GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.92 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe207-il-1000000-n5.txt Download as CSV file: xf-goe207-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2511 0.09451 0.09140 -0.0111 0.5457 0.0135
-7.500 -0.2425 0.09182 0.08867 -0.0127 0.5358 0.0140
-7.250 -0.2342 0.08751 0.08434 -0.0172 0.5299 0.0149
-7.000 -0.2201 0.08511 0.08190 -0.0194 0.5212 0.0150
-6.750 -0.2045 0.08264 0.07940 -0.0220 0.5139 0.0152
-6.500 -0.1875 0.08001 0.07675 -0.0251 0.5061 0.0155
-6.250 -0.1683 0.07744 0.07413 -0.0284 0.4979 0.0169
-6.000 -0.1476 0.07400 0.07064 -0.0329 0.4903 0.0171
-5.750 -0.1255 0.07059 0.06717 -0.0374 0.4824 0.0171
-5.500 -0.0996 0.06683 0.06335 -0.0429 0.4757 0.0173
-5.250 -0.0733 0.06330 0.05974 -0.0478 0.4684 0.0173
-5.000 -0.0442 0.05973 0.05608 -0.0529 0.4625 0.0173
-4.750 -0.0138 0.05623 0.05249 -0.0578 0.4554 0.0174
-4.500 0.0079 0.05362 0.04983 -0.0595 0.4476 0.0175
-4.250 0.0328 0.05144 0.04759 -0.0617 0.4400 0.0177
-4.000 0.0597 0.04934 0.04541 -0.0641 0.4320 0.0179
-3.750 0.0878 0.04732 0.04332 -0.0666 0.4250 0.0183
-3.500 0.1214 0.04493 0.04081 -0.0698 0.4167 0.0200
-3.250 0.1560 0.04208 0.03783 -0.0731 0.4094 0.0201
-3.000 0.1901 0.03941 0.03501 -0.0761 0.4008 0.0202
-2.750 0.2230 0.03698 0.03244 -0.0784 0.3929 0.0202
-2.500 0.2547 0.03476 0.03007 -0.0804 0.3838 0.0202
-2.250 0.2873 0.03257 0.02774 -0.0822 0.3759 0.0202
-1.750 0.3459 0.02914 0.02407 -0.0849 0.3576 0.0199
-1.500 0.3772 0.02745 0.02223 -0.0862 0.3488 0.0197
-1.250 0.4107 0.02549 0.02009 -0.0875 0.3407 0.0199
-0.500 0.5099 0.02014 0.01416 -0.0903 0.3210 0.0205
-0.250 0.5385 0.01972 0.01367 -0.0909 0.3155 0.0208
0.000 0.5742 0.01697 0.01058 -0.0917 0.3105 0.0205
0.250 0.6049 0.01589 0.00931 -0.0922 0.3048 0.0207
0.500 0.6348 0.01517 0.00847 -0.0925 0.2998 0.0209
0.750 0.6648 0.01441 0.00756 -0.0928 0.2934 0.0213
1.000 0.6955 0.01308 0.00598 -0.0931 0.2863 0.0219
1.250 0.7253 0.01217 0.00487 -0.0934 0.2817 0.0223
1.500 0.7544 0.01178 0.00436 -0.0935 0.2767 0.0227
1.750 0.7831 0.01159 0.00407 -0.0937 0.2718 0.0232
2.000 0.8120 0.01141 0.00384 -0.0938 0.2683 0.0234
2.250 0.8408 0.01131 0.00370 -0.0940 0.2649 0.0236
2.500 0.8696 0.01113 0.00348 -0.0942 0.2610 0.0241
2.750 0.8982 0.01113 0.00345 -0.0944 0.2561 0.0246
3.000 0.9268 0.01113 0.00345 -0.0946 0.2521 0.0251
3.250 0.9554 0.01114 0.00345 -0.0947 0.2489 0.0256
3.500 0.9839 0.01117 0.00346 -0.0949 0.2457 0.0262
3.750 1.0123 0.01122 0.00350 -0.0950 0.2424 0.0268
4.000 1.0405 0.01132 0.00359 -0.0951 0.2389 0.0275
4.250 1.0689 0.01134 0.00363 -0.0953 0.2363 0.0287
4.500 1.0971 0.01143 0.00371 -0.0954 0.2320 0.0297
4.750 1.1250 0.01155 0.00381 -0.0955 0.2271 0.0309
5.000 1.1528 0.01171 0.00395 -0.0956 0.2222 0.0322
5.250 1.1807 0.01181 0.00406 -0.0957 0.2187 0.0358
5.500 1.2084 0.01194 0.00424 -0.0958 0.2137 0.0664
5.750 1.2358 0.01213 0.00441 -0.0959 0.2087 0.0791
6.000 1.2632 0.01228 0.00459 -0.0960 0.2042 0.0943
6.500 1.3123 0.01152 0.00520 -0.0954 0.1849 1.0000
6.750 1.3319 0.01291 0.00614 -0.0947 0.1176 1.0000
7.000 1.3561 0.01352 0.00666 -0.0944 0.1014 1.0000
7.250 1.3806 0.01405 0.00712 -0.0942 0.0891 1.0000
7.500 1.3983 0.01552 0.00831 -0.0931 0.0287 1.0000
7.750 1.4230 0.01594 0.00872 -0.0929 0.0253 1.0000
8.000 1.4477 0.01632 0.00912 -0.0926 0.0230 1.0000
8.250 1.4720 0.01673 0.00953 -0.0923 0.0211 1.0000
8.500 1.4956 0.01719 0.01000 -0.0919 0.0194 1.0000
8.750 1.5194 0.01760 0.01043 -0.0915 0.0185 1.0000
9.000 1.5427 0.01804 0.01089 -0.0911 0.0174 1.0000
9.250 1.5652 0.01853 0.01138 -0.0906 0.0163 1.0000
9.500 1.5869 0.01906 0.01193 -0.0900 0.0153 1.0000
9.750 1.6087 0.01955 0.01245 -0.0894 0.0147 1.0000
10.000 1.6297 0.02008 0.01301 -0.0887 0.0140 1.0000
10.250 1.6497 0.02065 0.01361 -0.0879 0.0134 1.0000
10.500 1.6685 0.02129 0.01427 -0.0869 0.0128 1.0000
10.750 1.6852 0.02204 0.01506 -0.0857 0.0121 1.0000
11.000 1.7018 0.02269 0.01576 -0.0844 0.0118 1.0000
11.250 1.7165 0.02341 0.01653 -0.0829 0.0114 1.0000
11.500 1.7277 0.02421 0.01737 -0.0809 0.0111 1.0000
11.750 1.7352 0.02517 0.01840 -0.0785 0.0107 1.0000
12.000 1.7422 0.02634 0.01963 -0.0765 0.0104 1.0000
12.250 1.7485 0.02776 0.02111 -0.0749 0.0101 1.0000
12.500 1.7534 0.02947 0.02290 -0.0737 0.0098 1.0000
12.750 1.7563 0.03160 0.02511 -0.0728 0.0096 1.0000
13.000 1.7566 0.03423 0.02784 -0.0723 0.0093 1.0000
13.250 1.7584 0.03689 0.03060 -0.0721 0.0092 1.0000
13.500 1.7577 0.04000 0.03381 -0.0723 0.0091 1.0000
13.750 1.7544 0.04356 0.03748 -0.0726 0.0090 1.0000
14.000 1.7481 0.04761 0.04165 -0.0732 0.0089 1.0000
14.250 1.7387 0.05218 0.04634 -0.0739 0.0088 1.0000
14.500 1.7261 0.05724 0.05153 -0.0748 0.0087 1.0000
14.750 1.7102 0.06273 0.05715 -0.0757 0.0086 1.0000
15.000 1.6918 0.06858 0.06313 -0.0767 0.0086 1.0000
15.250 1.6711 0.07482 0.06950 -0.0778 0.0085 1.0000
15.500 1.6513 0.08111 0.07592 -0.0791 0.0085 1.0000
15.750 1.6304 0.08773 0.08266 -0.0805 0.0084 1.0000
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Polar data table (+)
Polar graphs
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