AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46c03-il-1000000.txt Download as CSV file: xf-ag46c03-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -03f
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6037 0.09590 0.09440 0.0275 1.0000 0.0079
-7.000 -0.6003 0.09188 0.09040 0.0251 1.0000 0.0081
-6.750 -0.5968 0.08771 0.08625 0.0220 1.0000 0.0084
-6.500 -0.5896 0.08286 0.08139 0.0168 1.0000 0.0087
-6.250 -0.5763 0.07710 0.07564 0.0093 1.0000 0.0090
-6.000 -0.5587 0.07143 0.06994 0.0021 1.0000 0.0092
-5.750 -0.5397 0.06568 0.06415 -0.0045 1.0000 0.0093
-5.500 -0.5194 0.05970 0.05810 -0.0104 1.0000 0.0094
-5.250 -0.4978 0.05360 0.05190 -0.0155 1.0000 0.0094
-5.000 -0.4751 0.04745 0.04560 -0.0195 1.0000 0.0094
-4.750 -0.4519 0.04124 0.03919 -0.0225 1.0000 0.0094
-4.500 -0.4285 0.03517 0.03285 -0.0246 1.0000 0.0095
-3.500 -0.3321 0.01216 0.00759 -0.0266 1.0000 0.0072
-3.250 -0.3049 0.01134 0.00666 -0.0264 1.0000 0.0079
-3.000 -0.2776 0.01057 0.00579 -0.0261 1.0000 0.0085
-2.750 -0.2503 0.00986 0.00498 -0.0258 1.0000 0.0089
-2.500 -0.2161 0.00921 0.00425 -0.0271 0.9814 0.0092
-2.250 -0.1844 0.00853 0.00332 -0.0276 0.8919 0.0099
-2.000 -0.1618 0.00825 0.00257 -0.0261 0.7881 0.0108
-1.750 -0.1347 0.00799 0.00212 -0.0257 0.7557 0.0118
-1.500 -0.1070 0.00780 0.00180 -0.0255 0.7393 0.0141
-1.250 -0.0790 0.00753 0.00145 -0.0253 0.7278 0.0221
-0.500 0.0043 0.00677 0.00105 -0.0252 0.7022 0.1643
-0.250 0.0321 0.00649 0.00098 -0.0252 0.6938 0.2413
0.000 0.0598 0.00599 0.00091 -0.0254 0.6846 0.3819
0.250 0.0869 0.00539 0.00086 -0.0254 0.6745 0.5700
0.500 0.1118 0.00470 0.00085 -0.0248 0.6630 0.7880
0.750 0.1325 0.00432 0.00083 -0.0227 0.6496 0.9222
1.000 0.1677 0.00426 0.00076 -0.0240 0.6320 1.0000
1.250 0.1956 0.00433 0.00072 -0.0239 0.6126 1.0000
1.500 0.2236 0.00441 0.00070 -0.0238 0.5908 1.0000
1.750 0.2515 0.00452 0.00069 -0.0237 0.5673 1.0000
2.000 0.2794 0.00464 0.00069 -0.0236 0.5414 1.0000
2.250 0.3073 0.00477 0.00071 -0.0236 0.5141 1.0000
2.500 0.3351 0.00492 0.00074 -0.0235 0.4852 1.0000
2.750 0.3629 0.00507 0.00078 -0.0235 0.4577 1.0000
3.000 0.3907 0.00524 0.00084 -0.0234 0.4276 1.0000
3.250 0.4184 0.00543 0.00090 -0.0234 0.3975 1.0000
3.500 0.4462 0.00562 0.00099 -0.0233 0.3674 1.0000
3.750 0.4738 0.00584 0.00108 -0.0233 0.3354 1.0000
4.000 0.5014 0.00606 0.00119 -0.0233 0.3070 1.0000
4.250 0.5289 0.00630 0.00131 -0.0233 0.2748 1.0000
4.500 0.5565 0.00654 0.00146 -0.0233 0.2468 1.0000
4.750 0.5839 0.00681 0.00161 -0.0232 0.2175 1.0000
5.000 0.6113 0.00708 0.00177 -0.0232 0.1906 1.0000
5.250 0.6386 0.00736 0.00195 -0.0232 0.1668 1.0000
5.500 0.6659 0.00764 0.00216 -0.0232 0.1446 1.0000
5.750 0.6931 0.00792 0.00237 -0.0231 0.1268 1.0000
6.000 0.7204 0.00819 0.00259 -0.0231 0.1109 1.0000
6.250 0.7476 0.00846 0.00282 -0.0231 0.0973 1.0000
6.500 0.7747 0.00875 0.00308 -0.0230 0.0842 1.0000
6.750 0.8017 0.00906 0.00334 -0.0229 0.0725 1.0000
7.000 0.8286 0.00939 0.00363 -0.0229 0.0609 1.0000
7.250 0.8553 0.00975 0.00396 -0.0228 0.0501 1.0000
7.500 0.8820 0.01009 0.00427 -0.0227 0.0423 1.0000
7.750 0.9087 0.01044 0.00464 -0.0226 0.0351 1.0000
8.000 0.9350 0.01090 0.00509 -0.0225 0.0279 1.0000
8.250 0.9613 0.01130 0.00549 -0.0224 0.0232 1.0000
8.500 0.9873 0.01181 0.00603 -0.0222 0.0187 1.0000
8.750 1.0132 0.01226 0.00650 -0.0220 0.0156 1.0000
9.000 1.0382 0.01306 0.00738 -0.0217 0.0126 1.0000
9.250 1.0640 0.01349 0.00789 -0.0216 0.0115 1.0000
9.500 1.0894 0.01404 0.00849 -0.0214 0.0101 1.0000
9.750 1.1114 0.01549 0.01012 -0.0208 0.0082 1.0000
10.000 1.1371 0.01585 0.01052 -0.0207 0.0078 1.0000
10.250 1.1616 0.01648 0.01124 -0.0204 0.0072 1.0000
10.500 1.1856 0.01720 0.01205 -0.0201 0.0066 1.0000
10.750 1.2092 0.01797 0.01290 -0.0198 0.0061 1.0000
11.000 1.2304 0.01922 0.01430 -0.0193 0.0055 1.0000
11.250 1.2431 0.02219 0.01762 -0.0182 0.0050 1.0000
11.500 1.2652 0.02302 0.01857 -0.0178 0.0049 1.0000
11.750 1.2858 0.02408 0.01976 -0.0174 0.0047 1.0000
12.000 1.3055 0.02521 0.02103 -0.0169 0.0044 1.0000
12.250 1.3244 0.02639 0.02234 -0.0164 0.0041 1.0000
12.500 1.3428 0.02753 0.02360 -0.0160 0.0039 1.0000
12.750 1.3604 0.02869 0.02486 -0.0155 0.0036 1.0000
13.000 1.3751 0.03017 0.02645 -0.0150 0.0034 1.0000
13.250 1.3832 0.03239 0.02886 -0.0142 0.0033 1.0000
13.500 1.3816 0.03551 0.03223 -0.0134 0.0032 1.0000
13.750 1.3677 0.03930 0.03624 -0.0129 0.0031 1.0000
14.000 1.3543 0.04489 0.04205 -0.0171 0.0031 1.0000
14.250 1.3397 0.05171 0.04907 -0.0225 0.0031 1.0000
14.500 1.3236 0.05944 0.05697 -0.0284 0.0031 1.0000
14.750 1.3066 0.06755 0.06523 -0.0340 0.0031 1.0000
15.000 1.2861 0.07635 0.07416 -0.0394 0.0032 1.0000
15.250 1.2636 0.08537 0.08328 -0.0443 0.0032 1.0000
15.500 1.2367 0.09517 0.09319 -0.0493 0.0033 1.0000
15.750 1.2030 0.10643 0.10457 -0.0549 0.0034 1.0000
16.000 1.1584 0.12036 0.11865 -0.0617 0.0036 1.0000
16.250 1.0167 0.16276 0.16133 -0.0824 0.0049 1.0000
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Polar data table (+)
Polar graphs
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