AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 59.52 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-200000.txt Download as CSV file: xf-ag455ct02r-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG455ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5811 0.11403 0.11061 0.0177 1.0000 0.0306
-8.750 -0.5768 0.11015 0.10675 0.0151 1.0000 0.0306
-8.500 -0.5787 0.10356 0.10022 0.0144 1.0000 0.0313
-8.250 -0.5718 0.09970 0.09637 0.0161 1.0000 0.0321
-8.000 -0.5652 0.09630 0.09299 0.0159 1.0000 0.0330
-7.750 -0.5597 0.09281 0.08953 0.0145 1.0000 0.0338
-7.500 -0.5549 0.08918 0.08593 0.0124 1.0000 0.0347
-7.250 -0.5486 0.08522 0.08200 0.0090 1.0000 0.0357
-7.000 -0.5389 0.08073 0.07750 0.0041 1.0000 0.0369
-6.750 -0.5263 0.07575 0.07251 -0.0021 1.0000 0.0385
-6.500 -0.5041 0.06936 0.06602 -0.0131 1.0000 0.0411
-6.250 -0.4771 0.06370 0.06000 -0.0225 1.0000 0.0422
-6.000 -0.4693 0.05629 0.05261 -0.0248 1.0000 0.0434
-5.750 -0.4551 0.05331 0.04968 -0.0246 1.0000 0.0449
-5.500 -0.4364 0.05004 0.04634 -0.0258 1.0000 0.0473
-5.250 -0.4081 0.04572 0.04163 -0.0294 1.0000 0.0537
-5.000 -0.3877 0.04021 0.03583 -0.0316 1.0000 0.0570
-4.750 -0.3666 0.03759 0.03322 -0.0318 1.0000 0.0602
-4.500 -0.3411 0.03407 0.02928 -0.0331 1.0000 0.0707
-4.250 -0.3170 0.03181 0.02679 -0.0336 1.0000 0.0837
-4.000 -0.2810 0.02409 0.01802 -0.0325 1.0000 0.0406
-3.750 -0.2524 0.01942 0.01256 -0.0318 1.0000 0.0326
-3.500 -0.2243 0.01796 0.01075 -0.0310 1.0000 0.0312
-3.250 -0.1972 0.01608 0.00864 -0.0304 1.0000 0.0313
-3.000 -0.1708 0.01418 0.00666 -0.0298 1.0000 0.0330
-2.750 -0.1444 0.01324 0.00572 -0.0294 1.0000 0.0380
-2.500 -0.1179 0.01214 0.00462 -0.0288 1.0000 0.0458
-2.250 -0.0912 0.01128 0.00379 -0.0284 1.0000 0.0652
-2.000 -0.0646 0.00984 0.00305 -0.0285 1.0000 0.1975
-1.750 -0.0400 0.00856 0.00286 -0.0286 1.0000 0.4677
-1.500 -0.0266 0.00723 0.00291 -0.0246 1.0000 0.8430
-1.250 0.0112 0.00702 0.00268 -0.0261 1.0000 1.0000
-1.000 0.0369 0.00705 0.00259 -0.0258 1.0000 1.0000
-0.750 0.0738 0.00710 0.00252 -0.0280 0.9899 1.0000
-0.500 0.1232 0.00712 0.00240 -0.0324 0.9579 1.0000
-0.250 0.1664 0.00714 0.00225 -0.0353 0.9136 1.0000
0.000 0.1982 0.00721 0.00213 -0.0354 0.8634 1.0000
0.250 0.2238 0.00737 0.00206 -0.0343 0.8210 1.0000
0.500 0.2487 0.00759 0.00204 -0.0332 0.7873 1.0000
0.750 0.2741 0.00782 0.00206 -0.0323 0.7587 1.0000
1.000 0.2999 0.00805 0.00211 -0.0316 0.7332 1.0000
1.250 0.3260 0.00829 0.00220 -0.0310 0.7100 1.0000
1.500 0.3524 0.00850 0.00231 -0.0305 0.6864 1.0000
1.750 0.3790 0.00866 0.00237 -0.0300 0.6627 1.0000
2.000 0.4056 0.00879 0.00241 -0.0295 0.6376 1.0000
2.250 0.4322 0.00893 0.00246 -0.0290 0.6111 1.0000
2.500 0.4588 0.00910 0.00254 -0.0286 0.5835 1.0000
2.750 0.4853 0.00929 0.00262 -0.0281 0.5548 1.0000
3.000 0.5118 0.00951 0.00273 -0.0277 0.5254 1.0000
3.250 0.5383 0.00975 0.00286 -0.0273 0.4952 1.0000
3.500 0.5648 0.01001 0.00302 -0.0269 0.4640 1.0000
3.750 0.5913 0.01029 0.00324 -0.0266 0.4326 1.0000
4.000 0.6177 0.01061 0.00345 -0.0263 0.4012 1.0000
4.250 0.6440 0.01096 0.00369 -0.0260 0.3703 1.0000
4.500 0.6703 0.01132 0.00397 -0.0257 0.3389 1.0000
4.750 0.6965 0.01171 0.00431 -0.0255 0.3079 1.0000
5.000 0.7226 0.01214 0.00467 -0.0252 0.2781 1.0000
5.250 0.7485 0.01261 0.00505 -0.0250 0.2490 1.0000
5.500 0.7744 0.01311 0.00549 -0.0247 0.2215 1.0000
5.750 0.8000 0.01365 0.00600 -0.0245 0.1955 1.0000
6.000 0.8255 0.01424 0.00654 -0.0242 0.1717 1.0000
6.250 0.8505 0.01491 0.00713 -0.0240 0.1497 1.0000
6.500 0.8758 0.01555 0.00779 -0.0237 0.1288 1.0000
6.750 0.9003 0.01634 0.00853 -0.0233 0.1103 1.0000
7.000 0.9246 0.01718 0.00943 -0.0230 0.0931 1.0000
7.250 0.9487 0.01809 0.01038 -0.0225 0.0779 1.0000
7.500 0.9722 0.01912 0.01146 -0.0220 0.0650 1.0000
7.750 0.9946 0.02043 0.01281 -0.0214 0.0549 1.0000
8.000 1.0155 0.02204 0.01441 -0.0207 0.0463 1.0000
8.250 1.0388 0.02324 0.01584 -0.0200 0.0407 1.0000
8.500 1.0573 0.02562 0.01829 -0.0191 0.0354 1.0000
8.750 1.0797 0.02694 0.01992 -0.0183 0.0321 1.0000
9.000 1.0997 0.02888 0.02208 -0.0175 0.0294 1.0000
9.250 1.1174 0.03126 0.02461 -0.0167 0.0272 1.0000
9.500 1.1284 0.03542 0.02922 -0.0156 0.0254 1.0000
9.750 1.1431 0.03774 0.03197 -0.0146 0.0239 1.0000
10.000 1.1508 0.04148 0.03618 -0.0135 0.0231 1.0000
10.250 1.1522 0.04574 0.04091 -0.0124 0.0227 1.0000
10.500 1.1462 0.05042 0.04602 -0.0117 0.0225 1.0000
10.750 1.1322 0.05511 0.05106 -0.0112 0.0225 1.0000
11.000 1.1127 0.05997 0.05618 -0.0124 0.0227 1.0000
11.250 1.0921 0.06631 0.06275 -0.0171 0.0229 1.0000
11.500 1.0706 0.07418 0.07081 -0.0238 0.0233 1.0000
11.750 1.0471 0.08372 0.08049 -0.0319 0.0237 1.0000
12.000 1.0210 0.09472 0.09158 -0.0402 0.0244 1.0000
12.250 0.9930 0.10659 0.10347 -0.0477 0.0252 1.0000
12.500 0.9677 0.11743 0.11428 -0.0530 0.0259 1.0000
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Polar data table (+)
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