GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.12 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe758-il-1000000-n5.txt Download as CSV file: xf-goe758-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6438 0.03531 0.03269 -0.1158 0.9388 0.0173
-12.500 -0.6161 0.03220 0.02928 -0.1244 0.8993 0.0174
-12.250 -0.6209 0.03087 0.02774 -0.1224 0.8701 0.0174
-12.000 -0.6249 0.02973 0.02645 -0.1193 0.8530 0.0175
-11.750 -0.6180 0.02872 0.02531 -0.1177 0.8406 0.0175
-11.500 -0.6069 0.02791 0.02437 -0.1162 0.8292 0.0176
-11.250 -0.5905 0.02746 0.02384 -0.1152 0.8188 0.0178
-11.000 -0.5784 0.02640 0.02264 -0.1139 0.8087 0.0179
-10.750 -0.5628 0.02565 0.02177 -0.1127 0.7975 0.0181
-10.500 -0.5471 0.02478 0.02075 -0.1116 0.7845 0.0182
-10.250 -0.5316 0.02376 0.01957 -0.1104 0.7698 0.0184
-10.000 -0.5154 0.02274 0.01835 -0.1093 0.7528 0.0187
-9.750 -0.4988 0.02176 0.01714 -0.1081 0.7298 0.0189
-9.500 -0.4818 0.02083 0.01596 -0.1068 0.6975 0.0192
-9.250 -0.4637 0.01999 0.01486 -0.1056 0.6699 0.0195
-9.000 -0.4435 0.01922 0.01389 -0.1046 0.6537 0.0198
-8.750 -0.4218 0.01855 0.01304 -0.1039 0.6425 0.0200
-8.500 -0.3994 0.01789 0.01223 -0.1032 0.6341 0.0202
-8.250 -0.3763 0.01731 0.01151 -0.1026 0.6266 0.0203
-8.000 -0.3524 0.01683 0.01091 -0.1020 0.6205 0.0204
-7.750 -0.3296 0.01598 0.00994 -0.1014 0.6155 0.0206
-7.500 -0.3062 0.01525 0.00912 -0.1008 0.6107 0.0209
-7.250 -0.2817 0.01479 0.00860 -0.1004 0.6060 0.0211
-7.000 -0.2562 0.01441 0.00818 -0.1000 0.6022 0.0213
-6.750 -0.2306 0.01406 0.00778 -0.0997 0.5983 0.0215
-6.500 -0.2048 0.01377 0.00744 -0.0993 0.5944 0.0217
-6.250 -0.1793 0.01341 0.00701 -0.0989 0.5906 0.0219
-6.000 -0.1533 0.01305 0.00661 -0.0986 0.5875 0.0221
-5.750 -0.1272 0.01270 0.00622 -0.0983 0.5843 0.0223
-5.500 -0.1012 0.01235 0.00582 -0.0980 0.5808 0.0225
-5.250 -0.0752 0.01205 0.00546 -0.0976 0.5773 0.0227
-5.000 -0.0492 0.01176 0.00512 -0.0973 0.5738 0.0229
-4.750 -0.0227 0.01147 0.00480 -0.0970 0.5710 0.0231
-4.500 0.0038 0.01119 0.00450 -0.0967 0.5677 0.0233
-4.250 0.0303 0.01094 0.00421 -0.0964 0.5642 0.0235
-4.000 0.0568 0.01072 0.00394 -0.0961 0.5605 0.0238
-3.750 0.0833 0.01052 0.00371 -0.0958 0.5566 0.0239
-3.500 0.1104 0.01032 0.00348 -0.0956 0.5528 0.0242
-3.250 0.1375 0.01017 0.00331 -0.0954 0.5484 0.0244
-3.000 0.1646 0.01006 0.00317 -0.0952 0.5440 0.0246
-2.750 0.1908 0.00981 0.00287 -0.0949 0.5403 0.0250
-2.500 0.2177 0.00958 0.00263 -0.0946 0.5369 0.0254
-2.250 0.2449 0.00943 0.00247 -0.0945 0.5330 0.0257
-2.000 0.2720 0.00931 0.00233 -0.0943 0.5286 0.0261
-1.750 0.2990 0.00922 0.00221 -0.0941 0.5248 0.0265
-1.500 0.3267 0.00912 0.00211 -0.0939 0.5212 0.0269
-1.250 0.3541 0.00904 0.00201 -0.0938 0.5168 0.0274
-1.000 0.3814 0.00898 0.00193 -0.0936 0.5120 0.0279
-0.750 0.4087 0.00893 0.00186 -0.0935 0.5079 0.0283
-0.500 0.4363 0.00887 0.00180 -0.0934 0.5033 0.0289
-0.250 0.4636 0.00885 0.00175 -0.0932 0.4976 0.0293
0.000 0.4907 0.00883 0.00171 -0.0930 0.4927 0.0302
0.250 0.5182 0.00878 0.00167 -0.0929 0.4880 0.0320
0.500 0.5454 0.00878 0.00164 -0.0928 0.4821 0.0335
1.000 0.5988 0.00862 0.00163 -0.0923 0.4704 0.1000
1.250 0.6230 0.00825 0.00164 -0.0918 0.4644 0.2570
1.500 0.6485 0.00806 0.00168 -0.0915 0.4590 0.3463
1.750 0.6737 0.00789 0.00174 -0.0911 0.4520 0.4391
2.000 0.6986 0.00778 0.00183 -0.0906 0.4452 0.5226
2.250 0.7243 0.00774 0.00191 -0.0902 0.4382 0.5783
2.500 0.7493 0.00772 0.00200 -0.0897 0.4314 0.6285
2.750 0.7740 0.00765 0.00208 -0.0891 0.4249 0.6883
3.000 0.7982 0.00766 0.00218 -0.0884 0.4168 0.7336
3.500 0.8991 0.00751 0.00250 -0.0985 0.3977 1.0000
3.750 0.9224 0.00770 0.00262 -0.0976 0.3852 1.0000
4.000 0.9465 0.00785 0.00273 -0.0969 0.3756 1.0000
4.250 0.9703 0.00802 0.00285 -0.0962 0.3676 1.0000
4.500 0.9945 0.00816 0.00297 -0.0955 0.3601 1.0000
4.750 1.0180 0.00835 0.00311 -0.0947 0.3521 1.0000
5.000 1.0415 0.00854 0.00326 -0.0939 0.3423 1.0000
5.250 1.0651 0.00872 0.00341 -0.0932 0.3355 1.0000
5.500 1.0891 0.00888 0.00356 -0.0925 0.3289 1.0000
5.750 1.1123 0.00908 0.00372 -0.0917 0.3229 1.0000
6.000 1.1364 0.00923 0.00388 -0.0911 0.3173 1.0000
6.250 1.1595 0.00944 0.00406 -0.0903 0.3106 1.0000
6.500 1.1822 0.00965 0.00425 -0.0894 0.3020 1.0000
6.750 1.2037 0.00993 0.00448 -0.0884 0.2921 1.0000
7.000 1.2263 0.01014 0.00468 -0.0876 0.2835 1.0000
7.250 1.2478 0.01040 0.00491 -0.0865 0.2755 1.0000
7.500 1.2680 0.01072 0.00517 -0.0853 0.2633 1.0000
7.750 1.2884 0.01101 0.00543 -0.0841 0.2523 1.0000
8.000 1.3081 0.01131 0.00570 -0.0828 0.2426 1.0000
8.250 1.3242 0.01176 0.00606 -0.0809 0.2250 1.0000
8.500 1.3350 0.01231 0.00649 -0.0780 0.2047 1.0000
8.750 1.3444 0.01287 0.00696 -0.0749 0.1850 1.0000
9.000 1.3504 0.01359 0.00755 -0.0714 0.1622 1.0000
9.250 1.3378 0.01517 0.00881 -0.0652 0.1088 1.0000
9.500 1.3394 0.01626 0.00979 -0.0616 0.0860 1.0000
9.750 1.3491 0.01705 0.01056 -0.0593 0.0772 1.0000
10.000 1.3613 0.01776 0.01127 -0.0575 0.0705 1.0000
10.250 1.3702 0.01870 0.01219 -0.0555 0.0614 1.0000
10.500 1.3643 0.02061 0.01393 -0.0521 0.0330 1.0000
10.750 1.3654 0.02227 0.01554 -0.0498 0.0203 1.0000
11.000 1.3741 0.02350 0.01678 -0.0484 0.0172 1.0000
11.250 1.3842 0.02468 0.01800 -0.0473 0.0158 1.0000
11.500 1.3934 0.02598 0.01934 -0.0461 0.0146 1.0000
11.750 1.4018 0.02740 0.02080 -0.0451 0.0136 1.0000
12.000 1.4110 0.02881 0.02226 -0.0442 0.0127 1.0000
12.250 1.4193 0.03034 0.02384 -0.0434 0.0123 1.0000
12.500 1.4259 0.03207 0.02562 -0.0426 0.0116 1.0000
12.750 1.4316 0.03396 0.02756 -0.0419 0.0111 1.0000
13.000 1.4365 0.03598 0.02964 -0.0413 0.0107 1.0000
13.250 1.4424 0.03794 0.03167 -0.0408 0.0104 1.0000
13.500 1.4478 0.03998 0.03377 -0.0404 0.0101 1.0000
13.750 1.4520 0.04220 0.03604 -0.0400 0.0098 1.0000
14.000 1.4552 0.04454 0.03845 -0.0397 0.0095 1.0000
14.250 1.4575 0.04697 0.04094 -0.0393 0.0093 1.0000
14.500 1.4585 0.04958 0.04362 -0.0391 0.0089 1.0000
14.750 1.4591 0.05228 0.04637 -0.0388 0.0088 1.0000
15.000 1.4577 0.05521 0.04936 -0.0386 0.0084 1.0000
15.250 1.4553 0.05831 0.05253 -0.0385 0.0082 1.0000
15.500 1.4560 0.06109 0.05539 -0.0385 0.0080 1.0000
15.750 1.4560 0.06399 0.05836 -0.0385 0.0079 1.0000
16.000 1.4546 0.06708 0.06153 -0.0385 0.0077 1.0000
16.250 1.4518 0.07040 0.06492 -0.0387 0.0076 1.0000
16.500 1.4487 0.07381 0.06841 -0.0389 0.0075 1.0000
16.750 1.4470 0.07709 0.07176 -0.0392 0.0072 1.0000
17.000 1.4439 0.08055 0.07529 -0.0395 0.0072 1.0000
17.250 1.4392 0.08428 0.07910 -0.0399 0.0071 1.0000
17.500 1.4359 0.08787 0.08275 -0.0405 0.0069 1.0000
17.750 1.4314 0.09166 0.08661 -0.0410 0.0068 1.0000
18.000 1.4268 0.09548 0.09051 -0.0417 0.0066 1.0000
18.250 1.4200 0.09967 0.09478 -0.0426 0.0066 1.0000
18.500 1.4151 0.10365 0.09883 -0.0435 0.0064 1.0000
18.750 1.4084 0.10795 0.10321 -0.0446 0.0063 1.0000
19.000 1.4021 0.11227 0.10760 -0.0458 0.0062 1.0000
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