AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 100,000 Max Cl/Cd: 44.05 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5045-il-100000.txt Download as CSV file: xf-as5045-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AS5045 (15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5132 0.10171 0.09732 -0.0182 1.0000 0.1855
-9.750 -0.5301 0.09682 0.09255 -0.0219 1.0000 0.1984
-8.250 -0.7140 0.04930 0.04273 -0.0445 0.9850 0.0784
-8.000 -0.6872 0.04348 0.03634 -0.0454 0.9787 0.0646
-7.750 -0.6589 0.03913 0.03114 -0.0465 0.9730 0.0571
-7.500 -0.6259 0.03698 0.02864 -0.0477 0.9677 0.0549
-7.250 -0.5931 0.03403 0.02548 -0.0490 0.9631 0.0537
-7.000 -0.5559 0.03161 0.02282 -0.0507 0.9598 0.0530
-6.750 -0.5214 0.02987 0.02088 -0.0518 0.9558 0.0540
-6.500 -0.4898 0.02874 0.01953 -0.0525 0.9511 0.0558
-6.250 -0.4567 0.02668 0.01766 -0.0531 0.9482 0.0580
-6.000 -0.4235 0.02534 0.01642 -0.0539 0.9450 0.0605
-5.750 -0.3978 0.02436 0.01545 -0.0539 0.9401 0.0638
-5.500 -0.3739 0.02336 0.01442 -0.0539 0.9349 0.0683
-5.250 -0.3471 0.02222 0.01328 -0.0549 0.9309 0.0805
-5.000 -0.3300 0.01992 0.01185 -0.0553 0.9265 0.1822
-4.750 -0.3261 0.02181 0.01591 -0.0474 0.9205 0.6210
-4.500 -0.3019 0.02577 0.01983 -0.0400 0.9170 0.6614
-4.250 -0.2710 0.03013 0.02419 -0.0306 0.9153 0.6980
-4.000 -0.2387 0.03050 0.02436 -0.0301 0.9127 0.7130
-3.750 -0.2150 0.03074 0.02447 -0.0283 0.9083 0.7218
-3.500 -0.1928 0.03066 0.02425 -0.0273 0.9039 0.7329
-3.250 -0.1699 0.03042 0.02387 -0.0272 0.8998 0.7452
-3.000 -0.1356 0.03033 0.02364 -0.0277 0.8970 0.7541
-2.750 -0.1214 0.03023 0.02347 -0.0260 0.8918 0.7637
-2.500 -0.1094 0.03005 0.02319 -0.0249 0.8863 0.7750
-2.250 -0.0743 0.02985 0.02290 -0.0254 0.8830 0.7809
-2.000 -0.0596 0.02967 0.02262 -0.0250 0.8783 0.7905
-1.750 -0.0408 0.02962 0.02253 -0.0233 0.8728 0.7960
-1.500 -0.0198 0.02946 0.02229 -0.0231 0.8678 0.8033
-1.250 0.0105 0.02919 0.02194 -0.0240 0.8641 0.8092
-1.000 0.0184 0.02931 0.02205 -0.0216 0.8572 0.8152
-0.750 0.0363 0.02920 0.02187 -0.0215 0.8513 0.8216
-0.500 0.0719 0.02897 0.02158 -0.0227 0.8475 0.8256
-0.250 0.0769 0.02917 0.02179 -0.0201 0.8391 0.8307
0.000 0.1043 0.02905 0.02162 -0.0209 0.8335 0.8355
0.250 0.1198 0.02915 0.02170 -0.0199 0.8262 0.8399
0.500 0.1441 0.02912 0.02166 -0.0197 0.8193 0.8437
0.750 0.1744 0.02906 0.02158 -0.0204 0.8136 0.8477
1.000 0.1891 0.02926 0.02178 -0.0197 0.8039 0.8518
1.250 0.2263 0.02904 0.02153 -0.0211 0.7989 0.8548
1.500 0.2378 0.02930 0.02184 -0.0194 0.7877 0.8582
1.750 0.2671 0.02927 0.02181 -0.0197 0.7804 0.8611
2.000 0.2906 0.02934 0.02190 -0.0197 0.7706 0.8645
2.250 0.3143 0.02951 0.02210 -0.0199 0.7604 0.8676
2.500 0.3486 0.02925 0.02185 -0.0206 0.7530 0.8699
2.750 0.3674 0.02940 0.02206 -0.0196 0.7411 0.8728
3.000 0.4042 0.02892 0.02158 -0.0198 0.7354 0.8755
3.250 0.4254 0.02902 0.02175 -0.0193 0.7222 0.8783
3.500 0.4503 0.02902 0.02181 -0.0192 0.7099 0.8811
3.750 0.4887 0.02832 0.02111 -0.0197 0.7037 0.8838
4.000 0.5113 0.02818 0.02107 -0.0189 0.6901 0.8867
4.250 0.5357 0.02794 0.02091 -0.0182 0.6771 0.8894
4.500 0.5646 0.02744 0.02048 -0.0178 0.6659 0.8920
4.750 0.5989 0.02653 0.01962 -0.0176 0.6571 0.8949
5.000 0.6266 0.02601 0.01920 -0.0173 0.6432 0.8983
5.250 0.6546 0.02531 0.01860 -0.0168 0.6294 0.9014
5.500 0.6827 0.02443 0.01783 -0.0160 0.6155 0.9042
5.750 0.7127 0.02343 0.01692 -0.0155 0.6006 0.9074
6.000 0.7436 0.02233 0.01590 -0.0150 0.5840 0.9111
6.250 0.7763 0.02116 0.01479 -0.0148 0.5650 0.9150
6.500 0.8022 0.02039 0.01407 -0.0138 0.5376 0.9188
6.750 0.8296 0.01974 0.01335 -0.0130 0.5050 0.9226
7.000 0.8543 0.01962 0.01306 -0.0122 0.4650 0.9268
7.250 0.8765 0.01990 0.01306 -0.0113 0.4244 0.9316
7.500 0.8946 0.02043 0.01343 -0.0100 0.3841 0.9373
7.750 0.9132 0.02115 0.01394 -0.0091 0.3478 0.9436
8.000 0.9314 0.02194 0.01454 -0.0082 0.3149 0.9501
8.250 0.9501 0.02281 0.01529 -0.0077 0.2847 0.9579
8.500 0.9701 0.02375 0.01614 -0.0075 0.2571 0.9672
8.750 0.9925 0.02484 0.01710 -0.0080 0.2328 0.9809
9.000 1.0141 0.02593 0.01816 -0.0084 0.2108 1.0000
9.250 1.0368 0.02722 0.01933 -0.0091 0.1921 1.0000
9.500 1.0609 0.02864 0.02061 -0.0100 0.1752 1.0000
9.750 1.0855 0.03011 0.02203 -0.0110 0.1603 1.0000
10.000 1.1081 0.03151 0.02349 -0.0117 0.1474 1.0000
10.250 1.1316 0.03310 0.02520 -0.0124 0.1362 1.0000
10.500 1.1565 0.03486 0.02698 -0.0133 0.1266 1.0000
10.750 1.1849 0.03658 0.02858 -0.0146 0.1181 1.0000
11.000 1.2034 0.03850 0.03083 -0.0147 0.1114 1.0000
11.250 1.2311 0.04035 0.03254 -0.0158 0.1048 1.0000
11.500 1.2468 0.04274 0.03528 -0.0156 0.1002 1.0000
11.750 1.2607 0.04474 0.03750 -0.0152 0.0956 1.0000
12.000 1.2895 0.04750 0.04012 -0.0165 0.0907 1.0000
12.250 1.2874 0.04995 0.04304 -0.0144 0.0887 1.0000
12.500 1.2840 0.05266 0.04610 -0.0126 0.0865 1.0000
12.750 1.2834 0.05532 0.04900 -0.0113 0.0841 1.0000
13.000 1.2895 0.05766 0.05142 -0.0106 0.0814 1.0000
13.250 1.3052 0.06156 0.05529 -0.0109 0.0786 1.0000
13.500 1.2848 0.06513 0.05921 -0.0093 0.0782 1.0000
13.750 1.2621 0.06937 0.06379 -0.0086 0.0779 1.0000
14.000 1.2369 0.07429 0.06900 -0.0087 0.0777 1.0000
14.250 1.2092 0.07989 0.07488 -0.0096 0.0776 1.0000
14.500 1.1794 0.08625 0.08149 -0.0113 0.0778 1.0000
14.750 1.1476 0.09348 0.08893 -0.0139 0.0780 1.0000
15.000 1.1147 0.10167 0.09729 -0.0175 0.0784 1.0000
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Polar data table (+)
Polar graphs
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