GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 500,000 Max Cl/Cd: 86.21 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795sm-il-500000-n5.txt Download as CSV file: xf-goe795sm-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4816 0.10107 0.09868 -0.0229 1.0000 0.0075
-10.000 -0.4852 0.09630 0.09393 -0.0245 1.0000 0.0076
-8.500 -0.6750 0.03224 0.02924 -0.0481 0.9978 0.0073
-8.250 -0.6610 0.02551 0.02172 -0.0501 0.9939 0.0075
-8.000 -0.6386 0.02302 0.01884 -0.0505 0.9906 0.0079
-7.750 -0.6139 0.02085 0.01629 -0.0510 0.9873 0.0082
-7.500 -0.5867 0.01909 0.01419 -0.0517 0.9847 0.0084
-7.250 -0.5584 0.01767 0.01247 -0.0524 0.9824 0.0086
-7.000 -0.5363 0.01600 0.01052 -0.0517 0.9776 0.0090
-6.750 -0.5082 0.01502 0.00939 -0.0521 0.9743 0.0094
-6.500 -0.4776 0.01436 0.00863 -0.0530 0.9719 0.0101
-6.250 -0.4477 0.01372 0.00788 -0.0536 0.9692 0.0107
-6.000 -0.4220 0.01313 0.00719 -0.0532 0.9638 0.0114
-5.750 -0.3923 0.01253 0.00646 -0.0537 0.9603 0.0121
-5.500 -0.3611 0.01193 0.00576 -0.0545 0.9577 0.0132
-5.250 -0.3344 0.01145 0.00524 -0.0544 0.9521 0.0149
-5.000 -0.3040 0.01110 0.00486 -0.0550 0.9474 0.0170
-4.750 -0.2704 0.01068 0.00436 -0.0562 0.9443 0.0193
-4.500 -0.2401 0.01031 0.00398 -0.0568 0.9385 0.0226
-4.250 -0.2073 0.01003 0.00365 -0.0579 0.9332 0.0257
-4.000 -0.1730 0.00970 0.00333 -0.0594 0.9285 0.0309
-3.750 -0.1416 0.00948 0.00307 -0.0601 0.9207 0.0353
-3.500 -0.1079 0.00920 0.00276 -0.0614 0.9139 0.0410
-3.250 -0.0761 0.00899 0.00253 -0.0623 0.9047 0.0462
-3.000 -0.0452 0.00878 0.00230 -0.0629 0.8948 0.0529
-2.750 -0.0147 0.00862 0.00209 -0.0634 0.8844 0.0596
-2.500 0.0145 0.00845 0.00189 -0.0637 0.8732 0.0682
-2.250 0.0420 0.00830 0.00174 -0.0636 0.8610 0.0815
-2.000 0.0688 0.00814 0.00159 -0.0633 0.8482 0.1022
-1.750 0.0942 0.00789 0.00148 -0.0628 0.8346 0.1536
-1.500 0.1196 0.00773 0.00140 -0.0622 0.8199 0.2015
-1.250 0.1451 0.00764 0.00133 -0.0617 0.8052 0.2317
-1.000 0.1704 0.00754 0.00127 -0.0611 0.7915 0.2623
-0.750 0.1950 0.00739 0.00121 -0.0604 0.7783 0.3118
-0.500 0.2185 0.00715 0.00118 -0.0595 0.7653 0.3906
-0.250 0.2396 0.00677 0.00116 -0.0581 0.7527 0.5230
0.000 0.2540 0.00613 0.00118 -0.0552 0.7404 0.7285
0.500 0.3831 0.00590 0.00140 -0.0712 0.7135 0.9697
0.750 0.4146 0.00601 0.00144 -0.0719 0.6988 0.9801
1.000 0.4470 0.00611 0.00147 -0.0729 0.6825 0.9872
1.250 0.4852 0.00625 0.00152 -0.0752 0.6649 0.9950
1.500 0.5250 0.00636 0.00155 -0.0779 0.6444 1.0000
1.750 0.5473 0.00647 0.00158 -0.0767 0.6224 1.0000
2.000 0.5685 0.00665 0.00162 -0.0752 0.5903 1.0000
2.250 0.5891 0.00687 0.00167 -0.0736 0.5520 1.0000
2.500 0.6104 0.00708 0.00175 -0.0722 0.5190 1.0000
2.750 0.6314 0.00733 0.00187 -0.0708 0.4822 1.0000
3.000 0.6525 0.00760 0.00199 -0.0694 0.4458 1.0000
3.250 0.6739 0.00787 0.00213 -0.0681 0.4132 1.0000
3.500 0.6950 0.00817 0.00230 -0.0667 0.3791 1.0000
3.750 0.7165 0.00846 0.00247 -0.0655 0.3488 1.0000
4.000 0.7377 0.00878 0.00268 -0.0642 0.3154 1.0000
4.250 0.7586 0.00913 0.00290 -0.0628 0.2808 1.0000
4.500 0.7788 0.00955 0.00314 -0.0614 0.2398 1.0000
4.750 0.7980 0.01006 0.00343 -0.0598 0.1904 1.0000
5.000 0.8166 0.01063 0.00379 -0.0581 0.1442 1.0000
5.250 0.8364 0.01111 0.00412 -0.0567 0.1126 1.0000
5.500 0.8567 0.01155 0.00444 -0.0553 0.0887 1.0000
5.750 0.8773 0.01196 0.00478 -0.0540 0.0696 1.0000
6.000 0.8975 0.01242 0.00514 -0.0526 0.0514 1.0000
6.250 0.9178 0.01286 0.00554 -0.0512 0.0374 1.0000
6.500 0.9380 0.01331 0.00596 -0.0498 0.0272 1.0000
6.750 0.9582 0.01377 0.00641 -0.0484 0.0208 1.0000
7.000 0.9781 0.01424 0.00689 -0.0469 0.0170 1.0000
7.250 0.9981 0.01472 0.00742 -0.0455 0.0147 1.0000
7.500 1.0181 0.01518 0.00793 -0.0441 0.0130 1.0000
7.750 1.0371 0.01572 0.00852 -0.0425 0.0114 1.0000
8.000 1.0541 0.01644 0.00931 -0.0406 0.0103 1.0000
8.250 1.0728 0.01699 0.00994 -0.0390 0.0099 1.0000
8.500 1.0908 0.01757 0.01061 -0.0373 0.0094 1.0000
8.750 1.1081 0.01820 0.01132 -0.0355 0.0089 1.0000
9.000 1.1263 0.01873 0.01190 -0.0340 0.0081 1.0000
9.250 1.1425 0.01942 0.01266 -0.0321 0.0077 1.0000
9.500 1.1569 0.02023 0.01356 -0.0300 0.0072 1.0000
9.750 1.1669 0.02136 0.01479 -0.0272 0.0067 1.0000
10.000 1.1814 0.02209 0.01563 -0.0251 0.0065 1.0000
10.250 1.1913 0.02302 0.01667 -0.0223 0.0063 1.0000
10.500 1.2009 0.02391 0.01768 -0.0195 0.0061 1.0000
10.750 1.2098 0.02490 0.01879 -0.0167 0.0059 1.0000
11.000 1.2179 0.02600 0.02001 -0.0140 0.0056 1.0000
11.250 1.2262 0.02708 0.02121 -0.0115 0.0054 1.0000
11.500 1.2344 0.02819 0.02244 -0.0091 0.0052 1.0000
11.750 1.2404 0.02951 0.02388 -0.0067 0.0050 1.0000
12.000 1.2459 0.03089 0.02540 -0.0045 0.0049 1.0000
12.250 1.2505 0.03237 0.02701 -0.0025 0.0048 1.0000
12.500 1.2535 0.03405 0.02882 -0.0006 0.0046 1.0000
12.750 1.2528 0.03619 0.03111 0.0013 0.0045 1.0000
13.000 1.2506 0.03857 0.03364 0.0028 0.0044 1.0000
13.250 1.2451 0.04148 0.03673 0.0041 0.0044 1.0000
13.500 1.2317 0.04547 0.04092 0.0048 0.0042 1.0000
13.750 1.2253 0.04888 0.04452 0.0049 0.0042 1.0000
14.000 1.2181 0.05266 0.04850 0.0045 0.0041 1.0000
14.250 1.2068 0.05721 0.05322 0.0034 0.0041 1.0000
14.500 1.2038 0.06089 0.05704 0.0020 0.0041 1.0000
14.750 1.1804 0.06800 0.06438 -0.0009 0.0041 1.0000
15.000 1.1670 0.07405 0.07061 -0.0039 0.0040 1.0000
15.250 1.1530 0.08056 0.07727 -0.0074 0.0041 1.0000
15.500 1.1320 0.08881 0.08569 -0.0119 0.0041 1.0000
15.750 1.1166 0.09633 0.09333 -0.0161 0.0041 1.0000
16.000 1.0948 0.10553 0.10268 -0.0211 0.0040 1.0000
16.250 1.0567 0.11862 0.11592 -0.0280 0.0042 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 795 smoothed (goe795sm-il)