AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 60.56 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-200000.txt Download as CSV file: xf-ag45ct02r-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG45ct -02f
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5545 0.09571 0.09239 0.0151 1.0000 0.0354
-7.750 -0.5511 0.09182 0.08853 0.0124 1.0000 0.0365
-7.500 -0.5478 0.08771 0.08447 0.0085 1.0000 0.0377
-7.250 -0.5374 0.08221 0.07899 -0.0017 1.0000 0.0393
-7.000 -0.5184 0.07574 0.07241 -0.0143 1.0000 0.0401
-6.750 -0.5031 0.07041 0.06691 -0.0201 1.0000 0.0403
-6.500 -0.5007 0.06345 0.06004 -0.0210 1.0000 0.0416
-6.250 -0.4885 0.06058 0.05720 -0.0205 1.0000 0.0429
-6.000 -0.4723 0.05705 0.05359 -0.0222 1.0000 0.0449
-5.750 -0.4526 0.05259 0.04900 -0.0254 1.0000 0.0480
-5.500 -0.4267 0.04573 0.04145 -0.0315 1.0000 0.0537
-5.250 -0.4095 0.04235 0.03822 -0.0314 1.0000 0.0557
-5.000 -0.3883 0.03966 0.03544 -0.0318 1.0000 0.0600
-4.750 -0.3653 0.03602 0.03149 -0.0331 1.0000 0.0696
-4.500 -0.3414 0.03327 0.02837 -0.0337 1.0000 0.0815
-4.250 -0.3080 0.02470 0.01856 -0.0327 1.0000 0.0418
-4.000 -0.2816 0.02117 0.01472 -0.0320 1.0000 0.0346
-3.750 -0.2535 0.01815 0.01106 -0.0309 1.0000 0.0309
-3.500 -0.2267 0.01641 0.00905 -0.0302 1.0000 0.0307
-3.250 -0.2005 0.01488 0.00742 -0.0295 1.0000 0.0320
-3.000 -0.1745 0.01378 0.00629 -0.0289 1.0000 0.0351
-2.750 -0.1485 0.01289 0.00535 -0.0283 1.0000 0.0417
-2.500 -0.1225 0.01192 0.00440 -0.0277 1.0000 0.0521
-2.250 -0.0965 0.01073 0.00346 -0.0274 1.0000 0.0994
-2.000 -0.0714 0.00938 0.00310 -0.0276 1.0000 0.3114
-1.750 -0.0491 0.00815 0.00304 -0.0270 1.0000 0.6007
-1.500 -0.0172 0.00715 0.00301 -0.0261 1.0000 0.9901
-1.250 0.0136 0.00719 0.00288 -0.0272 0.9961 1.0000
-1.000 0.0639 0.00721 0.00270 -0.0319 0.9711 1.0000
-0.750 0.1092 0.00721 0.00254 -0.0353 0.9376 1.0000
-0.500 0.1466 0.00723 0.00237 -0.0369 0.8976 1.0000
-0.250 0.1749 0.00732 0.00226 -0.0364 0.8582 1.0000
0.000 0.2002 0.00746 0.00219 -0.0353 0.8247 1.0000
0.250 0.2254 0.00764 0.00216 -0.0344 0.7964 1.0000
0.750 0.2766 0.00803 0.00219 -0.0328 0.7484 1.0000
1.000 0.3024 0.00825 0.00224 -0.0321 0.7274 1.0000
1.250 0.3286 0.00847 0.00232 -0.0315 0.7068 1.0000
1.500 0.3550 0.00865 0.00242 -0.0310 0.6851 1.0000
1.750 0.3814 0.00879 0.00247 -0.0305 0.6637 1.0000
2.000 0.4080 0.00889 0.00251 -0.0300 0.6402 1.0000
2.250 0.4345 0.00902 0.00255 -0.0295 0.6162 1.0000
2.500 0.4609 0.00917 0.00261 -0.0290 0.5911 1.0000
2.750 0.4873 0.00935 0.00268 -0.0285 0.5646 1.0000
3.000 0.5136 0.00955 0.00278 -0.0280 0.5371 1.0000
3.250 0.5400 0.00977 0.00291 -0.0276 0.5091 1.0000
3.500 0.5663 0.01002 0.00308 -0.0272 0.4807 1.0000
3.750 0.5926 0.01030 0.00326 -0.0268 0.4525 1.0000
4.000 0.6189 0.01059 0.00347 -0.0265 0.4245 1.0000
4.250 0.6451 0.01090 0.00370 -0.0261 0.3966 1.0000
4.500 0.6713 0.01123 0.00399 -0.0258 0.3689 1.0000
4.750 0.6973 0.01158 0.00428 -0.0255 0.3411 1.0000
5.000 0.7233 0.01196 0.00460 -0.0252 0.3134 1.0000
5.250 0.7491 0.01237 0.00495 -0.0249 0.2856 1.0000
5.500 0.7748 0.01281 0.00536 -0.0246 0.2577 1.0000
5.750 0.8003 0.01329 0.00579 -0.0243 0.2300 1.0000
6.000 0.8257 0.01382 0.00626 -0.0240 0.2029 1.0000
6.250 0.8508 0.01439 0.00679 -0.0237 0.1772 1.0000
6.500 0.8757 0.01501 0.00739 -0.0234 0.1528 1.0000
6.750 0.9001 0.01575 0.00810 -0.0231 0.1306 1.0000
7.000 0.9241 0.01652 0.00883 -0.0227 0.1090 1.0000
7.250 0.9478 0.01742 0.00975 -0.0222 0.0894 1.0000
7.500 0.9710 0.01839 0.01070 -0.0218 0.0722 1.0000
7.750 0.9930 0.01960 0.01192 -0.0211 0.0590 1.0000
8.000 1.0152 0.02078 0.01318 -0.0204 0.0487 1.0000
8.250 1.0351 0.02257 0.01510 -0.0194 0.0422 1.0000
8.500 1.0560 0.02392 0.01650 -0.0188 0.0363 1.0000
8.750 1.0750 0.02607 0.01884 -0.0177 0.0325 1.0000
9.000 1.0951 0.02795 0.02095 -0.0167 0.0298 1.0000
9.250 1.1139 0.02986 0.02302 -0.0158 0.0274 1.0000
9.500 1.1244 0.03441 0.02785 -0.0147 0.0251 1.0000
9.750 1.1413 0.03595 0.02976 -0.0137 0.0238 1.0000
10.000 1.1520 0.03917 0.03342 -0.0125 0.0230 1.0000
10.250 1.1573 0.04294 0.03763 -0.0112 0.0224 1.0000
10.500 1.1561 0.04713 0.04225 -0.0101 0.0222 1.0000
10.750 1.1478 0.05156 0.04712 -0.0092 0.0221 1.0000
11.000 1.1318 0.05581 0.05167 -0.0085 0.0222 1.0000
11.250 1.1130 0.06078 0.05685 -0.0103 0.0223 1.0000
11.500 1.0933 0.06699 0.06327 -0.0146 0.0225 1.0000
11.750 1.0726 0.07440 0.07087 -0.0205 0.0228 1.0000
12.000 1.0505 0.08310 0.07972 -0.0275 0.0231 1.0000
12.250 1.0263 0.09309 0.08983 -0.0351 0.0236 1.0000
12.500 0.9999 0.10425 0.10106 -0.0426 0.0241 1.0000
12.750 0.9732 0.11560 0.11241 -0.0489 0.0248 1.0000
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Polar data table (+)
Polar graphs
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