GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.22 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795sm-il-1000000.txt Download as CSV file: xf-goe795sm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4628 0.09404 0.09240 -0.0253 1.0000 0.0127
-9.250 -0.4627 0.09046 0.08882 -0.0264 1.0000 0.0127
-8.000 -0.6236 0.03096 0.02857 -0.0484 0.9963 0.0086
-7.750 -0.6054 0.02512 0.02213 -0.0506 0.9935 0.0086
-7.500 -0.5900 0.01996 0.01630 -0.0507 0.9894 0.0087
-7.250 -0.5665 0.01678 0.01262 -0.0511 0.9866 0.0089
-7.000 -0.5391 0.01458 0.01007 -0.0517 0.9848 0.0092
-6.750 -0.5071 0.01370 0.00907 -0.0530 0.9836 0.0097
-6.500 -0.4789 0.01294 0.00821 -0.0532 0.9808 0.0102
-6.250 -0.4509 0.01222 0.00739 -0.0534 0.9773 0.0108
-6.000 -0.4196 0.01162 0.00669 -0.0542 0.9749 0.0116
-5.750 -0.3872 0.01100 0.00597 -0.0552 0.9731 0.0122
-5.500 -0.3531 0.01069 0.00562 -0.0567 0.9717 0.0127
-5.250 -0.3214 0.00959 0.00436 -0.0576 0.9704 0.0146
-5.000 -0.2962 0.00926 0.00401 -0.0569 0.9644 0.0163
-4.750 -0.2637 0.00898 0.00372 -0.0579 0.9615 0.0182
-4.500 -0.2302 0.00848 0.00319 -0.0592 0.9591 0.0229
-4.250 -0.1934 0.00832 0.00303 -0.0612 0.9572 0.0259
-4.000 -0.1663 0.00795 0.00265 -0.0610 0.9497 0.0314
-3.750 -0.1312 0.00775 0.00244 -0.0625 0.9452 0.0353
-3.500 -0.0996 0.00749 0.00217 -0.0634 0.9380 0.0415
-3.250 -0.0655 0.00734 0.00201 -0.0647 0.9307 0.0472
-3.000 -0.0354 0.00711 0.00177 -0.0651 0.9203 0.0546
-2.750 -0.0050 0.00699 0.00161 -0.0656 0.9089 0.0605
-2.500 0.0234 0.00682 0.00143 -0.0657 0.8956 0.0718
-2.250 0.0504 0.00668 0.00128 -0.0654 0.8808 0.0871
-2.000 0.0755 0.00644 0.00115 -0.0648 0.8664 0.1318
-1.750 0.1000 0.00621 0.00108 -0.0641 0.8526 0.1993
-1.500 0.1252 0.00609 0.00102 -0.0635 0.8395 0.2372
-1.250 0.1501 0.00597 0.00097 -0.0628 0.8267 0.2770
-1.000 0.1742 0.00579 0.00092 -0.0620 0.8141 0.3371
-0.750 0.1969 0.00551 0.00089 -0.0610 0.8020 0.4365
-0.500 0.2176 0.00513 0.00087 -0.0595 0.7899 0.5726
-0.250 0.2331 0.00462 0.00088 -0.0567 0.7776 0.7487
0.000 0.3150 0.00422 0.00102 -0.0688 0.7677 0.9496
0.250 0.3572 0.00442 0.00116 -0.0718 0.7555 0.9761
0.500 0.3992 0.00459 0.00125 -0.0749 0.7422 0.9867
0.750 0.4376 0.00470 0.00130 -0.0772 0.7276 0.9918
1.000 0.4739 0.00479 0.00132 -0.0791 0.7115 0.9952
1.250 0.5114 0.00487 0.00130 -0.0813 0.6902 0.9982
1.500 0.5448 0.00497 0.00130 -0.0825 0.6637 1.0000
1.750 0.5671 0.00507 0.00131 -0.0813 0.6409 1.0000
2.000 0.5893 0.00518 0.00134 -0.0800 0.6173 1.0000
2.250 0.6113 0.00532 0.00138 -0.0788 0.5898 1.0000
2.500 0.6337 0.00546 0.00143 -0.0776 0.5651 1.0000
2.750 0.6555 0.00564 0.00150 -0.0763 0.5325 1.0000
3.000 0.6775 0.00583 0.00158 -0.0750 0.5010 1.0000
3.250 0.6987 0.00607 0.00168 -0.0736 0.4634 1.0000
3.500 0.7200 0.00634 0.00180 -0.0723 0.4254 1.0000
3.750 0.7411 0.00663 0.00195 -0.0709 0.3861 1.0000
4.000 0.7619 0.00695 0.00211 -0.0695 0.3467 1.0000
4.250 0.7823 0.00733 0.00230 -0.0680 0.3022 1.0000
4.500 0.8017 0.00777 0.00251 -0.0664 0.2518 1.0000
4.750 0.8197 0.00833 0.00279 -0.0646 0.1903 1.0000
5.000 0.8390 0.00881 0.00308 -0.0630 0.1478 1.0000
5.250 0.8592 0.00923 0.00336 -0.0615 0.1178 1.0000
5.500 0.8801 0.00960 0.00363 -0.0602 0.0948 1.0000
5.750 0.9011 0.00996 0.00390 -0.0589 0.0760 1.0000
6.000 0.9216 0.01037 0.00421 -0.0575 0.0564 1.0000
6.250 0.9416 0.01082 0.00458 -0.0560 0.0374 1.0000
6.500 0.9607 0.01136 0.00503 -0.0544 0.0221 1.0000
6.750 0.9795 0.01194 0.00560 -0.0525 0.0155 1.0000
7.000 1.0011 0.01227 0.00597 -0.0513 0.0145 1.0000
7.250 1.0218 0.01266 0.00640 -0.0500 0.0132 1.0000
7.500 1.0413 0.01317 0.00694 -0.0484 0.0118 1.0000
7.750 1.0568 0.01402 0.00792 -0.0460 0.0105 1.0000
8.000 1.0774 0.01440 0.00833 -0.0447 0.0100 1.0000
8.250 1.0965 0.01491 0.00891 -0.0431 0.0096 1.0000
8.500 1.1159 0.01538 0.00943 -0.0416 0.0090 1.0000
8.750 1.1342 0.01594 0.01004 -0.0400 0.0084 1.0000
9.000 1.1530 0.01644 0.01058 -0.0384 0.0079 1.0000
9.250 1.1679 0.01727 0.01148 -0.0362 0.0075 1.0000
9.500 1.1787 0.01844 0.01278 -0.0334 0.0071 1.0000
9.750 1.1842 0.02013 0.01465 -0.0297 0.0067 1.0000
10.000 1.2031 0.02052 0.01509 -0.0283 0.0064 1.0000
10.250 1.2163 0.02145 0.01613 -0.0260 0.0063 1.0000
10.500 1.2301 0.02213 0.01688 -0.0238 0.0060 1.0000
10.750 1.2437 0.02264 0.01745 -0.0216 0.0056 1.0000
11.000 1.2520 0.02364 0.01855 -0.0186 0.0054 1.0000
11.250 1.2605 0.02465 0.01966 -0.0158 0.0053 1.0000
11.500 1.2710 0.02544 0.02051 -0.0135 0.0050 1.0000
11.750 1.2773 0.02666 0.02187 -0.0108 0.0049 1.0000
12.000 1.2824 0.02798 0.02329 -0.0082 0.0047 1.0000
12.250 1.2856 0.02949 0.02491 -0.0057 0.0046 1.0000
12.500 1.2828 0.03168 0.02726 -0.0028 0.0045 1.0000
12.750 1.2764 0.03429 0.03007 -0.0002 0.0044 1.0000
13.000 1.2678 0.03728 0.03326 0.0020 0.0044 1.0000
13.250 1.2623 0.04009 0.03624 0.0035 0.0044 1.0000
13.500 1.2327 0.04593 0.04240 0.0047 0.0043 1.0000
13.750 1.2245 0.04951 0.04613 0.0047 0.0043 1.0000
14.000 1.2002 0.05563 0.05250 0.0037 0.0042 1.0000
14.250 1.2013 0.05851 0.05546 0.0027 0.0043 1.0000
14.500 1.1721 0.06635 0.06354 -0.0006 0.0042 1.0000
14.750 1.1672 0.07079 0.06808 -0.0028 0.0043 1.0000
15.000 1.1409 0.07948 0.07696 -0.0075 0.0043 1.0000
15.250 1.1323 0.08532 0.08290 -0.0109 0.0043 1.0000
15.500 1.1153 0.09319 0.09089 -0.0154 0.0043 1.0000
15.750 1.1002 0.10098 0.09880 -0.0199 0.0043 1.0000
16.000 1.0767 0.11089 0.10883 -0.0254 0.0043 1.0000
16.250 1.0682 0.11761 0.11562 -0.0289 0.0044 1.0000
16.500 1.0514 0.12652 0.12462 -0.0335 0.0044 1.0000
16.750 1.0316 0.13638 0.13458 -0.0385 0.0045 1.0000
18.500 0.8989 0.22505 0.22333 -0.0769 0.0067 1.0000
18.750 0.7093 0.20761 0.20618 -0.0688 0.0067 1.0000
19.000 0.7124 0.21185 0.21043 -0.0708 0.0067 1.0000
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