AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 100,000 Max Cl/Cd: 44.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46c03-il-100000-n5.txt Download as CSV file: xf-ag46c03-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5841 0.10581 0.10104 0.0248 1.0000 0.0399
-7.250 -0.5805 0.10198 0.09724 0.0225 1.0000 0.0405
-7.000 -0.5769 0.09808 0.09339 0.0200 1.0000 0.0409
-6.750 -0.5731 0.09409 0.08945 0.0173 1.0000 0.0410
-6.250 -0.5588 0.08319 0.07858 0.0061 1.0000 0.0307
-6.000 -0.5494 0.07857 0.07397 0.0030 1.0000 0.0292
-5.750 -0.5367 0.07335 0.06873 -0.0021 1.0000 0.0284
-5.500 -0.5216 0.06790 0.06322 -0.0074 1.0000 0.0280
-5.250 -0.5042 0.06232 0.05754 -0.0124 1.0000 0.0276
-5.000 -0.4847 0.05652 0.05157 -0.0169 1.0000 0.0268
-4.750 -0.4623 0.04955 0.04431 -0.0215 1.0000 0.0248
-4.250 -0.4107 0.03773 0.03141 -0.0261 1.0000 0.0219
-4.000 -0.3867 0.03354 0.02677 -0.0271 1.0000 0.0217
-3.750 -0.3612 0.02987 0.02258 -0.0276 1.0000 0.0217
-3.500 -0.3347 0.02678 0.01895 -0.0277 1.0000 0.0218
-3.250 -0.3076 0.02426 0.01592 -0.0275 1.0000 0.0222
-3.000 -0.2811 0.02156 0.01285 -0.0274 1.0000 0.0231
-2.750 -0.2547 0.02019 0.01135 -0.0273 1.0000 0.0262
-2.500 -0.2276 0.01885 0.00980 -0.0269 1.0000 0.0296
-2.250 -0.2005 0.01745 0.00820 -0.0263 1.0000 0.0319
-2.000 -0.1743 0.01612 0.00687 -0.0260 1.0000 0.0366
-1.750 -0.1477 0.01522 0.00592 -0.0256 1.0000 0.0460
-1.500 -0.1211 0.01433 0.00504 -0.0253 1.0000 0.0628
-1.250 -0.0946 0.01343 0.00437 -0.0251 1.0000 0.1075
-1.000 -0.0688 0.01251 0.00396 -0.0250 1.0000 0.2175
-0.750 -0.0447 0.01126 0.00371 -0.0248 1.0000 0.4622
-0.500 -0.0291 0.00994 0.00366 -0.0208 1.0000 0.8401
-0.250 0.0110 0.00970 0.00334 -0.0230 1.0000 1.0000
0.000 0.0415 0.00973 0.00318 -0.0237 0.9885 1.0000
0.250 0.0833 0.00980 0.00304 -0.0267 0.9436 1.0000
0.500 0.1227 0.00989 0.00289 -0.0288 0.8958 1.0000
0.750 0.1563 0.01000 0.00278 -0.0296 0.8514 1.0000
1.250 0.2111 0.01034 0.00266 -0.0284 0.7859 1.0000
1.500 0.2373 0.01054 0.00267 -0.0276 0.7610 1.0000
1.750 0.2635 0.01075 0.00272 -0.0270 0.7388 1.0000
2.000 0.2898 0.01098 0.00279 -0.0263 0.7187 1.0000
2.250 0.3160 0.01121 0.00292 -0.0257 0.6989 1.0000
2.500 0.3426 0.01140 0.00305 -0.0253 0.6768 1.0000
2.750 0.3692 0.01156 0.00315 -0.0248 0.6537 1.0000
3.000 0.3957 0.01170 0.00325 -0.0244 0.6285 1.0000
3.250 0.4221 0.01185 0.00334 -0.0238 0.6016 1.0000
3.500 0.4483 0.01202 0.00346 -0.0233 0.5724 1.0000
3.750 0.4744 0.01222 0.00356 -0.0227 0.5408 1.0000
4.000 0.5005 0.01245 0.00371 -0.0222 0.5066 1.0000
4.250 0.5264 0.01274 0.00387 -0.0216 0.4710 1.0000
4.500 0.5524 0.01307 0.00414 -0.0212 0.4335 1.0000
4.750 0.5783 0.01344 0.00440 -0.0208 0.3952 1.0000
5.000 0.6040 0.01386 0.00471 -0.0204 0.3571 1.0000
5.250 0.6297 0.01433 0.00507 -0.0201 0.3193 1.0000
5.500 0.6554 0.01483 0.00552 -0.0198 0.2819 1.0000
5.750 0.6809 0.01539 0.00599 -0.0196 0.2475 1.0000
6.000 0.7064 0.01598 0.00652 -0.0193 0.2159 1.0000
6.250 0.7317 0.01662 0.00712 -0.0191 0.1887 1.0000
6.500 0.7568 0.01731 0.00776 -0.0189 0.1649 1.0000
6.750 0.7819 0.01802 0.00853 -0.0186 0.1444 1.0000
7.000 0.8065 0.01881 0.00930 -0.0184 0.1260 1.0000
7.250 0.8312 0.01962 0.01018 -0.0181 0.1104 1.0000
7.500 0.8556 0.02046 0.01110 -0.0178 0.0949 1.0000
7.750 0.8795 0.02146 0.01217 -0.0174 0.0829 1.0000
8.000 0.9030 0.02248 0.01333 -0.0171 0.0710 1.0000
8.250 0.9257 0.02368 0.01458 -0.0167 0.0616 1.0000
8.500 0.9488 0.02485 0.01596 -0.0162 0.0529 1.0000
8.750 0.9706 0.02629 0.01757 -0.0157 0.0458 1.0000
9.000 0.9918 0.02783 0.01926 -0.0152 0.0407 1.0000
9.250 1.0120 0.02968 0.02135 -0.0146 0.0358 1.0000
9.500 1.0321 0.03148 0.02341 -0.0140 0.0318 1.0000
9.750 1.0497 0.03367 0.02581 -0.0135 0.0293 1.0000
10.000 1.0654 0.03662 0.02914 -0.0127 0.0272 1.0000
10.250 1.0801 0.03933 0.03234 -0.0121 0.0245 1.0000
10.500 1.0919 0.04222 0.03562 -0.0117 0.0227 1.0000
10.750 1.0998 0.04554 0.03929 -0.0112 0.0217 1.0000
11.000 1.1035 0.04909 0.04316 -0.0110 0.0210 1.0000
11.250 1.1015 0.05307 0.04744 -0.0110 0.0205 1.0000
11.500 1.0918 0.05745 0.05211 -0.0115 0.0202 1.0000
11.750 1.0761 0.06249 0.05742 -0.0137 0.0202 1.0000
12.000 1.0566 0.06941 0.06460 -0.0193 0.0204 1.0000
12.250 1.0199 0.08225 0.07777 -0.0307 0.0213 1.0000
12.500 0.9549 0.10588 0.10142 -0.0471 0.0242 1.0000
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Polar data table (+)
Polar graphs
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