AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.96 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46c03-il-1000000-n5.txt Download as CSV file: xf-ag46c03-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4938 0.09768 0.09622 0.0190 1.0000 0.0059
-7.250 -0.6044 0.09369 0.09219 0.0258 1.0000 0.0059
-5.250 -0.5195 0.01660 0.01274 -0.0272 1.0000 0.0033
-5.000 -0.4938 0.01461 0.01039 -0.0270 1.0000 0.0034
-4.750 -0.4673 0.01343 0.00899 -0.0269 1.0000 0.0035
-4.500 -0.4413 0.01156 0.00679 -0.0267 1.0000 0.0039
-4.250 -0.4104 0.01099 0.00614 -0.0274 0.9803 0.0042
-4.000 -0.3845 0.01092 0.00557 -0.0266 0.8087 0.0044
-3.750 -0.3586 0.01071 0.00506 -0.0261 0.7483 0.0047
-3.250 -0.3040 0.00991 0.00397 -0.0257 0.7213 0.0052
-3.000 -0.2764 0.00954 0.00349 -0.0256 0.7141 0.0055
-2.750 -0.2486 0.00924 0.00310 -0.0254 0.7081 0.0057
-2.500 -0.2208 0.00906 0.00286 -0.0253 0.7026 0.0060
-2.250 -0.1929 0.00860 0.00231 -0.0252 0.6964 0.0067
-2.000 -0.1648 0.00833 0.00201 -0.0251 0.6903 0.0075
-1.750 -0.1367 0.00812 0.00176 -0.0250 0.6827 0.0087
-1.500 -0.1085 0.00792 0.00152 -0.0249 0.6746 0.0112
-1.250 -0.0805 0.00777 0.00135 -0.0248 0.6651 0.0153
-1.000 -0.0524 0.00762 0.00120 -0.0248 0.6536 0.0231
-0.750 -0.0244 0.00743 0.00106 -0.0247 0.6404 0.0425
-0.500 0.0036 0.00725 0.00093 -0.0247 0.6255 0.0731
-0.250 0.0315 0.00710 0.00084 -0.0247 0.6084 0.1084
0.000 0.0594 0.00694 0.00076 -0.0247 0.5894 0.1552
0.250 0.0873 0.00682 0.00070 -0.0247 0.5689 0.2026
0.500 0.1151 0.00663 0.00065 -0.0247 0.5462 0.2764
0.750 0.1427 0.00642 0.00062 -0.0248 0.5220 0.3696
1.000 0.1702 0.00618 0.00060 -0.0249 0.4969 0.4809
1.250 0.1975 0.00593 0.00061 -0.0249 0.4701 0.6044
1.500 0.2241 0.00568 0.00064 -0.0247 0.4436 0.7267
1.750 0.2492 0.00546 0.00068 -0.0240 0.4179 0.8384
2.000 0.2712 0.00532 0.00071 -0.0223 0.3928 0.9335
2.250 0.3050 0.00541 0.00074 -0.0235 0.3644 1.0000
2.500 0.3328 0.00558 0.00078 -0.0235 0.3379 1.0000
2.750 0.3607 0.00574 0.00084 -0.0235 0.3149 1.0000
3.000 0.3885 0.00592 0.00090 -0.0234 0.2895 1.0000
3.250 0.4162 0.00611 0.00098 -0.0234 0.2645 1.0000
3.500 0.4440 0.00630 0.00108 -0.0234 0.2415 1.0000
3.750 0.4717 0.00651 0.00119 -0.0234 0.2167 1.0000
4.000 0.4993 0.00670 0.00130 -0.0234 0.1970 1.0000
4.250 0.5269 0.00693 0.00142 -0.0234 0.1743 1.0000
4.500 0.5545 0.00714 0.00158 -0.0233 0.1568 1.0000
4.750 0.5821 0.00737 0.00173 -0.0233 0.1393 1.0000
5.000 0.6096 0.00759 0.00189 -0.0233 0.1237 1.0000
5.250 0.6371 0.00780 0.00205 -0.0233 0.1110 1.0000
5.500 0.6645 0.00804 0.00225 -0.0232 0.0974 1.0000
5.750 0.6919 0.00828 0.00245 -0.0232 0.0869 1.0000
6.000 0.7192 0.00853 0.00266 -0.0231 0.0757 1.0000
6.250 0.7465 0.00877 0.00288 -0.0231 0.0670 1.0000
6.500 0.7736 0.00904 0.00313 -0.0230 0.0577 1.0000
6.750 0.8006 0.00934 0.00340 -0.0230 0.0489 1.0000
7.000 0.8275 0.00966 0.00369 -0.0229 0.0403 1.0000
7.250 0.8544 0.00994 0.00397 -0.0229 0.0348 1.0000
7.500 0.8811 0.01030 0.00431 -0.0228 0.0280 1.0000
7.750 0.9077 0.01064 0.00466 -0.0227 0.0234 1.0000
8.000 0.9342 0.01100 0.00503 -0.0226 0.0192 1.0000
8.250 0.9606 0.01137 0.00542 -0.0225 0.0164 1.0000
8.500 0.9867 0.01181 0.00586 -0.0223 0.0128 1.0000
8.750 1.0129 0.01219 0.00628 -0.0222 0.0113 1.0000
9.000 1.0387 0.01266 0.00677 -0.0221 0.0095 1.0000
9.250 1.0644 0.01316 0.00733 -0.0219 0.0081 1.0000
9.500 1.0901 0.01360 0.00784 -0.0217 0.0074 1.0000
9.750 1.1155 0.01410 0.00839 -0.0216 0.0066 1.0000
10.000 1.1404 0.01468 0.00902 -0.0214 0.0057 1.0000
10.250 1.1649 0.01536 0.00978 -0.0211 0.0050 1.0000
10.500 1.1897 0.01590 0.01040 -0.0209 0.0047 1.0000
10.750 1.2140 0.01652 0.01110 -0.0206 0.0043 1.0000
11.000 1.2380 0.01717 0.01186 -0.0204 0.0040 1.0000
11.250 1.2615 0.01788 0.01266 -0.0201 0.0037 1.0000
11.500 1.2844 0.01869 0.01355 -0.0198 0.0034 1.0000
11.750 1.3059 0.01975 0.01474 -0.0193 0.0031 1.0000
12.000 1.3265 0.02093 0.01606 -0.0188 0.0029 1.0000
12.250 1.3480 0.02182 0.01708 -0.0185 0.0028 1.0000
12.500 1.3689 0.02277 0.01815 -0.0180 0.0027 1.0000
12.750 1.3890 0.02378 0.01928 -0.0176 0.0025 1.0000
13.000 1.4083 0.02485 0.02049 -0.0171 0.0024 1.0000
13.250 1.4266 0.02598 0.02175 -0.0166 0.0022 1.0000
13.500 1.4440 0.02718 0.02307 -0.0161 0.0021 1.0000
13.750 1.4598 0.02850 0.02451 -0.0155 0.0020 1.0000
14.000 1.4732 0.03001 0.02616 -0.0148 0.0019 1.0000
14.250 1.4835 0.03177 0.02807 -0.0141 0.0018 1.0000
14.500 1.4893 0.03387 0.03033 -0.0132 0.0017 1.0000
14.750 1.4854 0.03638 0.03301 -0.0120 0.0017 1.0000
15.000 1.4751 0.04029 0.03711 -0.0133 0.0016 1.0000
15.250 1.4628 0.04603 0.04305 -0.0177 0.0016 1.0000
15.500 1.4454 0.05325 0.05045 -0.0230 0.0016 1.0000
15.750 1.4217 0.06225 0.05964 -0.0295 0.0016 1.0000
16.000 1.3894 0.07319 0.07076 -0.0364 0.0017 1.0000
16.250 1.3465 0.08607 0.08382 -0.0434 0.0017 1.0000
16.500 1.2910 0.10131 0.09923 -0.0511 0.0019 1.0000
16.750 1.2335 0.11715 0.11521 -0.0590 0.0020 1.0000
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Polar data table (+)
Polar graphs
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