GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe670-il-1000000-n5.txt Download as CSV file: xf-goe670-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -1.0542 0.02898 0.02604 -0.0872 0.9931 0.0099
-13.500 -1.0409 0.02601 0.02283 -0.0878 0.9899 0.0105
-13.250 -1.0210 0.02403 0.02065 -0.0885 0.9877 0.0110
-13.000 -0.9984 0.02235 0.01880 -0.0892 0.9861 0.0119
-12.750 -0.9754 0.02103 0.01736 -0.0897 0.9840 0.0129
-12.500 -0.9524 0.02003 0.01626 -0.0896 0.9809 0.0138
-12.250 -0.9261 0.01913 0.01524 -0.0902 0.9786 0.0148
-12.000 -0.8974 0.01843 0.01450 -0.0910 0.9770 0.0158
-11.750 -0.8669 0.01793 0.01396 -0.0921 0.9758 0.0169
-11.500 -0.8405 0.01744 0.01342 -0.0922 0.9728 0.0179
-11.250 -0.8131 0.01699 0.01288 -0.0925 0.9699 0.0187
-11.000 -0.7844 0.01646 0.01225 -0.0931 0.9677 0.0191
-10.750 -0.7548 0.01588 0.01158 -0.0940 0.9658 0.0197
-10.500 -0.7278 0.01546 0.01112 -0.0941 0.9622 0.0204
-10.250 -0.6997 0.01514 0.01077 -0.0944 0.9586 0.0210
-10.000 -0.6703 0.01480 0.01038 -0.0950 0.9556 0.0215
-9.750 -0.6414 0.01457 0.01011 -0.0954 0.9525 0.0223
-9.500 -0.6151 0.01425 0.00973 -0.0952 0.9480 0.0228
-9.250 -0.5876 0.01389 0.00929 -0.0953 0.9442 0.0233
-9.000 -0.5599 0.01361 0.00894 -0.0954 0.9404 0.0239
-8.750 -0.5344 0.01328 0.00854 -0.0951 0.9356 0.0242
-8.500 -0.5074 0.01300 0.00818 -0.0950 0.9315 0.0244
-8.250 -0.4800 0.01283 0.00796 -0.0949 0.9274 0.0247
-8.000 -0.4571 0.01211 0.00712 -0.0942 0.9218 0.0255
-7.750 -0.4317 0.01165 0.00659 -0.0938 0.9168 0.0262
-7.500 -0.4062 0.01128 0.00616 -0.0934 0.9123 0.0266
-7.250 -0.3808 0.01095 0.00576 -0.0929 0.9076 0.0270
-7.000 -0.3547 0.01065 0.00541 -0.0926 0.9034 0.0274
-6.750 -0.3283 0.01038 0.00508 -0.0922 0.8995 0.0278
-6.500 -0.3026 0.01011 0.00477 -0.0918 0.8945 0.0283
-6.250 -0.2764 0.00988 0.00448 -0.0914 0.8893 0.0288
-5.750 -0.2238 0.00943 0.00393 -0.0907 0.8804 0.0298
-5.500 -0.1977 0.00921 0.00366 -0.0903 0.8746 0.0301
-5.250 -0.1712 0.00901 0.00340 -0.0899 0.8695 0.0305
-5.000 -0.1449 0.00882 0.00317 -0.0895 0.8647 0.0308
-4.750 -0.1185 0.00864 0.00295 -0.0892 0.8599 0.0311
-4.500 -0.0918 0.00848 0.00275 -0.0888 0.8553 0.0313
-4.250 -0.0653 0.00831 0.00254 -0.0885 0.8508 0.0316
-4.000 -0.0391 0.00809 0.00230 -0.0880 0.8455 0.0326
-3.750 -0.0128 0.00794 0.00210 -0.0876 0.8394 0.0339
-3.500 0.0135 0.00779 0.00195 -0.0872 0.8314 0.0352
-3.250 0.0395 0.00769 0.00181 -0.0867 0.8221 0.0367
-3.000 0.0658 0.00758 0.00169 -0.0862 0.8124 0.0382
-2.750 0.0920 0.00751 0.00157 -0.0857 0.8023 0.0396
-2.500 0.1178 0.00741 0.00146 -0.0852 0.7913 0.0438
-2.250 0.1431 0.00734 0.00136 -0.0845 0.7745 0.0479
-2.000 0.1673 0.00734 0.00127 -0.0836 0.7477 0.0522
-1.750 0.1891 0.00741 0.00120 -0.0822 0.7031 0.0587
-1.500 0.2109 0.00754 0.00118 -0.0808 0.6631 0.0655
-1.250 0.2346 0.00761 0.00117 -0.0799 0.6396 0.0737
-1.000 0.2594 0.00764 0.00117 -0.0792 0.6233 0.0826
-0.750 0.2847 0.00769 0.00117 -0.0785 0.6087 0.0873
-0.500 0.3105 0.00770 0.00116 -0.0780 0.5969 0.0931
-0.250 0.3367 0.00770 0.00115 -0.0776 0.5875 0.0983
0.000 0.3628 0.00772 0.00115 -0.0772 0.5790 0.1018
0.250 0.3892 0.00770 0.00115 -0.0768 0.5703 0.1101
0.500 0.4152 0.00771 0.00115 -0.0763 0.5603 0.1168
0.750 0.4409 0.00773 0.00116 -0.0758 0.5469 0.1230
1.000 0.4655 0.00780 0.00117 -0.0751 0.5201 0.1315
1.250 0.4852 0.00810 0.00125 -0.0735 0.4525 0.1519
1.500 0.5055 0.00833 0.00138 -0.0720 0.3995 0.1967
1.750 0.5275 0.00843 0.00150 -0.0709 0.3660 0.2621
2.000 0.5497 0.00854 0.00162 -0.0698 0.3328 0.3202
2.250 0.5558 0.00748 0.00176 -0.0656 0.3106 0.7934
2.500 0.5895 0.00742 0.00200 -0.0668 0.2803 0.9428
2.750 0.6498 0.00776 0.00222 -0.0743 0.2536 0.9755
3.000 0.6848 0.00799 0.00237 -0.0759 0.2384 0.9858
3.250 0.7186 0.00820 0.00250 -0.0774 0.2262 0.9914
3.500 0.7537 0.00837 0.00263 -0.0791 0.2179 0.9963
3.750 0.7894 0.00855 0.00276 -0.0809 0.2114 0.9991
4.000 0.8186 0.00868 0.00288 -0.0813 0.2069 1.0000
4.250 0.8410 0.00881 0.00300 -0.0801 0.2027 1.0000
4.500 0.8628 0.00896 0.00313 -0.0789 0.1969 1.0000
4.750 0.8847 0.00913 0.00327 -0.0776 0.1889 1.0000
5.000 0.9059 0.00934 0.00342 -0.0763 0.1789 1.0000
5.250 0.9279 0.00949 0.00356 -0.0751 0.1712 1.0000
5.500 0.9492 0.00971 0.00373 -0.0738 0.1609 1.0000
5.750 0.9700 0.00995 0.00391 -0.0724 0.1477 1.0000
6.000 0.9893 0.01029 0.00413 -0.0707 0.1267 1.0000
6.250 1.0044 0.01089 0.00452 -0.0684 0.0897 1.0000
6.500 1.0232 0.01127 0.00484 -0.0667 0.0765 1.0000
6.750 1.0440 0.01154 0.00510 -0.0653 0.0689 1.0000
7.250 1.0759 0.01270 0.00599 -0.0610 0.0252 1.0000
7.500 1.0953 0.01305 0.00634 -0.0594 0.0206 1.0000
7.750 1.1150 0.01337 0.00667 -0.0579 0.0179 1.0000
8.000 1.1342 0.01372 0.00701 -0.0563 0.0158 1.0000
8.250 1.1530 0.01410 0.00738 -0.0547 0.0138 1.0000
8.500 1.1722 0.01441 0.00773 -0.0532 0.0129 1.0000
8.750 1.1897 0.01476 0.00810 -0.0513 0.0120 1.0000
9.000 1.2062 0.01513 0.00848 -0.0492 0.0112 1.0000
9.250 1.2219 0.01557 0.00894 -0.0471 0.0103 1.0000
9.500 1.2386 0.01595 0.00935 -0.0452 0.0098 1.0000
9.750 1.2554 0.01635 0.00979 -0.0433 0.0094 1.0000
10.000 1.2719 0.01677 0.01025 -0.0414 0.0091 1.0000
10.250 1.2880 0.01723 0.01075 -0.0396 0.0087 1.0000
10.500 1.3039 0.01771 0.01125 -0.0378 0.0081 1.0000
10.750 1.3188 0.01827 0.01184 -0.0358 0.0078 1.0000
11.000 1.3323 0.01892 0.01254 -0.0337 0.0073 1.0000
11.250 1.3474 0.01947 0.01314 -0.0319 0.0071 1.0000
11.500 1.3619 0.02006 0.01378 -0.0301 0.0069 1.0000
11.750 1.3755 0.02071 0.01449 -0.0282 0.0067 1.0000
12.000 1.3890 0.02139 0.01523 -0.0264 0.0065 1.0000
12.250 1.4013 0.02214 0.01604 -0.0245 0.0063 1.0000
12.500 1.4132 0.02294 0.01689 -0.0226 0.0061 1.0000
12.750 1.4255 0.02371 0.01771 -0.0209 0.0059 1.0000
13.000 1.4350 0.02471 0.01877 -0.0190 0.0057 1.0000
13.250 1.4449 0.02570 0.01980 -0.0172 0.0054 1.0000
13.500 1.4516 0.02694 0.02113 -0.0152 0.0053 1.0000
13.750 1.4585 0.02822 0.02249 -0.0134 0.0051 1.0000
14.000 1.4657 0.02950 0.02385 -0.0117 0.0050 1.0000
14.250 1.4726 0.03086 0.02529 -0.0102 0.0050 1.0000
14.500 1.4772 0.03246 0.02698 -0.0087 0.0049 1.0000
14.750 1.4831 0.03400 0.02860 -0.0074 0.0048 1.0000
15.000 1.4858 0.03588 0.03058 -0.0061 0.0047 1.0000
15.250 1.4895 0.03777 0.03256 -0.0051 0.0046 1.0000
15.500 1.4892 0.04013 0.03502 -0.0042 0.0046 1.0000
15.750 1.4896 0.04254 0.03753 -0.0036 0.0045 1.0000
16.000 1.4916 0.04492 0.03999 -0.0032 0.0043 1.0000
16.250 1.4895 0.04787 0.04306 -0.0031 0.0043 1.0000
16.500 1.4819 0.05166 0.04697 -0.0033 0.0043 1.0000
16.750 1.4819 0.05461 0.05001 -0.0036 0.0042 1.0000
17.000 1.4703 0.05921 0.05475 -0.0045 0.0042 1.0000
17.250 1.4674 0.06274 0.05835 -0.0053 0.0041 1.0000
17.500 1.4535 0.06802 0.06377 -0.0068 0.0041 1.0000
17.750 1.4431 0.07298 0.06885 -0.0084 0.0041 1.0000
18.000 1.4254 0.07927 0.07528 -0.0107 0.0041 1.0000
18.250 1.4118 0.08514 0.08126 -0.0130 0.0040 1.0000
18.500 1.3881 0.09291 0.08919 -0.0163 0.0040 1.0000
18.750 1.3656 0.10052 0.09694 -0.0196 0.0041 1.0000
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Polar data table (+)
Polar graphs
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