GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Reynolds number: 200,000 Max Cl/Cd: 71.63 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe207-il-200000-n5.txt Download as CSV file: xf-goe207-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2139 0.09494 0.09141 -0.0194 0.8118 0.0273
-7.250 -0.2043 0.09273 0.08908 -0.0233 0.7859 0.0275
-7.000 -0.1903 0.09008 0.08631 -0.0278 0.7624 0.0275
-6.750 -0.1743 0.08714 0.08326 -0.0321 0.7413 0.0276
-6.500 -0.1643 0.08353 0.07956 -0.0308 0.7216 0.0277
-6.250 -0.1514 0.08042 0.07636 -0.0316 0.7029 0.0280
-6.000 -0.1359 0.07752 0.07337 -0.0336 0.6848 0.0283
-5.750 -0.1181 0.07469 0.07044 -0.0363 0.6673 0.0287
-5.500 -0.0985 0.07187 0.06751 -0.0394 0.6506 0.0292
-5.250 -0.0769 0.06908 0.06461 -0.0428 0.6344 0.0301
-5.000 -0.0513 0.06627 0.06166 -0.0471 0.6189 0.0313
-4.750 -0.0171 0.06356 0.05876 -0.0536 0.6042 0.0319
-4.500 0.0200 0.06096 0.05592 -0.0601 0.5906 0.0321
-4.250 0.0462 0.05792 0.05275 -0.0630 0.5780 0.0323
-4.000 0.0629 0.05485 0.04962 -0.0632 0.5663 0.0325
-3.750 0.0854 0.05226 0.04694 -0.0647 0.5549 0.0330
-3.500 0.1117 0.04989 0.04444 -0.0669 0.5440 0.0336
-3.250 0.1401 0.04769 0.04208 -0.0693 0.5336 0.0348
-3.000 0.1763 0.04567 0.03987 -0.0727 0.5232 0.0370
-2.750 0.2211 0.04416 0.03798 -0.0769 0.5136 0.0375
-2.500 0.2470 0.04143 0.03515 -0.0784 0.5039 0.0378
-2.250 0.2708 0.03907 0.03273 -0.0794 0.4951 0.0383
-2.000 0.2985 0.03719 0.03074 -0.0808 0.4858 0.0391
-1.750 0.3288 0.03551 0.02892 -0.0822 0.4772 0.0403
-1.500 0.3613 0.03398 0.02719 -0.0837 0.4684 0.0422
-1.250 0.4006 0.03272 0.02558 -0.0853 0.4599 0.0441
-1.000 0.4257 0.03084 0.02367 -0.0864 0.4506 0.0452
-0.750 0.4553 0.02956 0.02226 -0.0873 0.4413 0.0472
-0.500 0.4932 0.02928 0.02153 -0.0878 0.4322 0.0505
-0.250 0.5222 0.02735 0.01953 -0.0889 0.4230 0.0511
0.000 0.5503 0.02600 0.01808 -0.0897 0.4143 0.0521
0.250 0.5801 0.02499 0.01694 -0.0904 0.4052 0.0538
0.500 0.6143 0.02501 0.01652 -0.0902 0.3971 0.0580
0.750 0.6446 0.02383 0.01517 -0.0907 0.3886 0.0582
1.000 0.6751 0.02157 0.01276 -0.0914 0.3813 0.0411
1.250 0.7053 0.02081 0.01180 -0.0916 0.3734 0.0419
1.750 0.7664 0.01894 0.00933 -0.0915 0.3596 0.0376
2.000 0.7949 0.01840 0.00863 -0.0915 0.3527 0.0374
2.250 0.8234 0.01792 0.00801 -0.0915 0.3464 0.0375
2.500 0.8515 0.01752 0.00751 -0.0915 0.3399 0.0378
2.750 0.8789 0.01738 0.00731 -0.0915 0.3342 0.0392
3.000 0.9067 0.01725 0.00718 -0.0915 0.3286 0.0414
3.250 0.9344 0.01707 0.00694 -0.0914 0.3234 0.0422
3.500 0.9617 0.01699 0.00678 -0.0914 0.3190 0.0431
3.750 0.9895 0.01692 0.00673 -0.0914 0.3148 0.0442
4.000 1.0171 0.01694 0.00679 -0.0915 0.3104 0.0461
4.250 1.0441 0.01707 0.00688 -0.0914 0.3065 0.0505
4.750 1.0981 0.01739 0.00718 -0.0913 0.2988 0.0628
5.000 1.1252 0.01753 0.00734 -0.0912 0.2945 0.0878
5.250 1.1453 0.01640 0.00757 -0.0898 0.2906 1.0000
5.500 1.1712 0.01676 0.00780 -0.0896 0.2867 1.0000
5.750 1.1979 0.01702 0.00807 -0.0895 0.2832 1.0000
6.000 1.2243 0.01732 0.00837 -0.0894 0.2801 1.0000
6.250 1.2503 0.01763 0.00868 -0.0892 0.2768 1.0000
6.500 1.2757 0.01798 0.00897 -0.0890 0.2724 1.0000
6.750 1.3012 0.01829 0.00929 -0.0888 0.2676 1.0000
7.000 1.3269 0.01857 0.00962 -0.0887 0.2625 1.0000
7.250 1.3518 0.01891 0.00996 -0.0884 0.2575 1.0000
7.500 1.3763 0.01926 0.01031 -0.0881 0.2517 1.0000
7.750 1.4011 0.01956 0.01066 -0.0879 0.2449 1.0000
8.000 1.4246 0.01997 0.01105 -0.0875 0.2386 1.0000
8.250 1.4489 0.02031 0.01148 -0.0872 0.2319 1.0000
8.500 1.4715 0.02076 0.01191 -0.0867 0.2227 1.0000
8.750 1.4945 0.02119 0.01239 -0.0862 0.2120 1.0000
9.000 1.5149 0.02181 0.01296 -0.0856 0.1934 1.0000
9.250 1.5173 0.02415 0.01471 -0.0832 0.1148 1.0000
9.500 1.5239 0.02599 0.01644 -0.0811 0.0894 1.0000
9.750 1.5163 0.02874 0.01897 -0.0775 0.0367 1.0000
10.000 1.5193 0.03023 0.02056 -0.0749 0.0327 1.0000
10.250 1.5221 0.03183 0.02230 -0.0726 0.0309 1.0000
10.500 1.5225 0.03387 0.02450 -0.0708 0.0295 1.0000
10.750 1.5224 0.03624 0.02703 -0.0697 0.0284 1.0000
11.000 1.5233 0.03877 0.02972 -0.0691 0.0274 1.0000
11.250 1.5215 0.04182 0.03294 -0.0689 0.0265 1.0000
11.500 1.5170 0.04543 0.03672 -0.0692 0.0257 1.0000
11.750 1.5096 0.04963 0.04109 -0.0698 0.0251 1.0000
12.000 1.4991 0.05442 0.04606 -0.0708 0.0247 1.0000
12.250 1.4860 0.05972 0.05152 -0.0719 0.0244 1.0000
12.500 1.4704 0.06542 0.05740 -0.0732 0.0241 1.0000
12.750 1.4533 0.07140 0.06355 -0.0746 0.0240 1.0000
13.000 1.4348 0.07761 0.06992 -0.0760 0.0238 1.0000
13.250 1.4166 0.08394 0.07641 -0.0776 0.0237 1.0000
13.500 1.4019 0.08988 0.08249 -0.0791 0.0236 1.0000
13.750 1.3883 0.09578 0.08855 -0.0807 0.0234 1.0000
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Polar data table (+)
Polar graphs
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