AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.65 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-1000000.txt Download as CSV file: xf-ag46ct02r-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4815 0.09148 0.09001 0.0137 1.0000 0.0083
-8.500 -0.4815 0.08722 0.08576 0.0124 1.0000 0.0085
-8.250 -0.4819 0.08285 0.08140 0.0111 1.0000 0.0088
-4.250 -0.3122 0.01121 0.00643 -0.0290 1.0000 0.0071
-4.000 -0.2857 0.01025 0.00537 -0.0286 1.0000 0.0074
-3.750 -0.2592 0.00970 0.00477 -0.0282 1.0000 0.0082
-3.500 -0.2326 0.00916 0.00417 -0.0277 1.0000 0.0090
-3.250 -0.2061 0.00868 0.00364 -0.0273 1.0000 0.0096
-3.000 -0.1796 0.00830 0.00322 -0.0269 1.0000 0.0099
-2.750 -0.1475 0.00750 0.00232 -0.0277 0.9966 0.0114
-2.500 -0.1090 0.00713 0.00192 -0.0299 0.9834 0.0137
-2.250 -0.0712 0.00673 0.00146 -0.0318 0.9507 0.0219
-2.000 -0.0464 0.00665 0.00121 -0.0306 0.8539 0.0459
-1.750 -0.0223 0.00667 0.00107 -0.0297 0.7687 0.0925
-1.500 0.0043 0.00649 0.00098 -0.0295 0.7356 0.1626
-1.250 0.0315 0.00627 0.00090 -0.0294 0.7166 0.2431
-1.000 0.0587 0.00596 0.00086 -0.0294 0.7032 0.3527
-0.750 0.0857 0.00547 0.00082 -0.0294 0.6887 0.5141
-0.500 0.1111 0.00480 0.00081 -0.0290 0.6720 0.7367
-0.250 0.1330 0.00439 0.00081 -0.0273 0.6532 0.8869
0.000 0.1664 0.00426 0.00076 -0.0281 0.6305 1.0000
0.250 0.1941 0.00436 0.00073 -0.0279 0.6077 1.0000
0.500 0.2218 0.00446 0.00071 -0.0278 0.5838 1.0000
0.750 0.2496 0.00457 0.00071 -0.0276 0.5607 1.0000
1.000 0.2773 0.00469 0.00072 -0.0275 0.5377 1.0000
1.250 0.3051 0.00481 0.00073 -0.0274 0.5135 1.0000
1.500 0.3329 0.00493 0.00076 -0.0273 0.4890 1.0000
1.750 0.3606 0.00508 0.00080 -0.0272 0.4613 1.0000
2.000 0.3883 0.00523 0.00084 -0.0271 0.4352 1.0000
2.250 0.4159 0.00541 0.00090 -0.0270 0.4047 1.0000
2.500 0.4435 0.00560 0.00099 -0.0269 0.3759 1.0000
2.750 0.4709 0.00581 0.00107 -0.0269 0.3450 1.0000
3.000 0.4984 0.00603 0.00117 -0.0268 0.3149 1.0000
3.250 0.5259 0.00625 0.00129 -0.0267 0.2862 1.0000
3.500 0.5532 0.00650 0.00141 -0.0266 0.2543 1.0000
3.750 0.5806 0.00675 0.00157 -0.0266 0.2271 1.0000
4.000 0.6078 0.00703 0.00173 -0.0265 0.1977 1.0000
4.250 0.6350 0.00730 0.00191 -0.0264 0.1744 1.0000
4.750 0.6894 0.00785 0.00231 -0.0262 0.1325 1.0000
5.000 0.7165 0.00812 0.00252 -0.0261 0.1164 1.0000
5.250 0.7436 0.00842 0.00275 -0.0260 0.1007 1.0000
5.500 0.7706 0.00870 0.00299 -0.0259 0.0881 1.0000
5.750 0.7975 0.00900 0.00326 -0.0258 0.0756 1.0000
6.000 0.8244 0.00930 0.00354 -0.0257 0.0650 1.0000
6.250 0.8512 0.00962 0.00383 -0.0256 0.0546 1.0000
6.500 0.8778 0.00997 0.00416 -0.0254 0.0456 1.0000
6.750 0.9041 0.01038 0.00454 -0.0252 0.0363 1.0000
7.000 0.9305 0.01076 0.00492 -0.0251 0.0301 1.0000
7.250 0.9568 0.01116 0.00535 -0.0249 0.0250 1.0000
7.500 0.9822 0.01180 0.00598 -0.0246 0.0187 1.0000
7.750 1.0085 0.01213 0.00636 -0.0244 0.0167 1.0000
8.000 1.0340 0.01270 0.00693 -0.0241 0.0136 1.0000
8.250 1.0588 0.01345 0.00779 -0.0237 0.0116 1.0000
8.500 1.0843 0.01392 0.00835 -0.0234 0.0105 1.0000
8.750 1.1093 0.01450 0.00898 -0.0232 0.0093 1.0000
9.000 1.1315 0.01577 0.01040 -0.0225 0.0078 1.0000
9.250 1.1555 0.01649 0.01122 -0.0221 0.0073 1.0000
9.500 1.1799 0.01709 0.01191 -0.0218 0.0068 1.0000
9.750 1.2034 0.01785 0.01276 -0.0214 0.0063 1.0000
10.000 1.2265 0.01864 0.01364 -0.0210 0.0058 1.0000
10.250 1.2484 0.01961 0.01473 -0.0205 0.0054 1.0000
10.500 1.2650 0.02160 0.01694 -0.0195 0.0049 1.0000
10.750 1.2770 0.02430 0.01996 -0.0183 0.0046 1.0000
11.000 1.2972 0.02533 0.02112 -0.0177 0.0045 1.0000
11.250 1.3152 0.02662 0.02257 -0.0170 0.0043 1.0000
11.500 1.3311 0.02816 0.02427 -0.0163 0.0041 1.0000
11.750 1.3448 0.02988 0.02617 -0.0154 0.0039 1.0000
12.000 1.3575 0.03156 0.02802 -0.0146 0.0037 1.0000
12.250 1.3683 0.03330 0.02990 -0.0138 0.0035 1.0000
12.500 1.3780 0.03498 0.03171 -0.0131 0.0034 1.0000
12.750 1.3794 0.03707 0.03394 -0.0119 0.0032 1.0000
13.000 1.3763 0.03969 0.03670 -0.0117 0.0032 1.0000
13.250 1.3660 0.04459 0.04179 -0.0150 0.0031 1.0000
13.500 1.3542 0.05105 0.04843 -0.0204 0.0031 1.0000
13.750 1.3317 0.06018 0.05777 -0.0275 0.0031 1.0000
14.000 1.2968 0.07196 0.06976 -0.0354 0.0032 1.0000
14.250 1.2468 0.08659 0.08462 -0.0438 0.0034 1.0000
14.500 1.1967 0.10126 0.09945 -0.0515 0.0037 1.0000
14.750 1.1499 0.11558 0.11390 -0.0587 0.0040 1.0000
15.000 1.1119 0.12883 0.12725 -0.0652 0.0042 1.0000
15.250 1.0734 0.14334 0.14184 -0.0724 0.0044 1.0000
15.500 1.0144 0.16550 0.16407 -0.0831 0.0047 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG46ct -02f rot. (ag46ct02r-il)