AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 200,000 Max Cl/Cd: 52.99 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47c03-il-200000.txt Download as CSV file: xf-ag47c03-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6238 0.10211 0.09875 0.0319 1.0000 0.0310
-7.000 -0.6198 0.09835 0.09501 0.0298 1.0000 0.0318
-6.750 -0.6157 0.09451 0.09121 0.0271 1.0000 0.0328
-6.500 -0.6109 0.09050 0.08723 0.0235 1.0000 0.0337
-6.250 -0.6004 0.08577 0.08251 0.0169 1.0000 0.0350
-6.000 -0.5788 0.08004 0.07673 0.0045 1.0000 0.0365
-5.750 -0.5565 0.07469 0.07123 -0.0041 1.0000 0.0369
-5.500 -0.5374 0.06974 0.06612 -0.0089 1.0000 0.0371
-5.250 -0.5336 0.06232 0.05878 -0.0102 1.0000 0.0384
-5.000 -0.5199 0.05899 0.05546 -0.0103 1.0000 0.0397
-4.750 -0.5014 0.05530 0.05170 -0.0122 1.0000 0.0416
-4.500 -0.4788 0.05105 0.04731 -0.0151 1.0000 0.0443
-4.250 -0.4402 0.04808 0.04356 -0.0198 1.0000 0.0497
-4.000 -0.4261 0.04095 0.03656 -0.0214 1.0000 0.0519
-3.750 -0.4041 0.03810 0.03363 -0.0219 1.0000 0.0548
-3.500 -0.3741 0.03462 0.02949 -0.0235 1.0000 0.0641
-3.250 -0.3516 0.03141 0.02637 -0.0239 1.0000 0.0672
-3.000 -0.3148 0.02447 0.01837 -0.0231 1.0000 0.0354
-2.750 -0.2868 0.02136 0.01482 -0.0229 1.0000 0.0349
-2.500 -0.2584 0.01891 0.01195 -0.0225 1.0000 0.0350
-2.250 -0.2300 0.01654 0.00922 -0.0219 1.0000 0.0339
-2.000 -0.2019 0.01483 0.00727 -0.0213 1.0000 0.0345
-1.750 -0.1741 0.01362 0.00590 -0.0208 1.0000 0.0367
-1.500 -0.1473 0.01229 0.00462 -0.0204 1.0000 0.0461
-1.250 -0.1200 0.01124 0.00359 -0.0201 1.0000 0.0604
-1.000 -0.0927 0.01012 0.00275 -0.0199 1.0000 0.1182
-0.750 -0.0697 0.00807 0.00241 -0.0200 1.0000 0.5217
-0.500 -0.0406 0.00669 0.00225 -0.0186 1.0000 1.0000
-0.250 -0.0135 0.00668 0.00207 -0.0184 1.0000 1.0000
0.000 0.0136 0.00667 0.00193 -0.0182 1.0000 1.0000
0.250 0.0406 0.00667 0.00184 -0.0180 1.0000 1.0000
0.500 0.0676 0.00668 0.00177 -0.0179 1.0000 1.0000
0.750 0.0944 0.00671 0.00175 -0.0178 1.0000 1.0000
1.000 0.1211 0.00676 0.00178 -0.0179 1.0000 1.0000
1.250 0.1695 0.00683 0.00181 -0.0223 0.9555 1.0000
1.500 0.2099 0.00692 0.00178 -0.0245 0.8933 1.0000
1.750 0.2364 0.00710 0.00176 -0.0235 0.8396 1.0000
2.000 0.2603 0.00734 0.00180 -0.0220 0.7998 1.0000
2.250 0.2849 0.00760 0.00187 -0.0209 0.7673 1.0000
2.500 0.3100 0.00787 0.00199 -0.0200 0.7390 1.0000
2.750 0.3356 0.00815 0.00213 -0.0192 0.7133 1.0000
3.000 0.3617 0.00838 0.00229 -0.0186 0.6870 1.0000
3.250 0.3881 0.00850 0.00238 -0.0181 0.6576 1.0000
3.500 0.4145 0.00860 0.00245 -0.0175 0.6244 1.0000
3.750 0.4407 0.00873 0.00249 -0.0168 0.5833 1.0000
4.000 0.4666 0.00895 0.00256 -0.0162 0.5321 1.0000
4.250 0.4923 0.00929 0.00268 -0.0157 0.4683 1.0000
4.500 0.5176 0.00979 0.00286 -0.0152 0.3899 1.0000
4.750 0.5430 0.01044 0.00319 -0.0149 0.3028 1.0000
5.000 0.5683 0.01126 0.00360 -0.0148 0.2195 1.0000
5.250 0.5939 0.01208 0.00413 -0.0147 0.1681 1.0000
5.500 0.6198 0.01283 0.00476 -0.0145 0.1373 1.0000
5.750 0.6454 0.01364 0.00546 -0.0143 0.1154 1.0000
6.000 0.6713 0.01440 0.00623 -0.0140 0.0997 1.0000
6.250 0.6970 0.01523 0.00707 -0.0138 0.0865 1.0000
6.500 0.7222 0.01620 0.00801 -0.0134 0.0751 1.0000
6.750 0.7481 0.01701 0.00890 -0.0131 0.0662 1.0000
7.000 0.7734 0.01808 0.01013 -0.0127 0.0577 1.0000
7.250 0.7971 0.02004 0.01206 -0.0122 0.0511 1.0000
7.500 0.8232 0.02111 0.01344 -0.0117 0.0469 1.0000
7.750 0.8480 0.02205 0.01446 -0.0114 0.0416 1.0000
8.000 0.8704 0.02513 0.01786 -0.0108 0.0386 1.0000
8.250 0.8940 0.02748 0.02068 -0.0101 0.0368 1.0000
8.500 0.9151 0.03084 0.02460 -0.0095 0.0353 1.0000
8.750 0.9357 0.03326 0.02742 -0.0091 0.0327 1.0000
9.000 0.9552 0.03547 0.02985 -0.0089 0.0307 1.0000
9.250 0.9685 0.04011 0.03499 -0.0087 0.0302 1.0000
9.500 0.9516 0.05432 0.05050 -0.0106 0.0338 1.0000
9.750 0.9400 0.06327 0.05984 -0.0140 0.0360 1.0000
10.000 0.9281 0.07065 0.06740 -0.0182 0.0373 1.0000
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Polar data table (+)
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