GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 200,000 Max Cl/Cd: 75.64 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe282-il-200000-n5.txt Download as CSV file: xf-goe282-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 282 (DAIMLER XIII) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3283 0.09921 0.09583 -0.0308 1.0000 0.0168
-8.500 -0.3353 0.09670 0.09339 -0.0296 1.0000 0.0167
-8.250 -0.3450 0.09439 0.09114 -0.0279 1.0000 0.0167
-8.000 -0.3464 0.09083 0.08762 -0.0293 0.9978 0.0168
-7.750 -0.3367 0.08542 0.08223 -0.0351 0.9923 0.0169
-7.500 -0.3205 0.07771 0.07451 -0.0450 0.9864 0.0174
-7.250 -0.3003 0.07418 0.07098 -0.0504 0.9809 0.0183
-7.000 -0.2741 0.07136 0.06813 -0.0555 0.9771 0.0195
-6.750 -0.2512 0.06565 0.06237 -0.0636 0.9704 0.0202
-6.500 -0.2196 0.05746 0.05407 -0.0757 0.9654 0.0211
-6.250 -0.1815 0.02778 0.02291 -0.1038 0.9571 0.0251
-6.000 -0.1465 0.02676 0.02178 -0.1062 0.9539 0.0269
-5.750 -0.1103 0.02412 0.01865 -0.1093 0.9517 0.0296
-5.500 -0.0813 0.02236 0.01635 -0.1102 0.9457 0.0324
-5.250 -0.0492 0.02033 0.01399 -0.1118 0.9415 0.0347
-5.000 -0.0151 0.01961 0.01317 -0.1134 0.9382 0.0374
-4.750 0.0152 0.01864 0.01197 -0.1140 0.9326 0.0397
-4.500 0.0467 0.01778 0.01086 -0.1148 0.9268 0.0420
-4.250 0.0813 0.01704 0.00988 -0.1161 0.9226 0.0437
-4.000 0.1100 0.01616 0.00883 -0.1162 0.9148 0.0447
-3.750 0.1422 0.01515 0.00770 -0.1170 0.9090 0.0464
-3.500 0.1718 0.01455 0.00704 -0.1173 0.9007 0.0485
-3.250 0.2037 0.01404 0.00646 -0.1180 0.8932 0.0510
-3.000 0.2325 0.01361 0.00595 -0.1180 0.8829 0.0529
-2.750 0.2625 0.01321 0.00546 -0.1182 0.8729 0.0548
-2.500 0.2925 0.01287 0.00502 -0.1184 0.8618 0.0571
-2.250 0.3217 0.01252 0.00461 -0.1184 0.8486 0.0609
-2.000 0.3505 0.01221 0.00428 -0.1183 0.8337 0.0677
-1.750 0.3789 0.01192 0.00407 -0.1182 0.8152 0.0863
-1.500 0.4076 0.01178 0.00394 -0.1181 0.7934 0.1228
-1.250 0.4359 0.01177 0.00379 -0.1178 0.7687 0.1433
-1.000 0.4636 0.01180 0.00365 -0.1174 0.7429 0.1562
-0.750 0.4907 0.01186 0.00357 -0.1170 0.7176 0.1660
-0.500 0.5173 0.01195 0.00354 -0.1166 0.6923 0.1780
-0.250 0.5438 0.01206 0.00351 -0.1162 0.6673 0.1902
0.000 0.5704 0.01214 0.00349 -0.1158 0.6445 0.2015
0.250 0.5971 0.01218 0.00347 -0.1155 0.6254 0.2098
0.750 0.6505 0.01230 0.00346 -0.1149 0.5895 0.2279
1.000 0.6770 0.01237 0.00349 -0.1146 0.5736 0.2421
1.500 0.7302 0.01244 0.00361 -0.1142 0.5471 0.3055
2.000 0.7771 0.01131 0.00378 -0.1120 0.5244 1.0000
2.250 0.8038 0.01152 0.00389 -0.1118 0.5135 1.0000
2.500 0.8302 0.01174 0.00402 -0.1115 0.5024 1.0000
2.750 0.8567 0.01196 0.00416 -0.1112 0.4905 1.0000
3.000 0.8831 0.01216 0.00432 -0.1109 0.4779 1.0000
3.250 0.9093 0.01238 0.00449 -0.1106 0.4647 1.0000
3.500 0.9353 0.01260 0.00467 -0.1102 0.4511 1.0000
3.750 0.9612 0.01283 0.00486 -0.1099 0.4367 1.0000
4.000 0.9867 0.01308 0.00507 -0.1094 0.4204 1.0000
4.250 1.0113 0.01337 0.00528 -0.1089 0.3996 1.0000
4.500 1.0352 0.01371 0.00552 -0.1082 0.3744 1.0000
4.750 1.0584 0.01412 0.00579 -0.1074 0.3493 1.0000
5.000 1.0817 0.01453 0.00612 -0.1067 0.3282 1.0000
5.500 1.1273 0.01544 0.00684 -0.1052 0.2900 1.0000
5.750 1.1488 0.01599 0.00728 -0.1042 0.2672 1.0000
6.000 1.1705 0.01652 0.00770 -0.1033 0.2484 1.0000
6.250 1.1927 0.01700 0.00813 -0.1025 0.2327 1.0000
6.500 1.2146 0.01749 0.00857 -0.1016 0.2166 1.0000
6.750 1.2365 0.01798 0.00903 -0.1008 0.1995 1.0000
7.000 1.2551 0.01872 0.00955 -0.0995 0.1559 1.0000
7.250 1.2619 0.02057 0.01075 -0.0967 0.0799 1.0000
7.500 1.2791 0.02142 0.01152 -0.0951 0.0631 1.0000
7.750 1.2953 0.02232 0.01231 -0.0935 0.0444 1.0000
8.000 1.3061 0.02363 0.01346 -0.0910 0.0180 1.0000
8.250 1.3229 0.02434 0.01431 -0.0893 0.0161 1.0000
8.500 1.3383 0.02508 0.01519 -0.0873 0.0153 1.0000
8.750 1.3502 0.02593 0.01619 -0.0849 0.0143 1.0000
9.000 1.3600 0.02696 0.01738 -0.0822 0.0133 1.0000
9.250 1.3677 0.02817 0.01877 -0.0794 0.0125 1.0000
9.500 1.3740 0.02953 0.02030 -0.0765 0.0120 1.0000
9.750 1.3790 0.03103 0.02197 -0.0737 0.0116 1.0000
10.000 1.3868 0.03234 0.02343 -0.0715 0.0114 1.0000
10.250 1.3931 0.03384 0.02510 -0.0693 0.0111 1.0000
10.500 1.3979 0.03550 0.02692 -0.0671 0.0108 1.0000
10.750 1.4012 0.03736 0.02892 -0.0650 0.0105 1.0000
11.000 1.4025 0.03948 0.03120 -0.0631 0.0100 1.0000
11.250 1.4023 0.04187 0.03373 -0.0615 0.0097 1.0000
11.500 1.3999 0.04462 0.03662 -0.0601 0.0093 1.0000
11.750 1.3959 0.04771 0.03985 -0.0590 0.0091 1.0000
12.000 1.3901 0.05121 0.04350 -0.0583 0.0090 1.0000
12.250 1.3830 0.05505 0.04747 -0.0580 0.0088 1.0000
12.500 1.3748 0.05918 0.05172 -0.0580 0.0087 1.0000
12.750 1.3664 0.06349 0.05615 -0.0583 0.0086 1.0000
13.000 1.3574 0.06795 0.06069 -0.0586 0.0086 1.0000
13.250 1.3498 0.07226 0.06508 -0.0590 0.0085 1.0000
13.500 1.3434 0.07623 0.06905 -0.0589 0.0084 1.0000
13.750 1.3421 0.07982 0.07274 -0.0592 0.0083 1.0000
14.000 1.3412 0.08333 0.07635 -0.0595 0.0082 1.0000
14.250 1.3410 0.08676 0.07991 -0.0598 0.0081 1.0000
14.500 1.3414 0.09009 0.08333 -0.0600 0.0081 1.0000
14.750 1.3420 0.09339 0.08672 -0.0603 0.0080 1.0000
15.000 1.3430 0.09663 0.09005 -0.0605 0.0079 1.0000
15.250 1.3435 0.10004 0.09358 -0.0610 0.0078 1.0000
15.500 1.3438 0.10356 0.09722 -0.0616 0.0076 1.0000
15.750 1.3426 0.10747 0.10126 -0.0627 0.0075 1.0000
16.000 1.3415 0.11138 0.10530 -0.0638 0.0073 1.0000
16.250 1.3400 0.11540 0.10944 -0.0651 0.0071 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)