AG10 (ag10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.86 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag10-il-1000000.txt Download as CSV file: xf-ag10-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG10
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5174 0.12383 0.12227 0.0252 1.0000 0.0087
-10.500 -0.5168 0.11963 0.11807 0.0248 1.0000 0.0089
-9.250 -0.6453 0.11331 0.11168 0.0361 1.0000 0.0089
-9.000 -0.6396 0.11028 0.10866 0.0353 1.0000 0.0090
-8.750 -0.6344 0.10709 0.10548 0.0340 1.0000 0.0092
-8.500 -0.6295 0.10377 0.10217 0.0325 1.0000 0.0094
-8.250 -0.6249 0.10033 0.09874 0.0308 1.0000 0.0097
-7.250 -0.5982 0.08146 0.07990 0.0129 1.0000 0.0115
-7.000 -0.5830 0.07598 0.07441 0.0067 1.0000 0.0115
-6.750 -0.5656 0.07025 0.06864 0.0004 1.0000 0.0115
-6.500 -0.5502 0.06202 0.06035 -0.0075 1.0000 0.0118
-6.250 -0.5314 0.05871 0.05699 -0.0105 1.0000 0.0120
-6.000 -0.5078 0.01850 0.01485 -0.0305 1.0000 0.0091
-5.750 -0.4814 0.01657 0.01263 -0.0308 1.0000 0.0094
-5.500 -0.4543 0.01538 0.01124 -0.0309 1.0000 0.0098
-5.250 -0.4269 0.01398 0.00959 -0.0309 1.0000 0.0103
-5.000 -0.3992 0.01275 0.00813 -0.0309 1.0000 0.0107
-4.750 -0.3714 0.01177 0.00696 -0.0308 1.0000 0.0110
-4.500 -0.3434 0.01104 0.00610 -0.0307 1.0000 0.0114
-4.250 -0.3156 0.00996 0.00485 -0.0307 1.0000 0.0119
-4.000 -0.2877 0.00943 0.00430 -0.0307 1.0000 0.0129
-3.750 -0.2596 0.00904 0.00386 -0.0306 1.0000 0.0139
-3.500 -0.2315 0.00866 0.00344 -0.0305 1.0000 0.0148
-3.250 -0.2034 0.00806 0.00279 -0.0304 1.0000 0.0164
-3.000 -0.1752 0.00781 0.00253 -0.0303 1.0000 0.0182
-2.750 -0.1471 0.00745 0.00215 -0.0302 1.0000 0.0205
-2.500 -0.1190 0.00724 0.00198 -0.0302 1.0000 0.0234
-2.250 -0.0909 0.00697 0.00170 -0.0301 1.0000 0.0276
-2.000 -0.0629 0.00682 0.00158 -0.0300 1.0000 0.0315
-1.750 -0.0349 0.00658 0.00138 -0.0298 1.0000 0.0399
-1.500 -0.0070 0.00639 0.00124 -0.0297 1.0000 0.0518
-1.250 0.0207 0.00620 0.00114 -0.0296 1.0000 0.0701
-1.000 0.0536 0.00605 0.00107 -0.0306 0.9894 0.0909
-0.750 0.0889 0.00590 0.00102 -0.0321 0.9574 0.1224
-0.500 0.1132 0.00586 0.00100 -0.0309 0.9053 0.1637
-0.250 0.1372 0.00582 0.00097 -0.0298 0.8449 0.2314
0.000 0.1630 0.00573 0.00095 -0.0293 0.7766 0.3475
0.250 0.1845 0.00437 0.00098 -0.0283 0.7084 0.8818
0.500 0.2107 0.00440 0.00088 -0.0275 0.6337 1.0000
0.750 0.2383 0.00470 0.00089 -0.0274 0.5620 1.0000
1.000 0.2661 0.00498 0.00092 -0.0273 0.5001 1.0000
1.250 0.2941 0.00522 0.00095 -0.0273 0.4514 1.0000
1.500 0.3221 0.00543 0.00100 -0.0273 0.4111 1.0000
1.750 0.3501 0.00563 0.00105 -0.0273 0.3765 1.0000
2.000 0.3782 0.00581 0.00111 -0.0272 0.3467 1.0000
2.250 0.4062 0.00600 0.00118 -0.0272 0.3184 1.0000
2.500 0.4342 0.00618 0.00126 -0.0272 0.2918 1.0000
2.750 0.4622 0.00637 0.00135 -0.0272 0.2668 1.0000
3.000 0.4902 0.00658 0.00145 -0.0271 0.2412 1.0000
3.250 0.5181 0.00678 0.00157 -0.0271 0.2166 1.0000
3.500 0.5459 0.00700 0.00170 -0.0271 0.1925 1.0000
3.750 0.5737 0.00725 0.00184 -0.0270 0.1686 1.0000
4.000 0.6014 0.00750 0.00200 -0.0270 0.1455 1.0000
4.250 0.6290 0.00777 0.00218 -0.0269 0.1238 1.0000
4.500 0.6565 0.00808 0.00238 -0.0269 0.1019 1.0000
4.750 0.6840 0.00836 0.00260 -0.0268 0.0834 1.0000
5.000 0.7114 0.00869 0.00284 -0.0268 0.0660 1.0000
5.250 0.7387 0.00903 0.00312 -0.0267 0.0503 1.0000
5.500 0.7659 0.00942 0.00343 -0.0266 0.0363 1.0000
5.750 0.7929 0.00984 0.00380 -0.0265 0.0255 1.0000
6.000 0.8199 0.01028 0.00423 -0.0264 0.0190 1.0000
6.250 0.8468 0.01079 0.00474 -0.0262 0.0151 1.0000
6.500 0.8737 0.01120 0.00519 -0.0260 0.0132 1.0000
6.750 0.9001 0.01183 0.00588 -0.0258 0.0115 1.0000
7.000 0.9268 0.01224 0.00634 -0.0256 0.0105 1.0000
7.250 0.9531 0.01277 0.00691 -0.0254 0.0097 1.0000
7.500 0.9777 0.01390 0.00818 -0.0250 0.0089 1.0000
7.750 1.0036 0.01446 0.00882 -0.0247 0.0086 1.0000
8.000 1.0290 0.01516 0.00961 -0.0244 0.0083 1.0000
8.250 1.0540 0.01593 0.01048 -0.0240 0.0080 1.0000
8.500 1.0785 0.01677 0.01142 -0.0236 0.0077 1.0000
8.750 1.1027 0.01762 0.01239 -0.0232 0.0074 1.0000
9.000 1.1265 0.01853 0.01339 -0.0228 0.0072 1.0000
9.250 1.1490 0.01970 0.01467 -0.0223 0.0069 1.0000
9.500 1.1669 0.02204 0.01724 -0.0214 0.0066 1.0000
9.750 1.1821 0.02498 0.02052 -0.0204 0.0064 1.0000
10.000 1.2009 0.02675 0.02253 -0.0196 0.0064 1.0000
10.250 1.2164 0.02908 0.02513 -0.0188 0.0063 1.0000
10.500 1.2278 0.03203 0.02840 -0.0178 0.0063 1.0000
10.750 1.2341 0.03554 0.03225 -0.0168 0.0063 1.0000
11.000 1.2365 0.03922 0.03626 -0.0159 0.0063 1.0000
11.250 1.2307 0.04355 0.04090 -0.0153 0.0063 1.0000
11.500 1.2157 0.04786 0.04545 -0.0147 0.0063 1.0000
11.750 1.1914 0.05517 0.05299 -0.0206 0.0063 1.0000
12.250 1.1425 0.07981 0.07795 -0.0429 0.0065 1.0000
12.500 1.1316 0.08749 0.08569 -0.0477 0.0065 1.0000
12.750 1.1139 0.09651 0.09478 -0.0529 0.0066 1.0000
13.000 1.0984 0.10494 0.10326 -0.0573 0.0066 1.0000
13.250 0.9578 0.09401 0.09226 -0.0354 0.0067 1.0000
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Polar data table (+)
Polar graphs
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