AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 200,000 Max Cl/Cd: 61 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45c03-il-200000-n5.txt Download as CSV file: xf-ag45c03-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -03f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4571 0.08408 0.08094 0.0089 1.0000 0.0163
-6.250 -0.5436 0.07423 0.07100 0.0001 1.0000 0.0120
-6.000 -0.5322 0.06869 0.06543 -0.0056 1.0000 0.0118
-5.750 -0.5174 0.06269 0.05938 -0.0116 1.0000 0.0116
-5.500 -0.5000 0.05620 0.05277 -0.0173 1.0000 0.0114
-5.250 -0.4801 0.04909 0.04544 -0.0226 1.0000 0.0114
-5.000 -0.4565 0.04062 0.03654 -0.0267 1.0000 0.0121
-4.750 -0.4360 0.03405 0.02945 -0.0294 1.0000 0.0127
-4.500 -0.4120 0.02946 0.02432 -0.0303 1.0000 0.0125
-4.250 -0.3868 0.02612 0.02047 -0.0307 1.0000 0.0124
-4.000 -0.3611 0.02322 0.01706 -0.0308 1.0000 0.0124
-3.750 -0.3350 0.02063 0.01403 -0.0308 1.0000 0.0124
-3.500 -0.3085 0.01845 0.01150 -0.0306 1.0000 0.0127
-3.250 -0.2819 0.01681 0.00965 -0.0303 1.0000 0.0131
-3.000 -0.2551 0.01559 0.00829 -0.0301 1.0000 0.0137
-2.750 -0.2282 0.01458 0.00719 -0.0298 1.0000 0.0146
-2.500 -0.2012 0.01368 0.00619 -0.0295 1.0000 0.0160
-2.250 -0.1704 0.01293 0.00537 -0.0301 0.9821 0.0192
-2.000 -0.1299 0.01218 0.00452 -0.0327 0.9074 0.0238
-1.750 -0.0978 0.01170 0.00380 -0.0330 0.8270 0.0325
-1.500 -0.0718 0.01135 0.00327 -0.0321 0.7827 0.0519
-1.000 -0.0196 0.01061 0.00276 -0.0314 0.7389 0.1766
-0.750 0.0068 0.01025 0.00260 -0.0311 0.7242 0.2653
-0.500 0.0327 0.00977 0.00247 -0.0309 0.7117 0.3961
-0.250 0.0567 0.00913 0.00243 -0.0301 0.7005 0.5880
0.000 0.0765 0.00851 0.00244 -0.0277 0.6878 0.7823
0.250 0.1090 0.00820 0.00232 -0.0276 0.6742 0.9609
0.500 0.1412 0.00823 0.00219 -0.0284 0.6599 1.0000
0.750 0.1688 0.00829 0.00211 -0.0282 0.6454 1.0000
1.000 0.1964 0.00836 0.00204 -0.0280 0.6303 1.0000
1.250 0.2240 0.00843 0.00198 -0.0278 0.6146 1.0000
1.500 0.2516 0.00852 0.00193 -0.0276 0.5983 1.0000
1.750 0.2791 0.00861 0.00190 -0.0274 0.5816 1.0000
2.000 0.3066 0.00872 0.00189 -0.0272 0.5646 1.0000
2.250 0.3341 0.00884 0.00191 -0.0270 0.5468 1.0000
2.500 0.3616 0.00897 0.00193 -0.0268 0.5288 1.0000
2.750 0.3890 0.00912 0.00197 -0.0266 0.5108 1.0000
3.000 0.4165 0.00927 0.00203 -0.0265 0.4926 1.0000
3.250 0.4439 0.00943 0.00213 -0.0263 0.4737 1.0000
3.500 0.4713 0.00961 0.00222 -0.0262 0.4548 1.0000
3.750 0.4987 0.00979 0.00233 -0.0260 0.4356 1.0000
4.000 0.5260 0.00998 0.00247 -0.0259 0.4157 1.0000
4.250 0.5533 0.01020 0.00261 -0.0258 0.3956 1.0000
4.500 0.5805 0.01042 0.00280 -0.0256 0.3740 1.0000
4.750 0.6076 0.01067 0.00299 -0.0255 0.3529 1.0000
5.000 0.6347 0.01093 0.00320 -0.0254 0.3306 1.0000
5.250 0.6617 0.01121 0.00344 -0.0253 0.3085 1.0000
5.500 0.6885 0.01153 0.00373 -0.0252 0.2859 1.0000
5.750 0.7153 0.01186 0.00402 -0.0251 0.2630 1.0000
6.000 0.7419 0.01222 0.00434 -0.0250 0.2405 1.0000
6.250 0.7684 0.01262 0.00472 -0.0249 0.2179 1.0000
6.500 0.7948 0.01303 0.00511 -0.0248 0.1965 1.0000
6.750 0.8209 0.01350 0.00553 -0.0247 0.1755 1.0000
7.000 0.8470 0.01396 0.00599 -0.0246 0.1560 1.0000
7.250 0.8729 0.01448 0.00648 -0.0245 0.1371 1.0000
7.500 0.8984 0.01504 0.00705 -0.0244 0.1203 1.0000
7.750 0.9240 0.01559 0.00763 -0.0242 0.1039 1.0000
8.000 0.9492 0.01620 0.00825 -0.0241 0.0889 1.0000
8.250 0.9741 0.01686 0.00893 -0.0239 0.0745 1.0000
8.500 0.9987 0.01757 0.00967 -0.0237 0.0619 1.0000
8.750 1.0228 0.01835 0.01051 -0.0235 0.0505 1.0000
9.000 1.0465 0.01922 0.01144 -0.0232 0.0416 1.0000
9.250 1.0693 0.02022 0.01248 -0.0229 0.0339 1.0000
9.500 1.0922 0.02118 0.01358 -0.0225 0.0286 1.0000
9.750 1.1133 0.02244 0.01494 -0.0221 0.0244 1.0000
10.000 1.1351 0.02347 0.01613 -0.0217 0.0209 1.0000
10.250 1.1541 0.02497 0.01778 -0.0212 0.0184 1.0000
10.500 1.1718 0.02664 0.01964 -0.0205 0.0169 1.0000
10.750 1.1903 0.02806 0.02128 -0.0198 0.0152 1.0000
11.000 1.2082 0.02942 0.02279 -0.0194 0.0136 1.0000
11.250 1.2226 0.03120 0.02472 -0.0188 0.0124 1.0000
11.500 1.2311 0.03377 0.02747 -0.0178 0.0117 1.0000
11.750 1.2416 0.03592 0.02989 -0.0170 0.0112 1.0000
12.000 1.2482 0.03839 0.03262 -0.0161 0.0108 1.0000
12.250 1.2497 0.04107 0.03556 -0.0152 0.0104 1.0000
12.500 1.2466 0.04409 0.03882 -0.0148 0.0101 1.0000
12.750 1.2418 0.04781 0.04277 -0.0162 0.0098 1.0000
13.000 1.2359 0.05216 0.04734 -0.0186 0.0095 1.0000
13.250 1.2282 0.05702 0.05240 -0.0215 0.0093 1.0000
13.500 1.2185 0.06245 0.05802 -0.0249 0.0092 1.0000
13.750 1.2060 0.06860 0.06436 -0.0287 0.0091 1.0000
14.000 1.1908 0.07546 0.07141 -0.0329 0.0091 1.0000
14.250 1.1736 0.08292 0.07904 -0.0374 0.0091 1.0000
14.500 1.1517 0.09159 0.08789 -0.0424 0.0093 1.0000
14.750 1.1272 0.10114 0.09762 -0.0478 0.0095 1.0000
15.000 1.1011 0.11157 0.10819 -0.0537 0.0098 1.0000
15.250 1.0745 0.12283 0.11956 -0.0598 0.0102 1.0000
15.500 1.0460 0.13536 0.13219 -0.0665 0.0106 1.0000
15.750 1.0144 0.14973 0.14659 -0.0737 0.0110 1.0000
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Polar data table (+)
Polar graphs
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