AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-1000000-n5.txt Download as CSV file: xf-ag44ct02r-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5711 0.08633 0.08481 0.0091 1.0000 0.0037
-8.000 -0.5820 0.07779 0.07630 0.0023 1.0000 0.0034
-7.750 -0.6445 0.02221 0.01903 -0.0368 1.0000 0.0033
-7.500 -0.6227 0.02011 0.01665 -0.0367 1.0000 0.0035
-7.250 -0.5993 0.01871 0.01506 -0.0364 1.0000 0.0036
-7.000 -0.5752 0.01757 0.01375 -0.0361 1.0000 0.0037
-6.750 -0.5509 0.01649 0.01249 -0.0358 1.0000 0.0039
-6.500 -0.5266 0.01534 0.01116 -0.0353 1.0000 0.0040
-6.250 -0.5022 0.01432 0.00996 -0.0348 1.0000 0.0042
-6.000 -0.4771 0.01337 0.00884 -0.0343 0.9997 0.0044
-5.750 -0.4448 0.01243 0.00774 -0.0355 0.9940 0.0045
-5.500 -0.4127 0.01162 0.00679 -0.0365 0.9847 0.0047
-5.250 -0.3790 0.01090 0.00595 -0.0378 0.9698 0.0048
-5.000 -0.3463 0.01035 0.00528 -0.0387 0.9383 0.0050
-4.750 -0.3217 0.01016 0.00484 -0.0377 0.8712 0.0051
-4.500 -0.2979 0.01009 0.00445 -0.0366 0.7940 0.0052
-4.250 -0.2724 0.00954 0.00362 -0.0361 0.7526 0.0055
-4.000 -0.2456 0.00917 0.00309 -0.0358 0.7317 0.0057
-3.750 -0.2183 0.00889 0.00270 -0.0356 0.7188 0.0061
-3.500 -0.1908 0.00867 0.00240 -0.0354 0.7097 0.0066
-3.250 -0.1631 0.00849 0.00214 -0.0352 0.7023 0.0074
-3.000 -0.1351 0.00830 0.00191 -0.0351 0.6933 0.0081
-2.750 -0.1072 0.00809 0.00168 -0.0350 0.6832 0.0109
-2.500 -0.0794 0.00794 0.00151 -0.0349 0.6722 0.0149
-2.250 -0.0515 0.00779 0.00134 -0.0348 0.6595 0.0229
-2.000 -0.0238 0.00761 0.00120 -0.0347 0.6451 0.0418
-1.750 0.0038 0.00743 0.00108 -0.0346 0.6294 0.0726
-1.500 0.0314 0.00725 0.00097 -0.0345 0.6124 0.1103
-1.250 0.0590 0.00710 0.00088 -0.0345 0.5943 0.1539
-1.000 0.0865 0.00694 0.00081 -0.0344 0.5752 0.2063
-0.750 0.1139 0.00679 0.00076 -0.0343 0.5545 0.2640
-0.500 0.1413 0.00664 0.00072 -0.0343 0.5339 0.3308
-0.250 0.1686 0.00650 0.00070 -0.0342 0.5115 0.4019
0.000 0.1958 0.00636 0.00069 -0.0341 0.4889 0.4758
0.250 0.2229 0.00625 0.00070 -0.0340 0.4661 0.5502
0.500 0.2496 0.00609 0.00073 -0.0338 0.4435 0.6401
0.750 0.2760 0.00595 0.00076 -0.0335 0.4221 0.7264
1.000 0.3010 0.00577 0.00081 -0.0328 0.4015 0.8194
1.250 0.3234 0.00560 0.00086 -0.0312 0.3818 0.9274
1.500 0.3634 0.00568 0.00089 -0.0338 0.3589 0.9990
1.750 0.3910 0.00583 0.00094 -0.0337 0.3392 1.0000
2.000 0.4185 0.00597 0.00100 -0.0336 0.3211 1.0000
2.250 0.4459 0.00612 0.00108 -0.0334 0.3032 1.0000
2.500 0.4733 0.00628 0.00115 -0.0333 0.2855 1.0000
2.750 0.5007 0.00644 0.00123 -0.0332 0.2697 1.0000
3.000 0.5281 0.00660 0.00133 -0.0331 0.2543 1.0000
3.250 0.5555 0.00677 0.00144 -0.0330 0.2387 1.0000
3.500 0.5828 0.00694 0.00155 -0.0328 0.2240 1.0000
3.750 0.6101 0.00712 0.00167 -0.0327 0.2086 1.0000
4.000 0.6373 0.00731 0.00181 -0.0326 0.1939 1.0000
4.250 0.6645 0.00751 0.00196 -0.0325 0.1796 1.0000
4.500 0.6917 0.00773 0.00212 -0.0324 0.1653 1.0000
4.750 0.7187 0.00795 0.00229 -0.0322 0.1510 1.0000
5.000 0.7456 0.00820 0.00248 -0.0321 0.1358 1.0000
5.250 0.7725 0.00845 0.00270 -0.0320 0.1222 1.0000
5.500 0.7991 0.00875 0.00292 -0.0318 0.1070 1.0000
6.000 0.8522 0.00936 0.00343 -0.0315 0.0800 1.0000
6.250 0.8785 0.00970 0.00372 -0.0313 0.0665 1.0000
6.500 0.9047 0.01006 0.00403 -0.0311 0.0541 1.0000
6.750 0.9307 0.01044 0.00437 -0.0309 0.0432 1.0000
7.000 0.9566 0.01085 0.00473 -0.0307 0.0332 1.0000
7.250 0.9824 0.01124 0.00510 -0.0305 0.0266 1.0000
7.500 1.0083 0.01161 0.00550 -0.0303 0.0216 1.0000
7.750 1.0338 0.01205 0.00592 -0.0300 0.0166 1.0000
8.000 1.0593 0.01247 0.00635 -0.0297 0.0136 1.0000
8.250 1.0846 0.01292 0.00682 -0.0295 0.0111 1.0000
8.500 1.1100 0.01333 0.00727 -0.0292 0.0097 1.0000
8.750 1.1348 0.01384 0.00781 -0.0289 0.0081 1.0000
9.000 1.1595 0.01434 0.00837 -0.0285 0.0071 1.0000
9.250 1.1843 0.01481 0.00890 -0.0282 0.0064 1.0000
9.500 1.2085 0.01535 0.00947 -0.0279 0.0056 1.0000
9.750 1.2320 0.01600 0.01018 -0.0274 0.0049 1.0000
10.000 1.2555 0.01663 0.01089 -0.0270 0.0045 1.0000
10.250 1.2790 0.01721 0.01155 -0.0266 0.0043 1.0000
10.500 1.3020 0.01784 0.01226 -0.0261 0.0040 1.0000
10.750 1.3244 0.01853 0.01304 -0.0256 0.0037 1.0000
11.000 1.3463 0.01926 0.01385 -0.0251 0.0035 1.0000
11.250 1.3674 0.02006 0.01474 -0.0245 0.0032 1.0000
11.500 1.3871 0.02103 0.01581 -0.0237 0.0030 1.0000
11.750 1.4039 0.02236 0.01728 -0.0227 0.0028 1.0000
12.000 1.4232 0.02323 0.01825 -0.0220 0.0027 1.0000
12.250 1.4416 0.02415 0.01927 -0.0212 0.0026 1.0000
12.500 1.4587 0.02514 0.02038 -0.0204 0.0025 1.0000
12.750 1.4745 0.02622 0.02157 -0.0194 0.0024 1.0000
13.000 1.4886 0.02738 0.02286 -0.0183 0.0022 1.0000
13.250 1.5007 0.02865 0.02424 -0.0171 0.0021 1.0000
13.500 1.5089 0.03004 0.02575 -0.0156 0.0021 1.0000
13.750 1.5122 0.03162 0.02745 -0.0137 0.0020 1.0000
14.000 1.5121 0.03363 0.02959 -0.0124 0.0019 1.0000
14.250 1.5104 0.03622 0.03232 -0.0122 0.0019 1.0000
14.500 1.5063 0.03971 0.03597 -0.0134 0.0019 1.0000
14.750 1.5003 0.04396 0.04036 -0.0155 0.0018 1.0000
15.000 1.4907 0.04904 0.04560 -0.0183 0.0018 1.0000
15.250 1.4757 0.05536 0.05208 -0.0220 0.0018 1.0000
15.500 1.4550 0.06294 0.05983 -0.0264 0.0018 1.0000
15.750 1.4291 0.07162 0.06868 -0.0312 0.0018 1.0000
16.000 1.3967 0.08159 0.07881 -0.0365 0.0018 1.0000
16.250 1.3606 0.09221 0.08959 -0.0418 0.0019 1.0000
16.500 1.3227 0.10332 0.10084 -0.0472 0.0019 1.0000
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Polar data table (+)
Polar graphs
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