AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 100,000 Max Cl/Cd: 42.29 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47c03-il-100000.txt Download as CSV file: xf-ag47c03-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG47c -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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6392 0.12137 0.11655 0.0353 1.0000 0.0614
-8.000 -0.6416 0.11896 0.11420 0.0302 1.0000 0.0622
-7.750 -0.6436 0.11627 0.11157 0.0247 1.0000 0.0626
-7.500 -0.6430 0.11291 0.10827 0.0179 1.0000 0.0628
-7.250 -0.6233 0.10532 0.10064 0.0290 1.0000 0.0659
-7.000 -0.6166 0.10166 0.09700 0.0283 1.0000 0.0682
-6.750 -0.6121 0.09804 0.09342 0.0262 1.0000 0.0707
-6.500 -0.6082 0.09429 0.08973 0.0215 1.0000 0.0735
-6.250 -0.5961 0.08973 0.08510 0.0037 1.0000 0.0760
-6.000 -0.5883 0.08404 0.07947 0.0043 1.0000 0.0773
-5.750 -0.5789 0.08051 0.07599 0.0085 1.0000 0.0801
-5.500 -0.5652 0.07643 0.07190 0.0056 1.0000 0.0845
-5.250 -0.5425 0.07032 0.06554 -0.0081 1.0000 0.0907
-5.000 -0.5319 0.06668 0.06204 -0.0045 1.0000 0.0938
-4.750 -0.5058 0.06183 0.05681 -0.0137 1.0000 0.1043
-4.500 -0.4937 0.05821 0.05340 -0.0105 1.0000 0.1089
-4.250 -0.4727 0.05414 0.04917 -0.0135 1.0000 0.1216
-4.000 -0.4519 0.05057 0.04551 -0.0151 1.0000 0.1365
-3.750 -0.4297 0.04707 0.04190 -0.0167 1.0000 0.1523
-3.500 -0.4058 0.04360 0.03823 -0.0188 1.0000 0.1754
-3.000 -0.3229 0.03011 0.02280 -0.0242 1.0000 0.0741
-2.750 -0.2913 0.02607 0.01800 -0.0239 1.0000 0.0613
-2.500 -0.2628 0.02304 0.01458 -0.0236 1.0000 0.0590
-2.250 -0.2335 0.02107 0.01213 -0.0231 1.0000 0.0616
-2.000 -0.2056 0.01884 0.00967 -0.0227 1.0000 0.0663
-1.750 -0.1775 0.01718 0.00789 -0.0220 1.0000 0.0722
-1.500 -0.1501 0.01583 0.00651 -0.0215 1.0000 0.0884
-1.250 -0.1236 0.01434 0.00519 -0.0208 1.0000 0.1175
-1.000 -0.0998 0.01167 0.00396 -0.0204 1.0000 0.3452
-0.750 -0.0687 0.00951 0.00345 -0.0188 1.0000 1.0000
-0.500 -0.0417 0.00947 0.00308 -0.0186 1.0000 1.0000
-0.250 -0.0149 0.00945 0.00283 -0.0183 1.0000 1.0000
0.000 0.0118 0.00944 0.00264 -0.0181 1.0000 1.0000
0.250 0.0384 0.00944 0.00251 -0.0179 1.0000 1.0000
0.500 0.0650 0.00945 0.00240 -0.0177 1.0000 1.0000
0.750 0.0914 0.00948 0.00236 -0.0176 1.0000 1.0000
1.000 0.1176 0.00952 0.00236 -0.0175 1.0000 1.0000
1.250 0.1433 0.00959 0.00243 -0.0174 1.0000 1.0000
1.500 0.1681 0.00971 0.00256 -0.0175 1.0000 1.0000
1.750 0.1913 0.00993 0.00281 -0.0176 1.0000 1.0000
2.000 0.2306 0.01021 0.00312 -0.0211 0.9866 1.0000
2.250 0.2889 0.01033 0.00330 -0.0273 0.9494 1.0000
2.500 0.3335 0.01042 0.00343 -0.0300 0.9045 1.0000
2.750 0.3633 0.01058 0.00353 -0.0292 0.8594 1.0000
3.000 0.3863 0.01083 0.00367 -0.0271 0.8172 1.0000
3.250 0.4084 0.01114 0.00386 -0.0249 0.7771 1.0000
3.500 0.4308 0.01150 0.00414 -0.0229 0.7384 1.0000
3.750 0.4535 0.01192 0.00444 -0.0210 0.7006 1.0000
4.000 0.4772 0.01217 0.00467 -0.0196 0.6568 1.0000
4.250 0.5011 0.01229 0.00476 -0.0181 0.6062 1.0000
4.500 0.5245 0.01248 0.00479 -0.0165 0.5420 1.0000
4.750 0.5476 0.01295 0.00496 -0.0151 0.4505 1.0000
5.000 0.5699 0.01394 0.00534 -0.0140 0.3354 1.0000
5.250 0.5932 0.01523 0.00608 -0.0134 0.2484 1.0000
5.500 0.6175 0.01646 0.00698 -0.0129 0.2006 1.0000
5.750 0.6422 0.01767 0.00797 -0.0124 0.1693 1.0000
6.000 0.6677 0.01891 0.00924 -0.0119 0.1471 1.0000
6.250 0.6927 0.02025 0.01046 -0.0115 0.1280 1.0000
6.500 0.7185 0.02186 0.01211 -0.0110 0.1146 1.0000
6.750 0.7438 0.02347 0.01380 -0.0106 0.1016 1.0000
7.000 0.7694 0.02504 0.01558 -0.0101 0.0910 1.0000
7.250 0.7949 0.02761 0.01867 -0.0094 0.0843 1.0000
7.500 0.8181 0.02991 0.02100 -0.0092 0.0757 1.0000
7.750 0.8417 0.03296 0.02486 -0.0085 0.0718 1.0000
8.000 0.8626 0.03711 0.02969 -0.0080 0.0700 1.0000
8.250 0.8823 0.04052 0.03349 -0.0078 0.0667 1.0000
8.500 0.8978 0.04478 0.03795 -0.0080 0.0627 1.0000
8.750 0.9102 0.05060 0.04427 -0.0082 0.0630 1.0000
9.000 0.8944 0.06797 0.06315 -0.0150 0.0922 1.0000
9.250 0.8530 0.09183 0.08733 -0.0420 0.1472 1.0000
9.500 0.8581 0.09618 0.09167 -0.0414 0.1414 1.0000
9.750 0.8420 0.10206 0.09745 -0.0489 0.1372 1.0000
10.000 0.8737 0.10455 0.10006 -0.0390 0.1291 1.0000
10.250 0.8415 0.11095 0.10629 -0.0518 0.1263 1.0000
10.500 0.8389 0.11530 0.11062 -0.0543 0.1208 1.0000
10.750 0.7367 0.11102 0.10660 -0.0329 0.1294 1.0000
11.000 0.7156 0.11613 0.11164 -0.0372 0.1289 1.0000
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Polar data table (+)
Polar graphs
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