AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 500,000 Max Cl/Cd: 66.57 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47c03-il-500000-n5.txt Download as CSV file: xf-ag47c03-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6537 0.11616 0.11395 0.0404 1.0000 0.0068
-8.250 -0.6551 0.11100 0.10881 0.0385 1.0000 0.0069
-8.000 -0.6520 0.10734 0.10517 0.0373 1.0000 0.0071
-7.750 -0.6470 0.10423 0.10207 0.0363 1.0000 0.0074
-7.500 -0.6427 0.10078 0.09864 0.0347 1.0000 0.0076
-7.250 -0.6389 0.09706 0.09491 0.0327 1.0000 0.0077
-7.000 -0.6350 0.09334 0.09121 0.0304 1.0000 0.0080
-6.250 -0.6023 0.07932 0.07722 0.0136 1.0000 0.0107
-6.000 -0.5870 0.07374 0.07162 0.0072 1.0000 0.0107
-5.750 -0.5700 0.06797 0.06580 0.0012 1.0000 0.0107
-5.500 -0.5512 0.06210 0.05985 -0.0043 1.0000 0.0107
-5.000 -0.5161 0.04510 0.04245 -0.0155 1.0000 0.0065
-4.750 -0.4928 0.03871 0.03579 -0.0187 1.0000 0.0062
-4.500 -0.4682 0.03211 0.02881 -0.0207 1.0000 0.0060
-4.250 -0.4428 0.02472 0.02082 -0.0218 1.0000 0.0057
-4.000 -0.4168 0.01838 0.01366 -0.0219 1.0000 0.0056
-3.750 -0.3901 0.01535 0.01008 -0.0216 1.0000 0.0057
-3.500 -0.3630 0.01356 0.00795 -0.0213 1.0000 0.0060
-3.250 -0.3359 0.01235 0.00652 -0.0210 1.0000 0.0064
-3.000 -0.3087 0.01156 0.00557 -0.0207 1.0000 0.0068
-2.750 -0.2818 0.01051 0.00440 -0.0205 1.0000 0.0075
-2.500 -0.2545 0.01003 0.00388 -0.0203 1.0000 0.0082
-2.250 -0.2272 0.00972 0.00357 -0.0201 1.0000 0.0096
-2.000 -0.1997 0.00929 0.00309 -0.0199 1.0000 0.0105
-1.750 -0.1674 0.00869 0.00240 -0.0208 0.9730 0.0125
-1.500 -0.1328 0.00847 0.00202 -0.0219 0.8769 0.0161
-1.250 -0.1104 0.00855 0.00174 -0.0202 0.7787 0.0234
-1.000 -0.0840 0.00847 0.00154 -0.0198 0.7474 0.0371
-0.750 -0.0568 0.00831 0.00139 -0.0196 0.7307 0.0656
-0.500 -0.0295 0.00812 0.00126 -0.0194 0.7184 0.1071
-0.250 -0.0022 0.00789 0.00116 -0.0194 0.7086 0.1704
0.000 0.0252 0.00756 0.00109 -0.0194 0.6989 0.2643
0.250 0.0524 0.00708 0.00104 -0.0195 0.6883 0.4075
0.500 0.0788 0.00648 0.00100 -0.0194 0.6758 0.5908
0.750 0.1031 0.00591 0.00099 -0.0185 0.6610 0.7625
1.000 0.1254 0.00545 0.00096 -0.0165 0.6430 0.9484
1.250 0.1597 0.00548 0.00089 -0.0177 0.6177 1.0000
1.500 0.1872 0.00559 0.00084 -0.0175 0.5888 1.0000
1.750 0.2146 0.00573 0.00082 -0.0173 0.5548 1.0000
2.000 0.2420 0.00590 0.00082 -0.0172 0.5164 1.0000
2.250 0.2693 0.00610 0.00084 -0.0170 0.4755 1.0000
2.500 0.2967 0.00633 0.00089 -0.0169 0.4317 1.0000
2.750 0.3240 0.00657 0.00096 -0.0168 0.3878 1.0000
3.000 0.3513 0.00685 0.00104 -0.0168 0.3396 1.0000
3.250 0.3786 0.00713 0.00115 -0.0167 0.2979 1.0000
3.500 0.4058 0.00745 0.00130 -0.0167 0.2511 1.0000
3.750 0.4330 0.00776 0.00144 -0.0166 0.2108 1.0000
4.000 0.4603 0.00806 0.00161 -0.0166 0.1769 1.0000
4.250 0.4875 0.00839 0.00179 -0.0166 0.1448 1.0000
4.500 0.5148 0.00866 0.00198 -0.0165 0.1236 1.0000
4.750 0.5421 0.00894 0.00222 -0.0164 0.1059 1.0000
5.000 0.5692 0.00924 0.00245 -0.0164 0.0893 1.0000
5.250 0.5965 0.00951 0.00269 -0.0163 0.0775 1.0000
5.500 0.6236 0.00978 0.00295 -0.0162 0.0676 1.0000
5.750 0.6507 0.01007 0.00325 -0.0161 0.0583 1.0000
6.000 0.6777 0.01040 0.00356 -0.0160 0.0505 1.0000
6.250 0.7047 0.01070 0.00387 -0.0159 0.0438 1.0000
6.500 0.7316 0.01105 0.00423 -0.0158 0.0376 1.0000
6.750 0.7583 0.01140 0.00462 -0.0157 0.0327 1.0000
7.000 0.7849 0.01182 0.00507 -0.0156 0.0277 1.0000
7.250 0.8115 0.01219 0.00548 -0.0155 0.0240 1.0000
7.500 0.8376 0.01274 0.00606 -0.0153 0.0201 1.0000
7.750 0.8639 0.01322 0.00662 -0.0151 0.0184 1.0000
8.000 0.8899 0.01372 0.00721 -0.0150 0.0166 1.0000
8.250 0.9157 0.01427 0.00784 -0.0148 0.0147 1.0000
8.500 0.9404 0.01520 0.00886 -0.0145 0.0126 1.0000
8.750 0.9659 0.01580 0.00959 -0.0143 0.0120 1.0000
9.000 0.9909 0.01654 0.01046 -0.0140 0.0112 1.0000
9.250 1.0155 0.01733 0.01138 -0.0138 0.0104 1.0000
9.500 1.0402 0.01805 0.01221 -0.0136 0.0096 1.0000
9.750 1.0642 0.01889 0.01317 -0.0134 0.0087 1.0000
10.000 1.0858 0.02042 0.01490 -0.0130 0.0079 1.0000
10.250 1.1088 0.02146 0.01612 -0.0127 0.0075 1.0000
10.500 1.1309 0.02269 0.01757 -0.0123 0.0071 1.0000
10.750 1.1522 0.02405 0.01914 -0.0120 0.0066 1.0000
11.000 1.1734 0.02529 0.02056 -0.0117 0.0062 1.0000
11.250 1.1950 0.02630 0.02171 -0.0115 0.0057 1.0000
11.500 1.2155 0.02744 0.02297 -0.0113 0.0053 1.0000
11.750 1.2282 0.03018 0.02599 -0.0109 0.0048 1.0000
12.000 1.2438 0.03213 0.02825 -0.0106 0.0046 1.0000
12.250 1.2552 0.03467 0.03109 -0.0104 0.0045 1.0000
12.500 1.2619 0.03775 0.03449 -0.0103 0.0043 1.0000
12.750 1.2620 0.04149 0.03854 -0.0107 0.0041 1.0000
13.000 1.2516 0.04595 0.04328 -0.0120 0.0041 1.0000
13.250 1.2309 0.05417 0.05176 -0.0203 0.0041 1.0000
13.500 1.2019 0.06750 0.06532 -0.0326 0.0043 1.0000
13.750 1.1582 0.08358 0.08148 -0.0429 0.0045 1.0000
14.000 1.1100 0.09867 0.09661 -0.0510 0.0048 1.0000
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Polar data table (+)
Polar graphs
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