GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 100,000 Max Cl/Cd: 56.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe282-il-100000.txt Download as CSV file: xf-goe282-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3422 0.09985 0.09541 -0.0239 1.0000 0.0902
-7.250 -0.3603 0.09941 0.09508 -0.0258 1.0000 0.0912
-7.000 -0.3697 0.09840 0.09411 -0.0331 1.0000 0.0918
-6.750 -0.3557 0.09233 0.08811 -0.0208 1.0000 0.0949
-6.500 -0.3551 0.09000 0.08583 -0.0192 1.0000 0.0979
-6.250 -0.3569 0.08776 0.08364 -0.0197 1.0000 0.1013
-6.000 -0.3524 0.08604 0.08184 -0.0346 1.0000 0.1055
-5.750 -0.3533 0.08181 0.07773 -0.0276 1.0000 0.1067
-5.500 -0.3508 0.07910 0.07508 -0.0237 1.0000 0.1089
-5.250 -0.3454 0.07662 0.07262 -0.0231 1.0000 0.1125
-5.000 -0.3219 0.07290 0.06872 -0.0351 1.0000 0.1202
-4.750 -0.3221 0.07011 0.06605 -0.0299 1.0000 0.1224
-4.500 -0.3138 0.06787 0.06383 -0.0289 1.0000 0.1277
-4.250 -0.2794 0.06344 0.05922 -0.0379 0.9980 0.1363
-4.000 -0.2399 0.05956 0.05527 -0.0429 0.9918 0.1441
-3.750 -0.1914 0.05499 0.05050 -0.0513 0.9852 0.1548
-3.500 -0.1411 0.05081 0.04607 -0.0598 0.9778 0.1676
-3.250 -0.0864 0.04698 0.04192 -0.0683 0.9717 0.1811
-3.000 -0.0090 0.03557 0.02923 -0.0811 0.9704 0.1092
-2.750 0.0422 0.03062 0.02330 -0.0862 0.9644 0.1040
-2.500 0.0923 0.02822 0.02043 -0.0909 0.9589 0.1079
-2.250 0.1360 0.02666 0.01860 -0.0941 0.9500 0.1115
-2.000 0.1872 0.02512 0.01656 -0.0983 0.9439 0.1200
-1.750 0.2280 0.02433 0.01574 -0.1007 0.9330 0.1313
-1.500 0.2742 0.02329 0.01453 -0.1039 0.9246 0.1493
-1.250 0.3206 0.02251 0.01383 -0.1072 0.9159 0.1930
-1.000 0.3612 0.02185 0.01322 -0.1096 0.9047 0.2358
-0.750 0.4129 0.02099 0.01241 -0.1139 0.8992 0.2719
-0.500 0.4496 0.02032 0.01185 -0.1153 0.8865 0.3034
-0.250 0.4871 0.01953 0.01111 -0.1164 0.8738 0.3234
0.000 0.5247 0.01864 0.01026 -0.1172 0.8602 0.3438
0.250 0.5612 0.01766 0.00941 -0.1177 0.8450 0.3747
0.500 0.5907 0.01546 0.00876 -0.1164 0.8292 1.0000
0.750 0.6241 0.01518 0.00814 -0.1162 0.8128 1.0000
1.000 0.6557 0.01502 0.00773 -0.1160 0.7968 1.0000
1.250 0.6852 0.01497 0.00748 -0.1156 0.7796 1.0000
1.500 0.7137 0.01501 0.00735 -0.1152 0.7619 1.0000
1.750 0.7421 0.01509 0.00728 -0.1147 0.7448 1.0000
2.000 0.7702 0.01523 0.00727 -0.1143 0.7279 1.0000
2.250 0.7978 0.01542 0.00732 -0.1138 0.7109 1.0000
2.500 0.8251 0.01564 0.00740 -0.1132 0.6940 1.0000
2.750 0.8520 0.01588 0.00751 -0.1127 0.6772 1.0000
3.000 0.8777 0.01615 0.00771 -0.1120 0.6596 1.0000
3.250 0.9032 0.01643 0.00794 -0.1113 0.6419 1.0000
3.500 0.9288 0.01671 0.00815 -0.1105 0.6241 1.0000
3.750 0.9544 0.01700 0.00835 -0.1098 0.6061 1.0000
4.000 0.9802 0.01730 0.00855 -0.1091 0.5878 1.0000
4.250 1.0045 0.01766 0.00887 -0.1082 0.5672 1.0000
4.500 1.0292 0.01806 0.00917 -0.1073 0.5465 1.0000
4.750 1.0543 0.01854 0.00951 -0.1065 0.5266 1.0000
5.000 1.0777 0.01906 0.01004 -0.1056 0.5048 1.0000
5.250 1.1018 0.01957 0.01046 -0.1048 0.4847 1.0000
5.500 1.1256 0.02006 0.01086 -0.1039 0.4654 1.0000
5.750 1.1479 0.02049 0.01131 -0.1028 0.4458 1.0000
6.000 1.1707 0.02089 0.01172 -0.1018 0.4282 1.0000
6.250 1.1938 0.02132 0.01215 -0.1009 0.4127 1.0000
6.500 1.2169 0.02179 0.01263 -0.1000 0.3987 1.0000
6.750 1.2385 0.02216 0.01299 -0.0989 0.3830 1.0000
7.000 1.2582 0.02243 0.01324 -0.0974 0.3647 1.0000
7.250 1.2765 0.02278 0.01357 -0.0958 0.3456 1.0000
7.500 1.2952 0.02321 0.01404 -0.0943 0.3283 1.0000
7.750 1.3143 0.02372 0.01458 -0.0929 0.3131 1.0000
8.000 1.3341 0.02428 0.01521 -0.0916 0.3006 1.0000
8.250 1.3507 0.02480 0.01578 -0.0899 0.2838 1.0000
8.500 1.3664 0.02537 0.01639 -0.0881 0.2670 1.0000
8.750 1.3822 0.02598 0.01706 -0.0863 0.2517 1.0000
9.000 1.3983 0.02663 0.01780 -0.0845 0.2386 1.0000
9.250 1.4137 0.02731 0.01860 -0.0827 0.2261 1.0000
9.500 1.4278 0.02803 0.01941 -0.0807 0.2129 1.0000
9.750 1.4392 0.02877 0.02023 -0.0784 0.1939 1.0000
10.000 1.4494 0.02956 0.02109 -0.0758 0.1760 1.0000
10.250 1.4597 0.03043 0.02204 -0.0734 0.1587 1.0000
10.500 1.4688 0.03147 0.02312 -0.0709 0.1417 1.0000
10.750 1.4752 0.03274 0.02442 -0.0683 0.1273 1.0000
11.000 1.4775 0.03438 0.02601 -0.0654 0.1122 1.0000
11.250 1.4777 0.03631 0.02790 -0.0627 0.0992 1.0000
11.500 1.4773 0.03839 0.03003 -0.0601 0.0885 1.0000
11.750 1.4752 0.04074 0.03244 -0.0578 0.0779 1.0000
12.000 1.4714 0.04336 0.03514 -0.0556 0.0681 1.0000
12.250 1.4660 0.04630 0.03816 -0.0539 0.0590 1.0000
12.500 1.4611 0.04938 0.04137 -0.0525 0.0507 1.0000
12.750 1.4538 0.05290 0.04502 -0.0516 0.0457 1.0000
13.000 1.4447 0.05687 0.04912 -0.0511 0.0425 1.0000
13.250 1.4330 0.06137 0.05375 -0.0512 0.0407 1.0000
13.500 1.4207 0.06623 0.05875 -0.0517 0.0395 1.0000
13.750 1.4083 0.07131 0.06402 -0.0526 0.0385 1.0000
14.000 1.3952 0.07672 0.06960 -0.0538 0.0378 1.0000
14.250 1.3820 0.08232 0.07540 -0.0552 0.0371 1.0000
14.500 1.3690 0.08797 0.08121 -0.0568 0.0366 1.0000
14.750 1.3571 0.09355 0.08694 -0.0584 0.0361 1.0000
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Polar data table (+)
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