AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.43 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45c03-il-1000000.txt Download as CSV file: xf-ag45c03-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5734 0.09370 0.09222 0.0222 1.0000 0.0081
-7.000 -0.5700 0.08952 0.08805 0.0195 1.0000 0.0081
-6.750 -0.5665 0.08517 0.08372 0.0163 1.0000 0.0081
-6.500 -0.5585 0.08009 0.07865 0.0107 1.0000 0.0081
-6.250 -0.5463 0.07431 0.07287 0.0037 1.0000 0.0082
-6.000 -0.5311 0.06801 0.06654 -0.0038 1.0000 0.0082
-5.750 -0.5133 0.06127 0.05975 -0.0110 1.0000 0.0082
-5.500 -0.4936 0.05419 0.05256 -0.0174 1.0000 0.0082
-4.250 -0.3861 0.01958 0.01598 -0.0308 1.0000 0.0083
-4.000 -0.3604 0.01625 0.01218 -0.0307 1.0000 0.0083
-3.750 -0.3324 0.01388 0.00948 -0.0309 0.9948 0.0084
-3.500 -0.2960 0.01234 0.00759 -0.0325 0.9039 0.0084
-3.250 -0.2750 0.01159 0.00624 -0.0307 0.7763 0.0085
-3.000 -0.2486 0.01069 0.00512 -0.0304 0.7479 0.0091
-2.750 -0.2212 0.01008 0.00435 -0.0301 0.7334 0.0093
-2.500 -0.1935 0.00945 0.00356 -0.0299 0.7231 0.0094
-2.250 -0.1657 0.00899 0.00297 -0.0297 0.7145 0.0096
-2.000 -0.1377 0.00863 0.00253 -0.0296 0.7071 0.0104
-1.750 -0.1095 0.00837 0.00219 -0.0294 0.6999 0.0119
-1.500 -0.0812 0.00800 0.00176 -0.0293 0.6919 0.0168
-1.250 -0.0528 0.00767 0.00148 -0.0292 0.6833 0.0347
-1.000 -0.0246 0.00737 0.00132 -0.0292 0.6743 0.0739
-0.750 0.0034 0.00708 0.00118 -0.0293 0.6640 0.1290
-0.500 0.0315 0.00679 0.00107 -0.0293 0.6518 0.1935
-0.250 0.0595 0.00652 0.00098 -0.0294 0.6386 0.2681
0.000 0.0873 0.00614 0.00091 -0.0295 0.6243 0.3843
0.250 0.1146 0.00565 0.00086 -0.0296 0.6091 0.5494
0.500 0.1408 0.00513 0.00085 -0.0293 0.5934 0.7307
0.750 0.1644 0.00476 0.00086 -0.0280 0.5775 0.8671
1.000 0.1932 0.00458 0.00081 -0.0277 0.5605 0.9891
1.250 0.2228 0.00466 0.00079 -0.0279 0.5428 1.0000
1.500 0.2510 0.00475 0.00078 -0.0279 0.5254 1.0000
1.750 0.2792 0.00485 0.00078 -0.0279 0.5085 1.0000
2.000 0.3074 0.00494 0.00079 -0.0278 0.4916 1.0000
2.250 0.3355 0.00505 0.00081 -0.0278 0.4746 1.0000
2.500 0.3637 0.00515 0.00084 -0.0278 0.4579 1.0000
2.750 0.3918 0.00527 0.00088 -0.0278 0.4409 1.0000
3.000 0.4199 0.00540 0.00093 -0.0278 0.4238 1.0000
3.250 0.4480 0.00552 0.00099 -0.0278 0.4057 1.0000
3.500 0.4761 0.00565 0.00105 -0.0277 0.3872 1.0000
3.750 0.5040 0.00581 0.00112 -0.0277 0.3676 1.0000
4.000 0.5320 0.00596 0.00121 -0.0277 0.3492 1.0000
4.250 0.5598 0.00614 0.00132 -0.0277 0.3282 1.0000
4.500 0.5877 0.00632 0.00142 -0.0277 0.3089 1.0000
4.750 0.6154 0.00652 0.00155 -0.0277 0.2868 1.0000
5.000 0.6432 0.00673 0.00168 -0.0277 0.2670 1.0000
5.250 0.6707 0.00697 0.00184 -0.0277 0.2445 1.0000
5.500 0.6983 0.00720 0.00201 -0.0277 0.2241 1.0000
5.750 0.7256 0.00748 0.00220 -0.0277 0.2017 1.0000
6.000 0.7531 0.00773 0.00239 -0.0277 0.1825 1.0000
6.500 0.8075 0.00833 0.00285 -0.0277 0.1442 1.0000
6.750 0.8345 0.00864 0.00310 -0.0276 0.1264 1.0000
7.000 0.8615 0.00897 0.00337 -0.0276 0.1104 1.0000
7.250 0.8883 0.00933 0.00367 -0.0276 0.0947 1.0000
7.500 0.9151 0.00968 0.00398 -0.0275 0.0809 1.0000
7.750 0.9417 0.01005 0.00431 -0.0275 0.0682 1.0000
8.000 0.9682 0.01045 0.00466 -0.0274 0.0558 1.0000
8.250 0.9944 0.01088 0.00506 -0.0273 0.0448 1.0000
8.500 1.0204 0.01136 0.00552 -0.0272 0.0348 1.0000
8.750 1.0462 0.01187 0.00599 -0.0271 0.0270 1.0000
9.000 1.0721 0.01232 0.00646 -0.0269 0.0220 1.0000
9.250 1.0974 0.01293 0.00709 -0.0267 0.0171 1.0000
9.500 1.1229 0.01344 0.00763 -0.0265 0.0145 1.0000
9.750 1.1471 0.01428 0.00855 -0.0262 0.0116 1.0000
10.000 1.1725 0.01472 0.00906 -0.0260 0.0104 1.0000
10.250 1.1971 0.01533 0.00970 -0.0258 0.0092 1.0000
10.500 1.2184 0.01667 0.01120 -0.0252 0.0077 1.0000
10.750 1.2430 0.01721 0.01181 -0.0250 0.0073 1.0000
11.000 1.2665 0.01792 0.01261 -0.0247 0.0067 1.0000
11.250 1.2895 0.01870 0.01347 -0.0244 0.0062 1.0000
11.500 1.3117 0.01955 0.01441 -0.0240 0.0057 1.0000
11.750 1.3294 0.02116 0.01616 -0.0233 0.0051 1.0000
12.000 1.3457 0.02286 0.01808 -0.0225 0.0047 1.0000
12.250 1.3671 0.02361 0.01891 -0.0222 0.0045 1.0000
12.500 1.3863 0.02465 0.02007 -0.0216 0.0042 1.0000
12.750 1.4034 0.02591 0.02146 -0.0210 0.0040 1.0000
13.000 1.4190 0.02726 0.02293 -0.0203 0.0038 1.0000
13.250 1.4328 0.02871 0.02450 -0.0196 0.0036 1.0000
13.500 1.4439 0.03034 0.02626 -0.0188 0.0035 1.0000
13.750 1.4504 0.03229 0.02834 -0.0180 0.0033 1.0000
14.000 1.4466 0.03478 0.03099 -0.0168 0.0032 1.0000
14.250 1.4381 0.03892 0.03531 -0.0189 0.0032 1.0000
14.500 1.4290 0.04415 0.04073 -0.0225 0.0031 1.0000
14.750 1.4162 0.05015 0.04690 -0.0263 0.0031 1.0000
15.000 1.4010 0.05670 0.05360 -0.0303 0.0031 1.0000
15.250 1.3835 0.06374 0.06080 -0.0343 0.0031 1.0000
15.500 1.3646 0.07107 0.06826 -0.0383 0.0031 1.0000
15.750 1.3445 0.07865 0.07597 -0.0422 0.0031 1.0000
16.000 1.3225 0.08668 0.08413 -0.0462 0.0032 1.0000
16.250 1.3007 0.09478 0.09234 -0.0501 0.0032 1.0000
16.500 1.2777 0.10335 0.10103 -0.0543 0.0032 1.0000
16.750 1.2549 0.11218 0.10997 -0.0585 0.0033 1.0000
17.000 1.2332 0.12099 0.11889 -0.0628 0.0033 1.0000
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Polar data table (+)
Polar graphs
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