AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 61.16 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-200000.txt Download as CSV file: xf-ag44ct02r-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5452 0.10517 0.10175 0.0112 1.0000 0.0354
-8.500 -0.5434 0.10141 0.09804 0.0062 1.0000 0.0361
-8.250 -0.5409 0.09741 0.09409 0.0016 1.0000 0.0363
-8.000 -0.5368 0.09311 0.08982 -0.0033 1.0000 0.0364
-7.750 -0.5281 0.08780 0.08451 -0.0104 1.0000 0.0365
-7.500 -0.5312 0.08146 0.07823 -0.0095 1.0000 0.0376
-7.250 -0.5233 0.07861 0.07540 -0.0079 1.0000 0.0387
-7.000 -0.5130 0.07496 0.07175 -0.0100 1.0000 0.0400
-6.750 -0.5011 0.07058 0.06736 -0.0140 1.0000 0.0416
-6.500 -0.4868 0.06551 0.06223 -0.0194 1.0000 0.0438
-6.250 -0.4601 0.05866 0.05490 -0.0308 1.0000 0.0483
-6.000 -0.4508 0.05150 0.04764 -0.0333 1.0000 0.0497
-5.750 -0.4364 0.04938 0.04566 -0.0322 1.0000 0.0522
-5.250 -0.3969 0.04133 0.03712 -0.0357 1.0000 0.0642
-5.000 -0.3768 0.03875 0.03448 -0.0357 1.0000 0.0678
-4.750 -0.3546 0.03505 0.03033 -0.0366 1.0000 0.0771
-4.500 -0.3332 0.03259 0.02785 -0.0363 1.0000 0.0808
-4.250 -0.2998 0.02292 0.01667 -0.0345 1.0000 0.0341
-4.000 -0.2748 0.01984 0.01313 -0.0336 1.0000 0.0315
-3.750 -0.2489 0.01760 0.01050 -0.0326 1.0000 0.0304
-3.500 -0.2231 0.01601 0.00868 -0.0317 1.0000 0.0310
-3.250 -0.1976 0.01479 0.00735 -0.0309 1.0000 0.0331
-3.000 -0.1722 0.01376 0.00623 -0.0302 1.0000 0.0379
-2.750 -0.1470 0.01267 0.00519 -0.0295 1.0000 0.0442
-2.500 -0.1214 0.01182 0.00436 -0.0290 1.0000 0.0596
-2.250 -0.0952 0.01046 0.00352 -0.0290 1.0000 0.1582
-2.000 -0.0700 0.00939 0.00333 -0.0293 1.0000 0.3621
-1.750 -0.0472 0.00834 0.00335 -0.0288 1.0000 0.6254
-1.500 -0.0065 0.00747 0.00332 -0.0298 0.9953 1.0000
-1.250 0.0444 0.00748 0.00309 -0.0347 0.9786 1.0000
-1.000 0.0912 0.00746 0.00290 -0.0386 0.9571 1.0000
-0.750 0.1328 0.00743 0.00271 -0.0412 0.9299 1.0000
-0.500 0.1679 0.00742 0.00253 -0.0422 0.8983 1.0000
-0.250 0.1964 0.00747 0.00241 -0.0418 0.8652 1.0000
0.000 0.2222 0.00757 0.00232 -0.0409 0.8350 1.0000
0.250 0.2475 0.00771 0.00227 -0.0399 0.8081 1.0000
0.500 0.2728 0.00788 0.00225 -0.0390 0.7837 1.0000
0.750 0.2984 0.00806 0.00226 -0.0382 0.7608 1.0000
1.000 0.3241 0.00825 0.00231 -0.0375 0.7395 1.0000
1.250 0.3499 0.00846 0.00238 -0.0368 0.7189 1.0000
1.500 0.3759 0.00867 0.00246 -0.0362 0.6990 1.0000
1.750 0.4021 0.00883 0.00254 -0.0356 0.6773 1.0000
2.000 0.4284 0.00893 0.00260 -0.0351 0.6540 1.0000
2.250 0.4547 0.00905 0.00265 -0.0345 0.6302 1.0000
2.500 0.4808 0.00919 0.00269 -0.0339 0.6047 1.0000
2.750 0.5068 0.00936 0.00275 -0.0334 0.5773 1.0000
3.000 0.5329 0.00955 0.00284 -0.0329 0.5478 1.0000
3.250 0.5589 0.00978 0.00296 -0.0324 0.5175 1.0000
3.500 0.5848 0.01004 0.00313 -0.0319 0.4870 1.0000
3.750 0.6106 0.01034 0.00331 -0.0314 0.4568 1.0000
4.000 0.6365 0.01066 0.00352 -0.0310 0.4277 1.0000
4.250 0.6623 0.01100 0.00377 -0.0306 0.3997 1.0000
4.500 0.6881 0.01135 0.00407 -0.0302 0.3729 1.0000
4.750 0.7139 0.01172 0.00437 -0.0299 0.3471 1.0000
5.000 0.7395 0.01213 0.00469 -0.0295 0.3228 1.0000
5.250 0.7651 0.01253 0.00505 -0.0291 0.2986 1.0000
5.500 0.7908 0.01293 0.00546 -0.0288 0.2751 1.0000
5.750 0.8161 0.01339 0.00586 -0.0285 0.2530 1.0000
6.000 0.8414 0.01383 0.00630 -0.0281 0.2303 1.0000
6.250 0.8666 0.01432 0.00677 -0.0278 0.2084 1.0000
6.500 0.8913 0.01486 0.00729 -0.0274 0.1867 1.0000
6.750 0.9162 0.01537 0.00783 -0.0270 0.1645 1.0000
7.000 0.9403 0.01601 0.00843 -0.0266 0.1429 1.0000
7.250 0.9643 0.01668 0.00908 -0.0262 0.1202 1.0000
7.500 0.9877 0.01749 0.00989 -0.0258 0.0976 1.0000
7.750 1.0096 0.01857 0.01094 -0.0251 0.0768 1.0000
8.000 1.0312 0.01971 0.01210 -0.0244 0.0603 1.0000
8.250 1.0515 0.02107 0.01350 -0.0235 0.0491 1.0000
8.500 1.0700 0.02281 0.01529 -0.0224 0.0418 1.0000
8.750 1.0902 0.02406 0.01661 -0.0216 0.0357 1.0000
9.000 1.1068 0.02641 0.01910 -0.0202 0.0323 1.0000
9.250 1.1259 0.02823 0.02114 -0.0191 0.0296 1.0000
9.500 1.1440 0.02984 0.02292 -0.0182 0.0269 1.0000
9.750 1.1547 0.03373 0.02699 -0.0169 0.0245 1.0000
10.000 1.1695 0.03592 0.02953 -0.0156 0.0236 1.0000
10.250 1.1804 0.03877 0.03277 -0.0142 0.0228 1.0000
10.500 1.1864 0.04213 0.03653 -0.0127 0.0223 1.0000
10.750 1.1865 0.04586 0.04067 -0.0111 0.0220 1.0000
11.000 1.1800 0.04982 0.04500 -0.0096 0.0219 1.0000
11.250 1.1659 0.05365 0.04914 -0.0081 0.0219 1.0000
11.500 1.1489 0.05803 0.05377 -0.0084 0.0220 1.0000
11.750 1.1305 0.06336 0.05935 -0.0109 0.0221 1.0000
12.000 1.1109 0.06972 0.06592 -0.0150 0.0223 1.0000
12.250 1.0901 0.07710 0.07349 -0.0204 0.0225 1.0000
12.500 1.0681 0.08555 0.08210 -0.0268 0.0228 1.0000
12.750 1.0445 0.09509 0.09176 -0.0337 0.0231 1.0000
13.000 1.0190 0.10565 0.10241 -0.0408 0.0236 1.0000
13.250 0.9916 0.11704 0.11383 -0.0475 0.0241 1.0000
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Polar data table (+)
Polar graphs
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