S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7055-il-1000000.txt Download as CSV file: xf-s7055-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
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 -0.3420 0.09200 0.09045 -0.0390 1.0000 0.0114
-9.250 -0.3421 0.08814 0.08662 -0.0403 1.0000 0.0114
-9.000 -0.3584 0.08194 0.08047 -0.0425 1.0000 0.0119
-8.750 -0.3480 0.07778 0.07631 -0.0468 0.9833 0.0120
-8.500 -0.3282 0.07213 0.07065 -0.0555 0.9723 0.0122
-8.250 -0.4711 0.02519 0.02219 -0.0800 0.8985 0.0081
-8.000 -0.4762 0.01884 0.01496 -0.0773 0.8878 0.0084
-7.750 -0.4576 0.01716 0.01303 -0.0763 0.8809 0.0088
-7.500 -0.4348 0.01633 0.01205 -0.0757 0.8742 0.0091
-7.250 -0.4111 0.01560 0.01118 -0.0751 0.8681 0.0094
-7.000 -0.3875 0.01471 0.01013 -0.0745 0.8615 0.0098
-6.750 -0.3632 0.01402 0.00927 -0.0739 0.8556 0.0102
-6.500 -0.3387 0.01319 0.00829 -0.0734 0.8491 0.0106
-6.250 -0.3133 0.01268 0.00765 -0.0729 0.8429 0.0111
-6.000 -0.2864 0.01246 0.00735 -0.0727 0.8365 0.0114
-5.750 -0.2645 0.01107 0.00575 -0.0717 0.8296 0.0126
-5.500 -0.2385 0.01065 0.00527 -0.0713 0.8231 0.0132
-5.250 -0.2123 0.01029 0.00483 -0.0710 0.8163 0.0140
-5.000 -0.1858 0.00996 0.00442 -0.0706 0.8100 0.0148
-4.750 -0.1592 0.00964 0.00404 -0.0703 0.8031 0.0155
-4.500 -0.1336 0.00914 0.00343 -0.0698 0.7966 0.0170
-4.250 -0.1065 0.00892 0.00321 -0.0696 0.7893 0.0191
-4.000 -0.0792 0.00879 0.00302 -0.0694 0.7825 0.0211
-3.750 -0.0526 0.00845 0.00268 -0.0691 0.7747 0.0256
-3.500 -0.0248 0.00842 0.00261 -0.0690 0.7674 0.0290
-3.250 0.0019 0.00815 0.00232 -0.0688 0.7591 0.0346
-3.000 0.0294 0.00807 0.00220 -0.0687 0.7512 0.0378
-2.750 0.0567 0.00796 0.00203 -0.0685 0.7427 0.0407
-2.500 0.0838 0.00777 0.00183 -0.0683 0.7342 0.0458
-2.250 0.1111 0.00769 0.00169 -0.0681 0.7259 0.0496
-2.000 0.1384 0.00755 0.00155 -0.0680 0.7172 0.0579
-1.750 0.1655 0.00741 0.00143 -0.0678 0.7088 0.0727
-1.500 0.1921 0.00720 0.00132 -0.0675 0.7000 0.1139
-1.250 0.2183 0.00691 0.00123 -0.0673 0.6913 0.1866
-1.000 0.2437 0.00659 0.00117 -0.0670 0.6828 0.2877
-0.750 0.2692 0.00628 0.00114 -0.0667 0.6734 0.3899
-0.500 0.2938 0.00592 0.00112 -0.0662 0.6644 0.5168
-0.250 0.3169 0.00555 0.00111 -0.0653 0.6551 0.6544
0.000 0.3384 0.00518 0.00114 -0.0638 0.6454 0.7903
0.250 0.3613 0.00496 0.00119 -0.0625 0.6359 0.8959
0.500 0.4095 0.00498 0.00126 -0.0666 0.6253 0.9688
0.750 0.4574 0.00510 0.00130 -0.0710 0.6141 0.9848
1.000 0.5021 0.00519 0.00132 -0.0747 0.6028 0.9932
1.250 0.5490 0.00526 0.00132 -0.0789 0.5916 0.9986
1.500 0.5814 0.00533 0.00133 -0.0800 0.5807 1.0000
1.750 0.6055 0.00542 0.00135 -0.0793 0.5690 1.0000
2.000 0.6298 0.00551 0.00138 -0.0786 0.5569 1.0000
2.250 0.6542 0.00559 0.00142 -0.0779 0.5446 1.0000
2.500 0.6786 0.00569 0.00147 -0.0772 0.5331 1.0000
2.750 0.7031 0.00580 0.00153 -0.0766 0.5215 1.0000
3.000 0.7275 0.00591 0.00160 -0.0759 0.5101 1.0000
3.250 0.7518 0.00604 0.00167 -0.0752 0.4982 1.0000
3.500 0.7763 0.00617 0.00176 -0.0746 0.4855 1.0000
3.750 0.8007 0.00631 0.00185 -0.0739 0.4724 1.0000
4.000 0.8251 0.00645 0.00195 -0.0733 0.4590 1.0000
4.250 0.8493 0.00661 0.00207 -0.0726 0.4454 1.0000
4.500 0.8736 0.00677 0.00219 -0.0720 0.4320 1.0000
4.750 0.8977 0.00695 0.00232 -0.0713 0.4183 1.0000
5.000 0.9218 0.00713 0.00246 -0.0707 0.4042 1.0000
5.250 0.9458 0.00732 0.00261 -0.0700 0.3894 1.0000
5.500 0.9693 0.00755 0.00279 -0.0692 0.3728 1.0000
6.000 1.0160 0.00802 0.00315 -0.0677 0.3404 1.0000
6.250 1.0394 0.00826 0.00335 -0.0670 0.3248 1.0000
6.500 1.0623 0.00853 0.00357 -0.0662 0.3067 1.0000
6.750 1.0844 0.00887 0.00382 -0.0653 0.2862 1.0000
7.000 1.1052 0.00929 0.00411 -0.0642 0.2583 1.0000
7.250 1.1254 0.00976 0.00444 -0.0630 0.2291 1.0000
7.500 1.1453 0.01023 0.00480 -0.0618 0.2023 1.0000
7.750 1.1642 0.01078 0.00519 -0.0604 0.1733 1.0000
8.000 1.1833 0.01130 0.00559 -0.0591 0.1492 1.0000
8.250 1.2019 0.01183 0.00601 -0.0577 0.1261 1.0000
8.500 1.2187 0.01247 0.00651 -0.0561 0.1013 1.0000
8.750 1.2355 0.01307 0.00701 -0.0545 0.0821 1.0000
9.000 1.2513 0.01371 0.00755 -0.0527 0.0635 1.0000
9.250 1.2662 0.01437 0.00812 -0.0508 0.0484 1.0000
9.500 1.2805 0.01501 0.00870 -0.0488 0.0356 1.0000
9.750 1.2889 0.01578 0.00938 -0.0457 0.0227 1.0000
10.000 1.2918 0.01679 0.01031 -0.0418 0.0099 1.0000
10.250 1.3005 0.01760 0.01113 -0.0390 0.0069 1.0000
10.500 1.3114 0.01833 0.01190 -0.0367 0.0057 1.0000
10.750 1.3221 0.01911 0.01275 -0.0346 0.0052 1.0000
11.000 1.3301 0.02010 0.01383 -0.0322 0.0048 1.0000
11.250 1.3406 0.02099 0.01478 -0.0302 0.0046 1.0000
11.500 1.3509 0.02191 0.01578 -0.0284 0.0044 1.0000
11.750 1.3588 0.02304 0.01699 -0.0265 0.0043 1.0000
12.000 1.3665 0.02424 0.01827 -0.0247 0.0042 1.0000
12.250 1.3741 0.02549 0.01960 -0.0231 0.0040 1.0000
12.500 1.3801 0.02692 0.02112 -0.0214 0.0040 1.0000
12.750 1.3863 0.02839 0.02265 -0.0200 0.0038 1.0000
13.000 1.3912 0.03003 0.02437 -0.0187 0.0037 1.0000
13.250 1.3934 0.03198 0.02643 -0.0174 0.0036 1.0000
13.500 1.3952 0.03404 0.02858 -0.0163 0.0035 1.0000
13.750 1.3960 0.03629 0.03092 -0.0153 0.0034 1.0000
14.000 1.3920 0.03912 0.03387 -0.0145 0.0034 1.0000
14.250 1.3827 0.04263 0.03751 -0.0138 0.0033 1.0000
14.500 1.3793 0.04567 0.04066 -0.0135 0.0033 1.0000
14.750 1.3741 0.04908 0.04419 -0.0134 0.0033 1.0000
15.000 1.3652 0.05306 0.04829 -0.0136 0.0032 1.0000
15.250 1.3528 0.05766 0.05304 -0.0141 0.0030 1.0000
15.500 1.3456 0.06177 0.05726 -0.0147 0.0030 1.0000
15.750 1.3390 0.06590 0.06151 -0.0156 0.0030 1.0000
16.000 1.3389 0.06933 0.06503 -0.0165 0.0029 1.0000
16.250 1.3324 0.07372 0.06953 -0.0177 0.0029 1.0000
16.500 1.3179 0.07930 0.07524 -0.0192 0.0030 1.0000
16.750 1.3146 0.08352 0.07957 -0.0207 0.0029 1.0000
17.000 1.3035 0.08892 0.08508 -0.0225 0.0030 1.0000
17.250 1.2968 0.09387 0.09014 -0.0244 0.0029 1.0000
17.500 1.2860 0.09949 0.09587 -0.0266 0.0029 1.0000
17.750 1.2771 0.10503 0.10153 -0.0290 0.0028 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S7055 (10.5%) Flat-Bottomed (s7055-il)