01126 0.00309 -0.1095 0.3723 0.0875
3.750 1.0324 0.01159 0.00339 -0.1090 0.3522 0.0998
4.000 1.0585 0.01175 0.00355 -0.1087 0.3449 0.1078
4.500 1.1110 0.01204 0.00389 -0.1083 0.3336 0.1302
4.750 1.1367 0.01222 0.00410 -0.1081 0.3276 0.1550
5.250 1.1859 0.01127 0.00461 -0.1073 0.3171 1.0000
5.500 1.2110 0.01153 0.00483 -0.1069 0.3113 1.0000
5.750 1.2368 0.01173 0.00503 -0.1066 0.3062 1.0000
6.000 1.2623 0.01194 0.00525 -0.1063 0.3004 1.0000
6.250 1.2871 0.01221 0.00549 -0.1059 0.2951 1.0000
6.500 1.3124 0.01242 0.00573 -0.1056 0.2889 1.0000
6.750 1.3369 0.01269 0.00598 -0.1052 0.2806 1.0000
7.000 1.3614 0.01296 0.00625 -0.1048 0.2720 1.0000
7.250 1.3850 0.01328 0.00655 -0.1042 0.2608 1.0000
7.500 1.4081 0.01363 0.00686 -0.1036 0.2451 1.0000
7.750 1.4285 0.01419 0.00728 -0.1027 0.2165 1.0000
8.000 1.4459 0.01497 0.00787 -0.1013 0.1872 1.0000
8.250 1.4650 0.01557 0.00842 -0.1002 0.1754 1.0000
8.500 1.4856 0.01603 0.00889 -0.0992 0.1696 1.0000
8.750 1.5037 0.01665 0.00948 -0.0979 0.1618 1.0000
9.000 1.5229 0.01715 0.01001 -0.0968 0.1548 1.0000
9.250 1.5396 0.01777 0.01062 -0.0953 0.1476 1.0000
9.500 1.5564 0.01827 0.01115 -0.0937 0.1428 1.0000
9.750 1.5738 0.01873 0.01166 -0.0923 0.1380 1.0000
10.000 1.5881 0.01939 0.01232 -0.0905 0.1312 1.0000
10.250 1.6037 0.01997 0.01295 -0.0890 0.1260 1.0000
10.500 1.6184 0.02063 0.01362 -0.0874 0.1185 1.0000
10.750 1.6310 0.02143 0.01442 -0.0856 0.1104 1.0000
11.000 1.6413 0.02241 0.01537 -0.0837 0.0990 1.0000
11.250 1.6481 0.02367 0.01657 -0.0815 0.0852 1.0000
11.500 1.6504 0.02532 0.01814 -0.0791 0.0695 1.0000
11.750 1.6411 0.02797 0.02063 -0.0760 0.0415 1.0000
12.000 1.6322 0.03080 0.02339 -0.0733 0.0256 1.0000
12.250 1.6332 0.03294 0.02559 -0.0717 0.0208 1.0000
12.500 1.6346 0.03514 0.02785 -0.0703 0.0179 1.0000
12.750 1.6372 0.03733 0.03012 -0.0692 0.0160 1.0000
13.000 1.6382 0.03974 0.03261 -0.0681 0.0145 1.0000
13.250 1.6405 0.04210 0.03507 -0.0673 0.0135 1.0000
13.500 1.6408 0.04476 0.03783 -0.0666 0.0126 1.0000
13.750 1.6386 0.04773 0.04089 -0.0660 0.0118 1.0000
14.000 1.6387 0.05055 0.04382 -0.0656 0.0112 1.0000
14.250 1.6373 0.05363 0.04701 -0.0653 0.0106 1.0000
14.500 1.6343 0.05698 0.05045 -0.0652 0.0101 1.0000
14.750 1.6294 0.06063 0.05420 -0.0651 0.0097 1.0000
15.000 1.6237 0.06450 0.05817 -0.0653 0.0093 1.0000
15.250 1.6193 0.06825 0.06205 -0.0655 0.0090 1.0000
15.500 1.6137 0.07224 0.06615 -0.0659 0.0087 1.0000
15.750 1.6069 0.07644 0.07047 -0.0663 0.0084 1.0000
16.000 1.5990 0.08089 0.07503 -0.0670 0.0082 1.0000
16.250 1.5903 0.08554 0.07979 -0.0678 0.0079 1.0000
16.500 1.5803 0.09043 0.08479 -0.0687 0.0078 1.0000
16.750 1.5694 0.09556 0.09005 -0.0698 0.0076 1.0000
17.000 1.5574 0.10096 0.09556 -0.0712 0.0075 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)