AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 200,000 Max Cl/Cd: 62.45 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45c03-il-200000.txt Download as CSV file: xf-ag45c03-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -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 -0.5587 0.09991 0.09662 0.0216 1.0000 0.0341
-7.000 -0.5553 0.09603 0.09278 0.0183 1.0000 0.0352
-6.750 -0.5522 0.09196 0.08877 0.0124 1.0000 0.0364
-6.500 -0.5408 0.08677 0.08358 0.0017 1.0000 0.0370
-6.250 -0.5254 0.08129 0.07806 -0.0065 1.0000 0.0373
-6.000 -0.5141 0.07458 0.07129 -0.0128 1.0000 0.0376
-5.750 -0.5125 0.06997 0.06677 -0.0105 1.0000 0.0389
-5.500 -0.5003 0.06690 0.06368 -0.0106 1.0000 0.0404
-5.250 -0.4841 0.06291 0.05965 -0.0135 1.0000 0.0423
-5.000 -0.4640 0.05799 0.05463 -0.0182 1.0000 0.0453
-4.750 -0.4338 0.04999 0.04597 -0.0278 1.0000 0.0503
-4.500 -0.4207 0.04759 0.04387 -0.0263 1.0000 0.0533
-4.000 -0.3728 0.03929 0.03504 -0.0307 1.0000 0.0652
-3.750 -0.3500 0.03669 0.03238 -0.0311 1.0000 0.0691
-3.500 -0.3236 0.03309 0.02837 -0.0325 1.0000 0.0787
-3.250 -0.2883 0.02420 0.01833 -0.0324 1.0000 0.0404
-3.000 -0.2592 0.02064 0.01426 -0.0318 1.0000 0.0326
-2.750 -0.2305 0.01781 0.01087 -0.0312 1.0000 0.0303
-2.500 -0.2026 0.01601 0.00882 -0.0307 1.0000 0.0304
-2.250 -0.1751 0.01465 0.00733 -0.0302 1.0000 0.0321
-2.000 -0.1475 0.01402 0.00661 -0.0298 1.0000 0.0371
-1.750 -0.1209 0.01245 0.00510 -0.0295 1.0000 0.0432
-1.500 -0.0937 0.01155 0.00423 -0.0292 1.0000 0.0580
-1.250 -0.0664 0.01028 0.00341 -0.0293 1.0000 0.1382
-1.000 -0.0359 0.00918 0.00317 -0.0308 0.9918 0.3355
-0.750 -0.0015 0.00754 0.00314 -0.0320 0.9439 0.7548
-0.500 0.0463 0.00712 0.00286 -0.0344 0.8913 1.0000
-0.250 0.0742 0.00726 0.00265 -0.0338 0.8423 1.0000
0.000 0.0994 0.00744 0.00252 -0.0328 0.8086 1.0000
0.250 0.1250 0.00765 0.00244 -0.0320 0.7833 1.0000
0.500 0.1511 0.00785 0.00240 -0.0314 0.7618 1.0000
0.750 0.1774 0.00808 0.00239 -0.0308 0.7435 1.0000
1.000 0.2041 0.00829 0.00242 -0.0304 0.7259 1.0000
1.250 0.2309 0.00852 0.00248 -0.0300 0.7094 1.0000
1.500 0.2579 0.00873 0.00255 -0.0296 0.6930 1.0000
1.750 0.2852 0.00887 0.00260 -0.0293 0.6766 1.0000
2.000 0.3125 0.00895 0.00261 -0.0291 0.6597 1.0000
2.250 0.3399 0.00903 0.00262 -0.0288 0.6429 1.0000
2.500 0.3671 0.00911 0.00261 -0.0284 0.6259 1.0000
2.750 0.3943 0.00921 0.00262 -0.0281 0.6087 1.0000
3.000 0.4215 0.00932 0.00265 -0.0278 0.5901 1.0000
3.250 0.4488 0.00944 0.00272 -0.0275 0.5708 1.0000
3.500 0.4758 0.00960 0.00278 -0.0272 0.5520 1.0000
3.750 0.5031 0.00975 0.00288 -0.0270 0.5313 1.0000
4.000 0.5301 0.00993 0.00298 -0.0267 0.5112 1.0000
4.250 0.5572 0.01012 0.00314 -0.0264 0.4902 1.0000
4.500 0.5842 0.01033 0.00329 -0.0262 0.4687 1.0000
4.750 0.6113 0.01055 0.00346 -0.0260 0.4463 1.0000
5.000 0.6381 0.01080 0.00364 -0.0257 0.4240 1.0000
5.250 0.6650 0.01103 0.00385 -0.0255 0.3996 1.0000
5.500 0.6918 0.01130 0.00412 -0.0253 0.3745 1.0000
5.750 0.7184 0.01161 0.00438 -0.0251 0.3486 1.0000
6.000 0.7449 0.01196 0.00468 -0.0249 0.3218 1.0000
6.250 0.7712 0.01235 0.00504 -0.0247 0.2943 1.0000
6.500 0.7973 0.01279 0.00542 -0.0246 0.2667 1.0000
6.750 0.8233 0.01327 0.00585 -0.0244 0.2392 1.0000
7.000 0.8489 0.01382 0.00633 -0.0242 0.2131 1.0000
7.250 0.8742 0.01443 0.00687 -0.0241 0.1883 1.0000
7.500 0.8997 0.01502 0.00750 -0.0239 0.1647 1.0000
7.750 0.9247 0.01572 0.00816 -0.0237 0.1429 1.0000
8.000 0.9492 0.01648 0.00889 -0.0235 0.1226 1.0000
8.250 0.9735 0.01731 0.00973 -0.0232 0.1031 1.0000
8.500 0.9974 0.01821 0.01064 -0.0229 0.0853 1.0000
8.750 1.0196 0.01944 0.01185 -0.0225 0.0699 1.0000
9.000 1.0411 0.02082 0.01324 -0.0220 0.0573 1.0000
9.250 1.0642 0.02184 0.01440 -0.0215 0.0482 1.0000
9.500 1.0844 0.02355 0.01625 -0.0206 0.0416 1.0000
9.750 1.1031 0.02539 0.01808 -0.0200 0.0357 1.0000
10.000 1.1230 0.02731 0.02026 -0.0190 0.0326 1.0000
10.250 1.1424 0.02916 0.02232 -0.0182 0.0297 1.0000
10.500 1.1595 0.03114 0.02440 -0.0176 0.0268 1.0000
10.750 1.1717 0.03469 0.02831 -0.0165 0.0249 1.0000
11.000 1.1852 0.03741 0.03142 -0.0155 0.0238 1.0000
11.250 1.1941 0.04074 0.03517 -0.0145 0.0230 1.0000
11.500 1.1974 0.04453 0.03937 -0.0135 0.0224 1.0000
11.750 1.1943 0.04865 0.04388 -0.0127 0.0221 1.0000
12.000 1.1839 0.05270 0.04827 -0.0119 0.0220 1.0000
12.250 1.1680 0.05710 0.05294 -0.0127 0.0219 1.0000
12.500 1.1496 0.06283 0.05891 -0.0162 0.0221 1.0000
12.750 1.1291 0.06969 0.06601 -0.0212 0.0224 1.0000
13.000 1.1068 0.07767 0.07418 -0.0272 0.0228 1.0000
13.250 1.0834 0.08660 0.08326 -0.0339 0.0232 1.0000
13.500 1.0582 0.09662 0.09341 -0.0411 0.0237 1.0000
13.750 1.0307 0.10781 0.10467 -0.0485 0.0243 1.0000
14.000 1.0019 0.11985 0.11670 -0.0554 0.0250 1.0000
14.250 0.7834 0.12921 0.12616 -0.0429 0.0338 1.0000
14.500 0.7630 0.13485 0.13179 -0.0446 0.0345 1.0000
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Polar data table (+)
Polar graphs
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