AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.24 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-1000000.txt Download as CSV file: xf-ag44ct02r-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG44ct -02f
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5511 0.08971 0.08819 0.0093 1.0000 0.0081
-8.000 -0.5487 0.08530 0.08379 0.0064 1.0000 0.0081
-7.750 -0.5463 0.08066 0.07918 0.0027 1.0000 0.0082
-7.500 -0.5384 0.07501 0.07353 -0.0039 1.0000 0.0082
-7.250 -0.5348 0.06425 0.06274 -0.0164 1.0000 0.0084
-7.000 -0.5228 0.05618 0.05458 -0.0244 1.0000 0.0085
-6.750 -0.5074 0.05008 0.04837 -0.0291 1.0000 0.0087
-6.500 -0.4905 0.04487 0.04301 -0.0323 1.0000 0.0089
-6.250 -0.4724 0.04002 0.03798 -0.0344 1.0000 0.0091
-6.000 -0.4535 0.03546 0.03322 -0.0357 1.0000 0.0094
-5.750 -0.4339 0.03113 0.02862 -0.0362 1.0000 0.0098
-5.500 -0.4203 0.01904 0.01539 -0.0348 1.0000 0.0076
-5.250 -0.3977 0.01667 0.01266 -0.0338 1.0000 0.0079
-5.000 -0.3735 0.01549 0.01121 -0.0330 1.0000 0.0083
-4.750 -0.3503 0.01344 0.00888 -0.0321 1.0000 0.0083
-4.500 -0.3263 0.01204 0.00729 -0.0313 1.0000 0.0084
-4.250 -0.2919 0.01066 0.00576 -0.0327 0.9969 0.0086
-4.000 -0.2557 0.00974 0.00478 -0.0346 0.9918 0.0092
-3.750 -0.2191 0.00900 0.00396 -0.0364 0.9831 0.0095
-3.500 -0.1838 0.00837 0.00324 -0.0379 0.9670 0.0098
-3.250 -0.1511 0.00792 0.00269 -0.0386 0.9335 0.0104
-3.000 -0.1264 0.00775 0.00228 -0.0374 0.8697 0.0116
-2.750 -0.1020 0.00758 0.00182 -0.0363 0.8046 0.0151
-2.500 -0.0757 0.00744 0.00153 -0.0358 0.7670 0.0248
-1.750 0.0054 0.00675 0.00111 -0.0353 0.7176 0.1664
-1.500 0.0326 0.00649 0.00104 -0.0352 0.7076 0.2411
-1.250 0.0598 0.00617 0.00097 -0.0351 0.6981 0.3357
-1.000 0.0867 0.00578 0.00093 -0.0351 0.6869 0.4559
-0.750 0.1134 0.00541 0.00090 -0.0348 0.6749 0.5778
-0.500 0.1394 0.00505 0.00087 -0.0344 0.6615 0.6997
-0.250 0.1634 0.00468 0.00086 -0.0334 0.6464 0.8249
0.000 0.1889 0.00441 0.00087 -0.0322 0.6295 0.9585
0.250 0.2307 0.00447 0.00082 -0.0352 0.6081 1.0000
0.500 0.2580 0.00456 0.00080 -0.0350 0.5876 1.0000
0.750 0.2852 0.00466 0.00079 -0.0348 0.5654 1.0000
1.000 0.3126 0.00478 0.00080 -0.0346 0.5418 1.0000
1.250 0.3398 0.00491 0.00082 -0.0344 0.5169 1.0000
1.500 0.3671 0.00505 0.00085 -0.0342 0.4914 1.0000
1.750 0.3943 0.00521 0.00089 -0.0340 0.4653 1.0000
2.000 0.4216 0.00537 0.00094 -0.0338 0.4395 1.0000
2.250 0.4490 0.00553 0.00101 -0.0337 0.4147 1.0000
2.500 0.4762 0.00570 0.00108 -0.0335 0.3904 1.0000
2.750 0.5035 0.00588 0.00116 -0.0334 0.3678 1.0000
3.000 0.5309 0.00605 0.00125 -0.0332 0.3460 1.0000
3.250 0.5581 0.00625 0.00136 -0.0331 0.3246 1.0000
3.500 0.5854 0.00643 0.00147 -0.0330 0.3046 1.0000
3.750 0.6126 0.00663 0.00159 -0.0329 0.2844 1.0000
4.000 0.6398 0.00683 0.00172 -0.0327 0.2656 1.0000
4.250 0.6670 0.00703 0.00187 -0.0326 0.2472 1.0000
4.500 0.6941 0.00726 0.00203 -0.0325 0.2287 1.0000
4.750 0.7211 0.00748 0.00219 -0.0324 0.2114 1.0000
5.000 0.7481 0.00772 0.00237 -0.0322 0.1932 1.0000
5.250 0.7750 0.00797 0.00258 -0.0321 0.1761 1.0000
5.500 0.8017 0.00826 0.00279 -0.0319 0.1582 1.0000
5.750 0.8284 0.00853 0.00301 -0.0318 0.1414 1.0000
6.000 0.8550 0.00883 0.00326 -0.0316 0.1254 1.0000
6.250 0.8812 0.00918 0.00354 -0.0314 0.1080 1.0000
6.500 0.9074 0.00954 0.00384 -0.0313 0.0917 1.0000
6.750 0.9335 0.00991 0.00415 -0.0311 0.0769 1.0000
7.000 0.9593 0.01033 0.00451 -0.0308 0.0616 1.0000
7.250 0.9849 0.01078 0.00490 -0.0306 0.0484 1.0000
7.500 1.0102 0.01127 0.00535 -0.0303 0.0368 1.0000
7.750 1.0354 0.01178 0.00582 -0.0300 0.0275 1.0000
8.000 1.0607 0.01227 0.00631 -0.0297 0.0211 1.0000
8.250 1.0853 0.01288 0.00693 -0.0293 0.0162 1.0000
8.500 1.1103 0.01339 0.00747 -0.0290 0.0136 1.0000
8.750 1.1338 0.01422 0.00838 -0.0284 0.0111 1.0000
9.000 1.1587 0.01468 0.00891 -0.0281 0.0100 1.0000
9.250 1.1829 0.01523 0.00950 -0.0278 0.0089 1.0000
9.500 1.2035 0.01648 0.01090 -0.0269 0.0075 1.0000
9.750 1.2269 0.01713 0.01163 -0.0265 0.0071 1.0000
10.000 1.2500 0.01780 0.01239 -0.0260 0.0067 1.0000
10.250 1.2722 0.01857 0.01325 -0.0254 0.0062 1.0000
10.500 1.2939 0.01939 0.01415 -0.0248 0.0058 1.0000
10.750 1.3145 0.02032 0.01517 -0.0242 0.0054 1.0000
11.000 1.3309 0.02180 0.01680 -0.0231 0.0050 1.0000
11.250 1.3372 0.02457 0.01986 -0.0212 0.0047 1.0000
11.500 1.3569 0.02535 0.02074 -0.0205 0.0045 1.0000
11.750 1.3747 0.02631 0.02180 -0.0197 0.0043 1.0000
12.000 1.3902 0.02746 0.02307 -0.0187 0.0041 1.0000
12.250 1.4035 0.02875 0.02448 -0.0176 0.0039 1.0000
12.500 1.4137 0.03024 0.02609 -0.0164 0.0037 1.0000
12.750 1.4174 0.03192 0.02791 -0.0145 0.0036 1.0000
13.000 1.4167 0.03397 0.03010 -0.0129 0.0035 1.0000
13.250 1.4143 0.03657 0.03284 -0.0125 0.0034 1.0000
13.500 1.4099 0.04009 0.03651 -0.0136 0.0034 1.0000
13.750 1.4043 0.04437 0.04094 -0.0159 0.0033 1.0000
14.000 1.3949 0.04955 0.04630 -0.0189 0.0033 1.0000
14.250 1.3824 0.05557 0.05248 -0.0225 0.0033 1.0000
14.500 1.3654 0.06260 0.05967 -0.0266 0.0033 1.0000
14.750 1.3451 0.07036 0.06758 -0.0310 0.0033 1.0000
15.000 1.3232 0.07848 0.07583 -0.0354 0.0033 1.0000
15.250 1.2972 0.08733 0.08483 -0.0399 0.0033 1.0000
15.500 1.2696 0.09658 0.09422 -0.0445 0.0034 1.0000
15.750 1.2441 0.10571 0.10346 -0.0490 0.0034 1.0000
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Polar data table (+)
Polar graphs
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