GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.74 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe280-il-1000000.txt Download as CSV file: xf-goe280-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2548 0.08928 0.08785 -0.0254 1.0000 0.0091
-8.500 -0.2521 0.08620 0.08479 -0.0259 1.0000 0.0093
-8.250 -0.2523 0.08344 0.08205 -0.0257 1.0000 0.0095
-8.000 -0.2464 0.07981 0.07843 -0.0274 0.9983 0.0098
-7.750 -0.2370 0.07563 0.07426 -0.0304 0.9958 0.0103
-7.500 -0.2279 0.07133 0.06996 -0.0338 0.9914 0.0113
-7.250 -0.2202 0.06695 0.06558 -0.0387 0.9840 0.0115
-7.000 -0.2129 0.06252 0.06115 -0.0436 0.9745 0.0116
-6.750 -0.2020 0.05789 0.05649 -0.0486 0.9663 0.0116
-6.500 -0.1908 0.05334 0.05191 -0.0528 0.9573 0.0116
-6.250 -0.1779 0.04874 0.04726 -0.0566 0.9489 0.0116
-6.000 -0.1633 0.04422 0.04266 -0.0598 0.9413 0.0116
-5.750 -0.1464 0.03950 0.03788 -0.0631 0.9336 0.0117
-4.250 -0.0189 0.03450 0.03198 -0.0779 0.9114 0.0156
-4.000 0.0097 0.02804 0.02519 -0.0800 0.9036 0.0159
-3.750 0.0322 0.02750 0.02462 -0.0804 0.8949 0.0166
-3.500 0.0584 0.02636 0.02338 -0.0808 0.8851 0.0180
-3.250 0.0924 0.02498 0.02174 -0.0802 0.8747 0.0205
-3.000 0.1221 0.02241 0.01888 -0.0803 0.8614 0.0206
-2.750 0.1507 0.01789 0.01394 -0.0814 0.8460 0.0218
-2.500 0.1772 0.01729 0.01321 -0.0816 0.8210 0.0227
-2.250 0.2047 0.01662 0.01234 -0.0815 0.7901 0.0247
-2.000 0.2337 0.01734 0.01280 -0.0807 0.7586 0.0277
-1.750 -0.90161118.054081118.05176 0.2231 0.7895 0.0206
-0.250 0.4343 0.01099 0.00482 -0.0819 0.5738 0.0393
0.000 0.4621 0.01058 0.00428 -0.0820 0.5402 0.0412
0.500 0.5190 0.00989 0.00335 -0.0820 0.4993 0.0349
0.750 0.5476 0.00953 0.00292 -0.0821 0.4845 0.0341
1.000 0.5761 0.00937 0.00270 -0.0823 0.4698 0.0348
1.250 0.6045 0.00928 0.00255 -0.0825 0.4550 0.0354
1.500 0.6328 0.00925 0.00243 -0.0826 0.4361 0.0357
1.750 0.6611 0.00925 0.00234 -0.0828 0.4140 0.0358
2.000 0.6891 0.00931 0.00230 -0.0829 0.3921 0.0365
2.250 0.7173 0.00936 0.00227 -0.0831 0.3718 0.0367
2.500 0.7452 0.00946 0.00226 -0.0832 0.3501 0.0369
2.750 0.7730 0.00959 0.00229 -0.0833 0.3264 0.0375
3.000 0.8006 0.00974 0.00231 -0.0833 0.3019 0.0413
3.250 0.8272 0.01008 0.00246 -0.0833 0.2613 0.0477
3.500 0.8482 0.00859 0.00278 -0.0826 0.2283 1.0000
3.750 0.8747 0.00900 0.00298 -0.0826 0.1954 1.0000
4.000 0.9010 0.00942 0.00320 -0.0825 0.1618 1.0000
4.250 0.9273 0.00983 0.00344 -0.0825 0.1364 1.0000
4.500 0.9541 0.01013 0.00364 -0.0825 0.1222 1.0000
4.750 0.9807 0.01045 0.00386 -0.0825 0.1087 1.0000
5.000 1.0048 0.01117 0.00427 -0.0821 0.0617 1.0000
5.250 1.0296 0.01179 0.00475 -0.0818 0.0341 1.0000
5.500 1.0549 0.01230 0.00521 -0.0815 0.0147 1.0000
5.750 1.0813 0.01259 0.00554 -0.0814 0.0130 1.0000
6.000 1.1075 0.01291 0.00590 -0.0812 0.0118 1.0000
6.250 1.1333 0.01326 0.00631 -0.0810 0.0111 1.0000
6.500 1.1588 0.01366 0.00676 -0.0807 0.0104 1.0000
6.750 1.1835 0.01415 0.00730 -0.0803 0.0097 1.0000
7.000 1.2072 0.01478 0.00800 -0.0797 0.0091 1.0000
7.250 1.2277 0.01587 0.00922 -0.0786 0.0084 1.0000
7.500 1.2513 0.01642 0.00982 -0.0781 0.0080 1.0000
7.750 1.2745 0.01698 0.01043 -0.0775 0.0076 1.0000
8.000 1.2963 0.01770 0.01121 -0.0767 0.0074 1.0000
8.250 1.3171 0.01849 0.01206 -0.0757 0.0071 1.0000
8.500 1.3368 0.01934 0.01299 -0.0746 0.0068 1.0000
8.750 1.3551 0.02027 0.01398 -0.0732 0.0065 1.0000
9.000 1.3716 0.02131 0.01508 -0.0717 0.0062 1.0000
9.250 1.3859 0.02247 0.01629 -0.0699 0.0060 1.0000
9.500 1.3967 0.02386 0.01774 -0.0675 0.0058 1.0000
9.750 1.4056 0.02533 0.01925 -0.0648 0.0058 1.0000
10.000 1.4140 0.02676 0.02073 -0.0621 0.0058 1.0000
10.250 1.4191 0.02842 0.02242 -0.0590 0.0057 1.0000
10.500 1.4283 0.03074 0.02469 -0.0567 0.0055 1.0000
10.750 1.4408 0.03211 0.02610 -0.0547 0.0056 1.0000
12.750 1.5809 0.05590 0.05065 -0.0495 0.0054 1.0000
13.000 1.5739 0.05834 0.05329 -0.0459 0.0054 1.0000
13.250 1.5610 0.06053 0.05565 -0.0414 0.0053 1.0000
13.500 1.5447 0.06290 0.05818 -0.0373 0.0053 1.0000
13.750 1.5288 0.06559 0.06104 -0.0342 0.0053 1.0000
14.000 1.5116 0.06863 0.06424 -0.0318 0.0053 1.0000
14.250 1.4941 0.07201 0.06778 -0.0302 0.0053 1.0000
14.500 1.4757 0.07579 0.07173 -0.0294 0.0053 1.0000
14.750 1.4578 0.07995 0.07604 -0.0294 0.0053 1.0000
15.000 1.4387 0.08453 0.08078 -0.0302 0.0053 1.0000
15.250 1.4208 0.08943 0.08583 -0.0316 0.0053 1.0000
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Polar data table (+)
Polar graphs
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