GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 500,000 Max Cl/Cd: 102.51 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe282-il-500000.txt Download as CSV file: xf-goe282-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3269 0.10059 0.09843 -0.0276 1.0000 0.0224
-8.500 -0.3334 0.09864 0.09652 -0.0258 1.0000 0.0229
-8.250 -0.3423 0.09678 0.09471 -0.0238 1.0000 0.0234
-8.000 -0.3412 0.09275 0.09070 -0.0281 0.9979 0.0249
-7.750 -0.3249 0.08687 0.08482 -0.0378 0.9936 0.0254
-7.500 -0.3039 0.08092 0.07886 -0.0462 0.9892 0.0255
-7.250 -0.2790 0.07433 0.07224 -0.0559 0.9858 0.0255
-7.000 -0.2616 0.06816 0.06605 -0.0621 0.9838 0.0265
-6.750 -0.2400 0.06643 0.06431 -0.0639 0.9802 0.0274
-6.500 -0.2129 0.06288 0.06074 -0.0696 0.9765 0.0295
-6.250 -0.1636 0.02284 0.01881 -0.1086 0.9716 0.0255
-6.000 -0.1292 0.01981 0.01546 -0.1119 0.9708 0.0275
-5.750 -0.1017 0.01942 0.01505 -0.1120 0.9656 0.0291
-5.500 -0.0670 0.01799 0.01334 -0.1138 0.9631 0.0309
-5.250 -0.0313 0.01737 0.01249 -0.1153 0.9607 0.0325
-5.000 0.0021 0.01505 0.00988 -0.1172 0.9586 0.0350
-4.750 0.0339 0.01437 0.00912 -0.1180 0.9550 0.0367
-4.500 0.0628 0.01372 0.00837 -0.1181 0.9491 0.0384
-4.250 0.0950 0.01317 0.00770 -0.1188 0.9448 0.0404
-4.000 0.1239 0.01271 0.00713 -0.1187 0.9387 0.0415
-3.750 0.1528 0.01192 0.00621 -0.1187 0.9319 0.0426
-3.500 0.1810 0.01094 0.00515 -0.1187 0.9250 0.0450
-3.250 0.2089 0.01046 0.00462 -0.1184 0.9161 0.0467
-3.000 0.2363 0.01007 0.00418 -0.1180 0.9055 0.0484
-2.750 0.2640 0.00973 0.00378 -0.1176 0.8934 0.0503
-2.500 0.2915 0.00948 0.00345 -0.1172 0.8797 0.0524
-2.250 0.3190 0.00921 0.00310 -0.1168 0.8642 0.0543
-2.000 0.3466 0.00889 0.00273 -0.1165 0.8465 0.0589
-1.750 0.3741 0.00871 0.00246 -0.1161 0.8253 0.0648
-1.500 0.4011 0.00847 0.00229 -0.1157 0.7976 0.1049
-1.250 0.4276 0.00855 0.00230 -0.1152 0.7654 0.1399
-1.000 0.4542 0.00871 0.00228 -0.1146 0.7362 0.1524
-0.750 0.4811 0.00885 0.00230 -0.1143 0.7121 0.1622
-0.500 0.5082 0.00893 0.00230 -0.1140 0.6909 0.1695
-0.250 0.5355 0.00902 0.00230 -0.1138 0.6696 0.1767
0.000 0.5626 0.00909 0.00230 -0.1136 0.6483 0.1849
0.250 0.5898 0.00920 0.00231 -0.1134 0.6271 0.1939
0.500 0.6169 0.00925 0.00233 -0.1132 0.6067 0.2048
0.750 0.6440 0.00933 0.00236 -0.1130 0.5888 0.2165
1.000 0.6712 0.00941 0.00238 -0.1128 0.5730 0.2283
1.250 0.6985 0.00946 0.00243 -0.1127 0.5586 0.2464
1.500 0.7259 0.00946 0.00250 -0.1127 0.5455 0.2849
1.750 0.7464 0.00798 0.00263 -0.1112 0.5345 1.0000
2.000 0.7737 0.00815 0.00270 -0.1111 0.5237 1.0000
2.250 0.8010 0.00833 0.00279 -0.1109 0.5130 1.0000
2.500 0.8285 0.00847 0.00287 -0.1108 0.5023 1.0000
2.750 0.8558 0.00863 0.00297 -0.1107 0.4916 1.0000
3.000 0.8828 0.00880 0.00308 -0.1105 0.4780 1.0000
3.250 0.9095 0.00897 0.00319 -0.1103 0.4601 1.0000
3.500 0.9360 0.00917 0.00330 -0.1100 0.4402 1.0000
3.750 0.9623 0.00939 0.00342 -0.1097 0.4197 1.0000
4.000 0.9882 0.00964 0.00358 -0.1094 0.3954 1.0000
4.250 1.0134 0.00997 0.00376 -0.1090 0.3663 1.0000
4.500 1.0375 0.01040 0.00400 -0.1084 0.3335 1.0000
4.750 1.0615 0.01085 0.00428 -0.1078 0.3040 1.0000
5.000 1.0861 0.01124 0.00456 -0.1073 0.2822 1.0000
5.250 1.1105 0.01164 0.00485 -0.1068 0.2633 1.0000
5.500 1.1354 0.01198 0.00512 -0.1064 0.2496 1.0000
5.750 1.1602 0.01231 0.00541 -0.1059 0.2363 1.0000
6.000 1.1847 0.01267 0.00569 -0.1055 0.2219 1.0000
6.250 1.2089 0.01303 0.00599 -0.1049 0.2065 1.0000
6.500 1.2326 0.01344 0.00630 -0.1044 0.1883 1.0000
6.750 1.2530 0.01417 0.00674 -0.1033 0.1372 1.0000
7.000 1.2654 0.01567 0.00776 -0.1011 0.0723 1.0000
7.250 1.2860 0.01632 0.00829 -0.1000 0.0553 1.0000
7.500 1.3053 0.01706 0.00888 -0.0987 0.0351 1.0000
7.750 1.3223 0.01800 0.00973 -0.0970 0.0180 1.0000
8.000 1.3433 0.01851 0.01032 -0.0958 0.0162 1.0000
8.250 1.3632 0.01909 0.01100 -0.0946 0.0153 1.0000
8.500 1.3819 0.01974 0.01176 -0.0931 0.0146 1.0000
8.750 1.3990 0.02047 0.01260 -0.0913 0.0139 1.0000
9.000 1.4140 0.02130 0.01355 -0.0893 0.0134 1.0000
9.250 1.4255 0.02229 0.01466 -0.0867 0.0130 1.0000
9.500 1.4310 0.02348 0.01596 -0.0831 0.0126 1.0000
9.750 1.4353 0.02478 0.01736 -0.0796 0.0124 1.0000
10.000 1.4456 0.02574 0.01840 -0.0771 0.0122 1.0000
10.250 1.4540 0.02684 0.01960 -0.0745 0.0119 1.0000
10.500 1.4604 0.02814 0.02098 -0.0719 0.0115 1.0000
10.750 1.4646 0.02965 0.02260 -0.0692 0.0112 1.0000
11.000 1.4669 0.03138 0.02443 -0.0666 0.0110 1.0000
11.250 1.4680 0.03331 0.02646 -0.0641 0.0109 1.0000
11.500 1.4680 0.03546 0.02870 -0.0619 0.0107 1.0000
11.750 1.4672 0.03780 0.03115 -0.0600 0.0106 1.0000
12.000 1.4656 0.04038 0.03382 -0.0583 0.0105 1.0000
12.250 1.4636 0.04317 0.03670 -0.0570 0.0104 1.0000
12.500 1.4611 0.04612 0.03974 -0.0559 0.0103 1.0000
12.750 1.4587 0.04919 0.04289 -0.0550 0.0102 1.0000
13.000 1.4564 0.05232 0.04610 -0.0543 0.0101 1.0000
13.250 1.4548 0.05540 0.04928 -0.0536 0.0101 1.0000
13.500 1.4538 0.05844 0.05239 -0.0530 0.0100 1.0000
13.750 1.4539 0.06138 0.05540 -0.0524 0.0100 1.0000
14.000 1.4552 0.06418 0.05827 -0.0516 0.0100 1.0000
14.250 1.4567 0.06706 0.06125 -0.0511 0.0101 1.0000
14.500 1.4579 0.07004 0.06435 -0.0507 0.0102 1.0000
14.750 1.4589 0.07307 0.06749 -0.0504 0.0103 1.0000
15.000 1.4603 0.07601 0.07052 -0.0499 0.0102 1.0000
15.250 1.4629 0.07875 0.07333 -0.0494 0.0101 1.0000
15.500 1.4646 0.08171 0.07638 -0.0491 0.0101 1.0000
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Polar data table (+)
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