GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.17 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe207-il-1000000.txt Download as CSV file: xf-goe207-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 207 (AVIATIK V8) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3352 0.12697 0.12544 0.0028 1.0000 0.0143
-10.250 -0.3291 0.12379 0.12227 0.0007 1.0000 0.0143
-10.000 -0.3220 0.12004 0.11853 -0.0003 1.0000 0.0144
-9.750 -0.3136 0.11684 0.11534 -0.0009 1.0000 0.0145
-9.500 -0.3039 0.11392 0.11243 -0.0023 0.9715 0.0146
-9.250 -0.2970 0.11155 0.10982 -0.0027 0.8841 0.0147
-9.000 -0.2900 0.10913 0.10725 -0.0033 0.8463 0.0149
-8.750 -0.2822 0.10659 0.10459 -0.0043 0.8149 0.0151
-8.500 -0.2739 0.10399 0.10187 -0.0054 0.7864 0.0154
-8.250 -0.2654 0.10133 0.09912 -0.0068 0.7611 0.0157
-7.750 -0.2476 0.09572 0.09334 -0.0101 0.7194 0.0169
-7.500 -0.2394 0.09288 0.09044 -0.0126 0.7012 0.0170
-7.250 -0.2286 0.08994 0.08744 -0.0164 0.6833 0.0171
-7.000 -0.2129 0.08667 0.08409 -0.0214 0.6648 0.0171
-6.750 -0.1949 0.08327 0.08061 -0.0268 0.6458 0.0172
-6.250 -0.1639 0.07609 0.07326 -0.0321 0.6068 0.0173
-5.750 -0.1286 0.07062 0.06761 -0.0366 0.5705 0.0176
-5.500 -0.1072 0.06788 0.06481 -0.0399 0.5565 0.0178
-5.250 -0.0840 0.06510 0.06196 -0.0434 0.5453 0.0181
-5.000 -0.0593 0.06228 0.05906 -0.0471 0.5355 0.0186
-4.750 -0.0328 0.05937 0.05608 -0.0509 0.5266 0.0192
-4.500 -0.0006 0.05633 0.05293 -0.0556 0.5182 0.0200
-4.250 0.0365 0.05321 0.04969 -0.0612 0.5101 0.0202
-4.000 0.0735 0.05007 0.04640 -0.0663 0.5025 0.0203
-3.750 0.1054 0.04709 0.04331 -0.0695 0.4957 0.0203
-3.500 0.1281 0.04369 0.03984 -0.0713 0.4886 0.0205
-3.250 0.1533 0.04155 0.03766 -0.0728 0.4819 0.0207
-3.000 0.1812 0.03959 0.03562 -0.0746 0.4743 0.0209
-2.750 0.2108 0.03769 0.03362 -0.0765 0.4673 0.0212
-2.500 0.2417 0.03577 0.03161 -0.0784 0.4596 0.0217
-2.250 0.2734 0.03388 0.02959 -0.0802 0.4521 0.0223
-2.000 0.3074 0.03198 0.02756 -0.0819 0.4441 0.0233
-1.750 0.3471 0.03012 0.02545 -0.0836 0.4360 0.0237
-1.500 0.3799 0.02823 0.02341 -0.0848 0.4271 0.0238
-1.250 0.4103 0.02558 0.02061 -0.0865 0.4182 0.0241
-1.000 0.4388 0.02441 0.01935 -0.0874 0.4079 0.0244
-0.750 0.4683 0.02334 0.01817 -0.0883 0.3986 0.0248
-0.500 0.4988 0.02227 0.01695 -0.0890 0.3886 0.0256
-0.250 0.5335 0.02111 0.01559 -0.0892 0.3798 0.0276
0.000 0.5658 0.01998 0.01425 -0.0896 0.3709 0.0277
0.250 0.5970 0.01807 0.01216 -0.0907 0.3621 0.0282
0.500 0.6261 0.01743 0.01142 -0.0913 0.3537 0.0287
0.750 0.6557 0.01678 0.01066 -0.0918 0.3452 0.0292
1.000 0.6858 0.01609 0.00984 -0.0922 0.3371 0.0302
1.250 0.7175 0.01552 0.00899 -0.0918 0.3291 0.0324
2.750 0.8947 0.01153 0.00425 -0.0933 0.2936 0.0320
3.000 0.9237 0.01121 0.00389 -0.0935 0.2896 0.0319
3.250 0.9523 0.01113 0.00378 -0.0937 0.2849 0.0323
3.500 0.9811 0.01102 0.00361 -0.0939 0.2795 0.0331
3.750 1.0099 0.01097 0.00357 -0.0941 0.2763 0.0341
4.000 1.0384 0.01099 0.00359 -0.0943 0.2722 0.0352
4.250 1.0666 0.01108 0.00366 -0.0944 0.2675 0.0371
4.500 1.0949 0.01115 0.00371 -0.0946 0.2625 0.0389
4.750 1.1232 0.01121 0.00377 -0.0947 0.2579 0.0430
5.000 1.1512 0.01132 0.00391 -0.0948 0.2523 0.0646
5.250 1.1790 0.01144 0.00407 -0.0949 0.2479 0.1051
5.500 1.2022 0.01018 0.00435 -0.0944 0.2449 1.0000
5.750 1.2300 0.01035 0.00449 -0.0945 0.2411 1.0000
6.000 1.2573 0.01057 0.00465 -0.0945 0.2361 1.0000
6.250 1.2849 0.01074 0.00480 -0.0946 0.2315 1.0000
6.500 1.3123 0.01092 0.00496 -0.0947 0.2264 1.0000
6.750 1.3390 0.01120 0.00518 -0.0947 0.2195 1.0000
7.000 1.3662 0.01138 0.00535 -0.0948 0.2127 1.0000
7.250 1.3925 0.01170 0.00559 -0.0947 0.2016 1.0000
7.500 1.4167 0.01231 0.00600 -0.0945 0.1721 1.0000
7.750 1.4300 0.01445 0.00759 -0.0931 0.0883 1.0000
8.000 1.4454 0.01616 0.00900 -0.0918 0.0277 1.0000
8.250 1.4695 0.01661 0.00948 -0.0914 0.0254 1.0000
8.500 1.4923 0.01719 0.01010 -0.0909 0.0232 1.0000
8.750 1.5153 0.01771 0.01066 -0.0904 0.0219 1.0000
9.000 1.5381 0.01821 0.01119 -0.0899 0.0209 1.0000
9.250 1.5600 0.01877 0.01177 -0.0893 0.0199 1.0000
9.500 1.5801 0.01948 0.01253 -0.0885 0.0187 1.0000
9.750 1.5989 0.02026 0.01338 -0.0875 0.0179 1.0000
10.000 1.6190 0.02084 0.01401 -0.0867 0.0173 1.0000
10.250 1.6377 0.02151 0.01472 -0.0857 0.0167 1.0000
10.500 1.6549 0.02224 0.01550 -0.0845 0.0161 1.0000
10.750 1.6698 0.02305 0.01636 -0.0830 0.0156 1.0000
11.000 1.6807 0.02405 0.01741 -0.0811 0.0151 1.0000
11.250 1.6793 0.02555 0.01903 -0.0775 0.0147 1.0000
11.500 1.6794 0.02722 0.02080 -0.0748 0.0144 1.0000
11.750 1.6870 0.02860 0.02225 -0.0734 0.0141 1.0000
12.000 1.6919 0.03041 0.02415 -0.0723 0.0138 1.0000
12.250 1.6945 0.03269 0.02653 -0.0717 0.0136 1.0000
12.500 1.6951 0.03543 0.02937 -0.0714 0.0133 1.0000
12.750 1.6936 0.03867 0.03271 -0.0716 0.0131 1.0000
13.000 1.6896 0.04238 0.03654 -0.0720 0.0129 1.0000
13.250 1.6827 0.04665 0.04092 -0.0728 0.0127 1.0000
13.500 1.6723 0.05148 0.04587 -0.0737 0.0126 1.0000
13.750 1.6586 0.05682 0.05134 -0.0747 0.0125 1.0000
14.000 1.6414 0.06264 0.05730 -0.0758 0.0124 1.0000
14.250 1.6214 0.06884 0.06362 -0.0769 0.0124 1.0000
14.500 1.6001 0.07525 0.07016 -0.0781 0.0123 1.0000
14.750 1.5800 0.08167 0.07670 -0.0795 0.0123 1.0000
15.000 1.5598 0.08829 0.08343 -0.0810 0.0123 1.0000
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Polar data table (+)
Polar graphs
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