GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.07 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe276-il-1000000-n5.txt Download as CSV file: xf-goe276-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 276 (DAIMLER VII) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4053 0.09408 0.09248 -0.0199 1.0000 0.0053
-8.500 -0.4042 0.09141 0.08983 -0.0202 1.0000 0.0054
-8.250 -0.4065 0.08886 0.08731 -0.0199 1.0000 0.0055
-7.750 -0.3845 0.07940 0.07787 -0.0304 0.9942 0.0061
-7.000 -0.3161 0.05998 0.05833 -0.0581 0.9639 0.0075
-6.750 -0.2800 0.05528 0.05354 -0.0665 0.9437 0.0080
-6.500 -0.2444 0.04406 0.04200 -0.0797 0.9184 0.0097
-6.250 -0.2184 0.04149 0.03927 -0.0821 0.9023 0.0100
-6.000 -0.1922 0.03890 0.03653 -0.0842 0.8913 0.0104
-5.500 -0.1343 0.02807 0.02504 -0.0906 0.8710 0.0133
-5.000 -0.0765 0.01819 0.01418 -0.0934 0.8513 0.0175
-4.750 -0.0492 0.01791 0.01381 -0.0935 0.8403 0.0178
-4.500 -0.0217 0.01755 0.01335 -0.0937 0.8300 0.0181
-4.250 0.0057 0.01727 0.01298 -0.0938 0.8204 0.0185
-4.000 0.0336 0.01673 0.01233 -0.0940 0.8110 0.0190
-3.750 0.0620 0.01559 0.01100 -0.0943 0.8008 0.0198
-3.500 0.0905 0.01443 0.00959 -0.0944 0.7872 0.0209
-3.250 0.1188 0.01354 0.00850 -0.0945 0.7693 0.0218
-3.000 0.1468 0.01281 0.00754 -0.0945 0.7457 0.0222
-2.750 0.1742 0.01228 0.00675 -0.0944 0.7054 0.0224
-2.500 0.2002 0.01205 0.00611 -0.0941 0.6270 0.0226
-2.250 0.2266 0.01194 0.00562 -0.0939 0.5512 0.0228
-2.000 0.2530 0.01208 0.00541 -0.0937 0.4739 0.0230
-1.750 0.2806 0.01191 0.00505 -0.0938 0.4422 0.0232
-1.500 0.3086 0.01160 0.00461 -0.0938 0.4263 0.0232
-1.250 0.3370 0.01049 0.00336 -0.0941 0.4161 0.0243
-1.000 0.3653 0.01026 0.00308 -0.0942 0.4075 0.0250
-0.750 0.3936 0.01010 0.00289 -0.0943 0.3999 0.0256
-0.500 0.4218 0.01000 0.00275 -0.0944 0.3925 0.0261
-0.250 0.4502 0.00989 0.00261 -0.0945 0.3849 0.0266
0.000 0.4785 0.00980 0.00247 -0.0947 0.3790 0.0270
0.250 0.5070 0.00968 0.00235 -0.0948 0.3742 0.0273
0.500 0.5354 0.00960 0.00224 -0.0949 0.3689 0.0275
0.750 0.5637 0.00955 0.00216 -0.0950 0.3638 0.0278
1.000 0.5921 0.00950 0.00211 -0.0951 0.3588 0.0284
1.250 0.6204 0.00948 0.00206 -0.0952 0.3527 0.0288
1.500 0.6487 0.00946 0.00201 -0.0953 0.3473 0.0289
1.750 0.6769 0.00945 0.00199 -0.0953 0.3402 0.0291
2.000 0.7049 0.00948 0.00198 -0.0954 0.3311 0.0295
2.250 0.7328 0.00954 0.00200 -0.0954 0.3194 0.0301
2.500 0.7607 0.00960 0.00203 -0.0954 0.3087 0.0313
2.750 0.7884 0.00969 0.00209 -0.0954 0.2975 0.0326
3.000 0.8160 0.00978 0.00216 -0.0954 0.2849 0.0411
3.250 0.8384 0.00811 0.00244 -0.0949 0.2727 1.0000
3.500 0.8656 0.00831 0.00257 -0.0949 0.2572 1.0000
3.750 0.8928 0.00852 0.00270 -0.0948 0.2443 1.0000
4.000 0.9200 0.00872 0.00284 -0.0947 0.2337 1.0000
4.250 0.9474 0.00889 0.00299 -0.0947 0.2251 1.0000
4.500 0.9743 0.00910 0.00315 -0.0946 0.2137 1.0000
4.750 1.0007 0.00940 0.00336 -0.0945 0.1947 1.0000
5.000 1.0260 0.00986 0.00362 -0.0942 0.1603 1.0000
5.250 1.0507 0.01041 0.00397 -0.0938 0.1254 1.0000
5.500 1.0769 0.01070 0.00422 -0.0936 0.1149 1.0000
5.750 1.1031 0.01100 0.00447 -0.0934 0.1058 1.0000
6.000 1.1290 0.01131 0.00475 -0.0932 0.0957 1.0000
6.250 1.1521 0.01205 0.00524 -0.0926 0.0534 1.0000
6.500 1.1743 0.01293 0.00592 -0.0918 0.0184 1.0000
6.750 1.1996 0.01328 0.00628 -0.0915 0.0134 1.0000
7.000 1.2248 0.01365 0.00667 -0.0911 0.0114 1.0000
7.250 1.2495 0.01408 0.00713 -0.0907 0.0093 1.0000
7.500 1.2745 0.01442 0.00751 -0.0903 0.0087 1.0000
7.750 1.2992 0.01481 0.00793 -0.0899 0.0079 1.0000
8.000 1.3232 0.01525 0.00839 -0.0894 0.0071 1.0000
8.250 1.3463 0.01581 0.00902 -0.0887 0.0064 1.0000
8.500 1.3703 0.01622 0.00946 -0.0882 0.0060 1.0000
8.750 1.3937 0.01667 0.00996 -0.0876 0.0056 1.0000
9.000 1.4167 0.01714 0.01047 -0.0870 0.0052 1.0000
9.250 1.4390 0.01767 0.01104 -0.0862 0.0048 1.0000
9.500 1.4603 0.01830 0.01172 -0.0853 0.0045 1.0000
9.750 1.4802 0.01906 0.01257 -0.0842 0.0042 1.0000
10.000 1.5010 0.01966 0.01323 -0.0832 0.0041 1.0000
10.250 1.5208 0.02032 0.01397 -0.0821 0.0039 1.0000
10.500 1.5397 0.02102 0.01475 -0.0809 0.0038 1.0000
10.750 1.5578 0.02176 0.01557 -0.0795 0.0036 1.0000
11.000 1.5748 0.02254 0.01642 -0.0780 0.0034 1.0000
11.250 1.5912 0.02331 0.01728 -0.0765 0.0033 1.0000
11.500 1.6065 0.02408 0.01812 -0.0748 0.0032 1.0000
11.750 1.6198 0.02492 0.01902 -0.0727 0.0030 1.0000
12.000 1.6297 0.02590 0.02008 -0.0702 0.0029 1.0000
12.250 1.6315 0.02717 0.02146 -0.0664 0.0028 1.0000
12.500 1.6328 0.02853 0.02293 -0.0628 0.0027 1.0000
12.750 1.6373 0.02981 0.02432 -0.0599 0.0027 1.0000
13.000 1.6403 0.03129 0.02591 -0.0573 0.0026 1.0000
13.250 1.6418 0.03302 0.02776 -0.0548 0.0026 1.0000
13.500 1.6429 0.03494 0.02980 -0.0528 0.0025 1.0000
13.750 1.6419 0.03721 0.03220 -0.0510 0.0025 1.0000
14.000 1.6385 0.03991 0.03504 -0.0495 0.0024 1.0000
14.250 1.6344 0.04292 0.03818 -0.0485 0.0024 1.0000
14.500 1.6281 0.04642 0.04183 -0.0481 0.0024 1.0000
14.750 1.6210 0.05037 0.04591 -0.0482 0.0023 1.0000
15.000 1.6103 0.05522 0.05091 -0.0493 0.0023 1.0000
15.250 1.5987 0.06067 0.05651 -0.0510 0.0023 1.0000
15.500 1.5836 0.06709 0.06310 -0.0536 0.0023 1.0000
15.750 1.5685 0.07373 0.06988 -0.0564 0.0023 1.0000
16.000 1.5496 0.08096 0.07725 -0.0593 0.0023 1.0000
16.250 1.5300 0.08820 0.08463 -0.0621 0.0023 1.0000
16.500 1.5091 0.09559 0.09214 -0.0649 0.0022 1.0000
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Polar data table (+)
Polar graphs
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