AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.98 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag03-il-1000000-n5.txt Download as CSV file: xf-ag03-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5599 0.10765 0.10605 0.0200 1.0000 0.0042
-8.750 -0.5559 0.10376 0.10217 0.0182 1.0000 0.0042
-8.250 -0.5596 0.09296 0.09141 0.0136 1.0000 0.0024
-7.500 -0.5467 0.08083 0.07933 0.0043 1.0000 0.0022
-7.250 -0.5371 0.07518 0.07368 -0.0024 1.0000 0.0022
-7.000 -0.5243 0.06903 0.06750 -0.0096 1.0000 0.0022
-6.750 -0.5085 0.06238 0.06080 -0.0167 1.0000 0.0022
-6.500 -0.4902 0.05551 0.05383 -0.0230 1.0000 0.0022
-6.250 -0.4715 0.04533 0.04344 -0.0302 1.0000 0.0025
-6.000 -0.4504 0.03941 0.03732 -0.0331 1.0000 0.0026
-5.750 -0.4286 0.03387 0.03154 -0.0346 1.0000 0.0028
-5.500 -0.4071 0.02780 0.02514 -0.0353 1.0000 0.0030
-5.250 -0.3874 0.01939 0.01603 -0.0347 1.0000 0.0032
-5.000 -0.3596 0.01577 0.01189 -0.0351 0.9964 0.0033
-4.750 -0.3281 0.01372 0.00948 -0.0359 0.9893 0.0035
-4.500 -0.2955 0.01261 0.00817 -0.0370 0.9802 0.0037
-4.250 -0.2629 0.01170 0.00708 -0.0380 0.9681 0.0040
-4.000 -0.2328 0.01075 0.00594 -0.0383 0.9510 0.0041
-3.750 -0.2059 0.00986 0.00484 -0.0378 0.9299 0.0040
-3.500 -0.1802 0.00920 0.00401 -0.0371 0.9069 0.0040
-3.250 -0.1545 0.00869 0.00333 -0.0364 0.8817 0.0040
-3.000 -0.1285 0.00830 0.00278 -0.0357 0.8546 0.0040
-2.750 -0.1020 0.00801 0.00232 -0.0352 0.8262 0.0040
-2.500 -0.0752 0.00780 0.00194 -0.0348 0.7968 0.0041
-2.250 -0.0481 0.00765 0.00163 -0.0344 0.7676 0.0042
-2.000 -0.0209 0.00755 0.00138 -0.0342 0.7386 0.0044
-1.750 0.0066 0.00745 0.00115 -0.0339 0.7106 0.0069
-1.500 0.0339 0.00728 0.00100 -0.0338 0.6837 0.0311
-1.250 0.0613 0.00717 0.00089 -0.0337 0.6565 0.0608
-1.000 0.0887 0.00703 0.00082 -0.0336 0.6299 0.1087
-0.750 0.1161 0.00690 0.00077 -0.0336 0.6026 0.1671
-0.500 0.1436 0.00680 0.00073 -0.0335 0.5762 0.2207
-0.250 0.1710 0.00667 0.00069 -0.0335 0.5494 0.2939
0.000 0.1980 0.00643 0.00068 -0.0336 0.5215 0.4103
0.250 0.2248 0.00614 0.00068 -0.0335 0.4940 0.5503
0.500 0.2511 0.00586 0.00070 -0.0333 0.4667 0.6855
0.750 0.2748 0.00551 0.00074 -0.0324 0.4411 0.8392
1.000 0.2972 0.00538 0.00079 -0.0308 0.4158 0.9419
1.250 0.3353 0.00550 0.00081 -0.0331 0.3863 1.0000
1.750 0.3901 0.00582 0.00091 -0.0329 0.3368 1.0000
2.000 0.4175 0.00599 0.00097 -0.0328 0.3152 1.0000
2.500 0.4722 0.00635 0.00113 -0.0326 0.2688 1.0000
2.750 0.4995 0.00654 0.00122 -0.0325 0.2478 1.0000
3.000 0.5268 0.00674 0.00134 -0.0324 0.2253 1.0000
3.250 0.5540 0.00695 0.00145 -0.0324 0.2042 1.0000
3.500 0.5813 0.00714 0.00158 -0.0323 0.1872 1.0000
3.750 0.6085 0.00736 0.00171 -0.0322 0.1695 1.0000
4.000 0.6356 0.00758 0.00188 -0.0321 0.1513 1.0000
4.250 0.6628 0.00779 0.00204 -0.0320 0.1377 1.0000
4.500 0.6899 0.00802 0.00222 -0.0319 0.1228 1.0000
4.750 0.7168 0.00830 0.00242 -0.0318 0.1059 1.0000
5.000 0.7437 0.00854 0.00263 -0.0317 0.0941 1.0000
5.250 0.7706 0.00880 0.00285 -0.0316 0.0819 1.0000
5.500 0.7972 0.00910 0.00310 -0.0315 0.0692 1.0000
5.750 0.8240 0.00937 0.00335 -0.0314 0.0609 1.0000
6.000 0.8505 0.00968 0.00364 -0.0312 0.0517 1.0000
6.250 0.8771 0.00997 0.00392 -0.0311 0.0451 1.0000
6.500 0.9036 0.01027 0.00422 -0.0310 0.0395 1.0000
6.750 0.9298 0.01060 0.00454 -0.0308 0.0335 1.0000
7.000 0.9561 0.01092 0.00488 -0.0306 0.0290 1.0000
7.250 0.9821 0.01129 0.00524 -0.0304 0.0242 1.0000
7.500 1.0080 0.01166 0.00565 -0.0302 0.0202 1.0000
7.750 1.0336 0.01207 0.00605 -0.0300 0.0164 1.0000
8.000 1.0590 0.01250 0.00650 -0.0298 0.0128 1.0000
8.250 1.0840 0.01301 0.00700 -0.0295 0.0094 1.0000
8.500 1.1091 0.01348 0.00750 -0.0293 0.0072 1.0000
8.750 1.1336 0.01403 0.00807 -0.0289 0.0053 1.0000
9.000 1.1583 0.01452 0.00862 -0.0286 0.0044 1.0000
9.250 1.1827 0.01507 0.00925 -0.0283 0.0036 1.0000
9.500 1.2065 0.01568 0.00991 -0.0279 0.0028 1.0000
9.750 1.2304 0.01626 0.01057 -0.0275 0.0024 1.0000
10.000 1.2536 0.01692 0.01130 -0.0271 0.0019 1.0000
10.250 1.2761 0.01770 0.01216 -0.0266 0.0014 1.0000
10.500 1.2988 0.01839 0.01294 -0.0261 0.0012 1.0000
10.750 1.3208 0.01915 0.01381 -0.0256 0.0010 1.0000
11.000 1.3418 0.02003 0.01479 -0.0249 0.0008 1.0000
11.250 1.3615 0.02109 0.01599 -0.0242 0.0006 1.0000
11.500 1.3798 0.02231 0.01738 -0.0233 0.0005 1.0000
11.750 1.3985 0.02336 0.01856 -0.0225 0.0005 1.0000
12.000 1.4159 0.02453 0.01988 -0.0216 0.0004 1.0000
12.250 1.4317 0.02583 0.02133 -0.0206 0.0004 1.0000
12.500 1.4456 0.02727 0.02294 -0.0195 0.0004 1.0000
12.750 1.4571 0.02884 0.02469 -0.0182 0.0004 1.0000
13.000 1.4657 0.03059 0.02661 -0.0167 0.0003 1.0000
13.250 1.4698 0.03252 0.02872 -0.0149 0.0003 1.0000
13.500 1.4667 0.03462 0.03099 -0.0125 0.0003 1.0000
13.750 1.4602 0.03727 0.03381 -0.0111 0.0003 1.0000
14.000 1.4509 0.04082 0.03755 -0.0112 0.0003 1.0000
14.250 1.4396 0.04549 0.04240 -0.0132 0.0003 1.0000
14.500 1.4238 0.05190 0.04901 -0.0174 0.0003 1.0000
14.750 1.4022 0.06040 0.05771 -0.0234 0.0003 1.0000
15.000 1.3728 0.07108 0.06858 -0.0306 0.0003 1.0000
15.250 1.3348 0.08335 0.08101 -0.0376 0.0003 1.0000
15.500 1.2911 0.09641 0.09421 -0.0443 0.0004 1.0000
15.750 1.2453 0.10986 0.10777 -0.0507 0.0004 1.0000
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Polar data table (+)
Polar graphs
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