GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 500,000 Max Cl/Cd: 81.9 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe670-il-500000-n5.txt Download as CSV file: xf-goe670-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4726 0.16345 0.16085 -0.0187 1.0000 0.0090
-15.000 -0.4682 0.15997 0.15738 -0.0199 1.0000 0.0091
-11.500 -0.8265 0.03204 0.02894 -0.0828 0.9871 0.0195
-11.250 -0.7922 0.03286 0.02986 -0.0836 0.9860 0.0202
-11.000 -0.7611 0.03307 0.03010 -0.0844 0.9841 0.0207
-10.750 -0.7366 0.03206 0.02901 -0.0852 0.9807 0.0213
-10.500 -0.7169 0.02919 0.02584 -0.0868 0.9776 0.0221
-10.250 -0.6942 0.02669 0.02303 -0.0884 0.9756 0.0230
-10.000 -0.6746 0.02502 0.02107 -0.0883 0.9709 0.0238
-9.750 -0.6493 0.02363 0.01943 -0.0890 0.9683 0.0244
-9.500 -0.6231 0.02215 0.01769 -0.0900 0.9664 0.0250
-9.250 -0.5970 0.02098 0.01640 -0.0906 0.9642 0.0258
-9.000 -0.5725 0.02051 0.01587 -0.0904 0.9600 0.0264
-8.750 -0.5437 0.02014 0.01545 -0.0910 0.9574 0.0271
-8.500 -0.5146 0.01950 0.01469 -0.0917 0.9552 0.0278
-8.250 -0.4877 0.01876 0.01381 -0.0920 0.9523 0.0285
-8.000 -0.4640 0.01795 0.01283 -0.0916 0.9480 0.0291
-7.750 -0.4368 0.01724 0.01197 -0.0918 0.9449 0.0298
-7.500 -0.4084 0.01645 0.01102 -0.0922 0.9425 0.0303
-7.250 -0.3840 0.01575 0.01015 -0.0917 0.9380 0.0307
-7.000 -0.3581 0.01512 0.00940 -0.0915 0.9338 0.0310
-6.750 -0.3300 0.01455 0.00870 -0.0917 0.9307 0.0313
-6.500 -0.3040 0.01377 0.00779 -0.0915 0.9271 0.0319
-6.250 -0.2802 0.01311 0.00705 -0.0908 0.9218 0.0328
-6.000 -0.2529 0.01264 0.00651 -0.0907 0.9178 0.0336
-5.750 -0.2246 0.01223 0.00603 -0.0909 0.9148 0.0342
-5.500 -0.2003 0.01189 0.00564 -0.0901 0.9094 0.0347
-5.250 -0.1737 0.01154 0.00524 -0.0898 0.9045 0.0354
-5.000 -0.1456 0.01121 0.00483 -0.0898 0.9009 0.0360
-4.750 -0.1204 0.01093 0.00451 -0.0893 0.8960 0.0368
-4.500 -0.0942 0.01065 0.00418 -0.0888 0.8910 0.0375
-4.250 -0.0668 0.01039 0.00386 -0.0887 0.8867 0.0383
-4.000 -0.0403 0.01016 0.00359 -0.0883 0.8822 0.0391
-3.750 -0.0143 0.00996 0.00336 -0.0878 0.8771 0.0397
-3.500 0.0122 0.00966 0.00304 -0.0875 0.8723 0.0422
-3.250 0.0391 0.00947 0.00285 -0.0872 0.8678 0.0448
-3.000 0.0650 0.00931 0.00268 -0.0867 0.8617 0.0474
-2.750 0.0923 0.00916 0.00248 -0.0864 0.8553 0.0497
-2.500 0.1177 0.00898 0.00232 -0.0858 0.8464 0.0548
-2.250 0.1446 0.00885 0.00217 -0.0855 0.8381 0.0606
-2.000 0.1703 0.00872 0.00207 -0.0849 0.8289 0.0685
-1.750 0.1966 0.00863 0.00198 -0.0844 0.8188 0.0768
-1.500 0.2229 0.00856 0.00190 -0.0839 0.8070 0.0852
-1.250 0.2486 0.00850 0.00180 -0.0833 0.7920 0.0916
-1.000 0.2737 0.00847 0.00173 -0.0826 0.7706 0.0990
-0.750 0.2980 0.00848 0.00163 -0.0816 0.7418 0.1044
-0.500 0.3207 0.00853 0.00155 -0.0804 0.7051 0.1119
-0.250 0.3433 0.00865 0.00152 -0.0791 0.6735 0.1180
0.000 0.3665 0.00870 0.00150 -0.0780 0.6512 0.1267
0.500 0.4154 0.00878 0.00151 -0.0765 0.6229 0.1471
0.750 0.4396 0.00873 0.00154 -0.0757 0.6113 0.1816
1.000 0.4636 0.00857 0.00160 -0.0749 0.6013 0.2656
1.250 0.4870 0.00842 0.00164 -0.0741 0.5913 0.3470
1.500 0.4923 0.00710 0.00176 -0.0693 0.5821 0.8361
1.750 0.5648 0.00717 0.00200 -0.0790 0.5618 0.9600
2.000 0.6041 0.00742 0.00209 -0.0815 0.5223 0.9785
2.250 0.6358 0.00787 0.00222 -0.0825 0.4544 0.9898
2.500 0.6709 0.00836 0.00241 -0.0844 0.3975 0.9979
2.750 0.6978 0.00872 0.00258 -0.0845 0.3584 1.0000
3.000 0.7167 0.00904 0.00273 -0.0827 0.3256 1.0000
3.250 0.7359 0.00934 0.00289 -0.0810 0.2976 1.0000
3.500 0.7560 0.00960 0.00305 -0.0794 0.2772 1.0000
3.750 0.7767 0.00983 0.00322 -0.0779 0.2623 1.0000
4.000 0.7976 0.01006 0.00338 -0.0765 0.2500 1.0000
4.250 0.8184 0.01030 0.00356 -0.0751 0.2402 1.0000
4.500 0.8401 0.01048 0.00374 -0.0739 0.2323 1.0000
4.750 0.8610 0.01072 0.00393 -0.0725 0.2239 1.0000
5.000 0.8830 0.01090 0.00412 -0.0713 0.2187 1.0000
5.250 0.9045 0.01111 0.00432 -0.0700 0.2128 1.0000
5.500 0.9256 0.01134 0.00453 -0.0687 0.2038 1.0000
5.750 0.9460 0.01162 0.00475 -0.0672 0.1929 1.0000
6.000 0.9675 0.01183 0.00496 -0.0660 0.1836 1.0000
6.250 0.9885 0.01207 0.00518 -0.0647 0.1754 1.0000
6.500 1.0089 0.01234 0.00542 -0.0633 0.1630 1.0000
6.750 1.0286 0.01267 0.00568 -0.0618 0.1443 1.0000
7.000 1.0446 0.01323 0.00604 -0.0597 0.1084 1.0000
7.250 1.0595 0.01388 0.00652 -0.0574 0.0829 1.0000
7.500 1.0769 0.01436 0.00696 -0.0556 0.0690 1.0000
8.000 1.1036 0.01584 0.00819 -0.0506 0.0260 1.0000
8.250 1.1201 0.01628 0.00865 -0.0486 0.0223 1.0000
8.500 1.1351 0.01680 0.00919 -0.0463 0.0192 1.0000
8.750 1.1517 0.01723 0.00967 -0.0444 0.0177 1.0000
9.000 1.1678 0.01771 0.01020 -0.0424 0.0164 1.0000
9.250 1.1831 0.01826 0.01078 -0.0404 0.0152 1.0000
9.500 1.1968 0.01893 0.01148 -0.0381 0.0138 1.0000
9.750 1.2124 0.01946 0.01208 -0.0362 0.0131 1.0000
10.000 1.2271 0.02005 0.01274 -0.0343 0.0126 1.0000
10.250 1.2412 0.02068 0.01343 -0.0323 0.0119 1.0000
10.500 1.2547 0.02136 0.01417 -0.0303 0.0113 1.0000
10.750 1.2665 0.02216 0.01503 -0.0281 0.0109 1.0000
11.000 1.2760 0.02312 0.01605 -0.0257 0.0104 1.0000
11.250 1.2843 0.02416 0.01717 -0.0233 0.0100 1.0000
11.500 1.2948 0.02507 0.01817 -0.0212 0.0097 1.0000
11.750 1.3043 0.02607 0.01926 -0.0192 0.0094 1.0000
12.000 1.3139 0.02708 0.02035 -0.0173 0.0090 1.0000
12.250 1.3210 0.02830 0.02166 -0.0152 0.0088 1.0000
12.500 1.3279 0.02957 0.02303 -0.0133 0.0086 1.0000
12.750 1.3379 0.03064 0.02416 -0.0118 0.0082 1.0000
13.000 1.3413 0.03227 0.02588 -0.0099 0.0080 1.0000
13.250 1.3461 0.03384 0.02753 -0.0084 0.0078 1.0000
13.500 1.3479 0.03574 0.02953 -0.0068 0.0076 1.0000
13.750 1.3468 0.03799 0.03188 -0.0053 0.0075 1.0000
14.000 1.3417 0.04076 0.03476 -0.0040 0.0073 1.0000
14.250 1.3448 0.04285 0.03697 -0.0033 0.0071 1.0000
14.500 1.3419 0.04570 0.03994 -0.0027 0.0071 1.0000
14.750 1.3402 0.04858 0.04295 -0.0024 0.0070 1.0000
15.000 1.3363 0.05185 0.04636 -0.0024 0.0069 1.0000
15.250 1.3334 0.05515 0.04979 -0.0027 0.0068 1.0000
15.500 1.3274 0.05900 0.05377 -0.0032 0.0068 1.0000
15.750 1.3217 0.06293 0.05783 -0.0040 0.0066 1.0000
16.000 1.3152 0.06715 0.06218 -0.0051 0.0065 1.0000
16.250 1.3071 0.07176 0.06692 -0.0065 0.0065 1.0000
16.500 1.2960 0.07698 0.07228 -0.0083 0.0064 1.0000
16.750 1.2879 0.08200 0.07743 -0.0103 0.0063 1.0000
17.000 1.2764 0.08766 0.08322 -0.0125 0.0064 1.0000
17.250 1.2676 0.09310 0.08878 -0.0150 0.0062 1.0000
17.500 1.2556 0.09912 0.09493 -0.0176 0.0062 1.0000
17.750 1.2450 0.10505 0.10097 -0.0204 0.0061 1.0000
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