AG36 (ag36-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 200,000 Max Cl/Cd: 67.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag36-il-200000.txt Download as CSV file: xf-ag36-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG36
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5210 0.11619 0.11260 0.0034 1.0000 0.0390
-11.000 -0.5219 0.11256 0.10901 -0.0017 1.0000 0.0398
-10.750 -0.5214 0.10872 0.10522 -0.0060 1.0000 0.0401
-10.500 -0.5195 0.10471 0.10124 -0.0096 1.0000 0.0402
-10.250 -0.5178 0.10046 0.09703 -0.0133 1.0000 0.0403
-10.000 -0.5144 0.09481 0.09140 -0.0094 1.0000 0.0417
-9.750 -0.5063 0.09186 0.08846 -0.0086 1.0000 0.0427
-9.500 -0.5010 0.08860 0.08522 -0.0096 1.0000 0.0439
-9.250 -0.4981 0.08503 0.08169 -0.0116 1.0000 0.0451
-9.000 -0.4952 0.08102 0.07771 -0.0151 1.0000 0.0466
-8.750 -0.4887 0.07598 0.07267 -0.0216 1.0000 0.0489
-8.500 -0.4768 0.06799 0.06439 -0.0370 1.0000 0.0518
-8.250 -0.4742 0.06092 0.05725 -0.0397 1.0000 0.0529
-8.000 -0.4624 0.05915 0.05562 -0.0369 1.0000 0.0547
-7.750 -0.4495 0.05635 0.05280 -0.0371 1.0000 0.0569
-7.500 -0.4355 0.05242 0.04874 -0.0388 1.0000 0.0602
-7.250 -0.4228 0.04614 0.04185 -0.0423 1.0000 0.0662
-7.000 -0.4081 0.04330 0.03912 -0.0414 1.0000 0.0679
-6.750 -0.3921 0.04094 0.03671 -0.0407 1.0000 0.0709
-6.500 -0.3752 0.03733 0.03256 -0.0410 1.0000 0.0802
-6.250 -0.3585 0.03485 0.03015 -0.0400 1.0000 0.0827
-6.000 -0.3300 0.02467 0.01818 -0.0379 1.0000 0.0409
-5.750 -0.3093 0.02187 0.01509 -0.0370 1.0000 0.0420
-5.500 -0.2863 0.02011 0.01298 -0.0358 1.0000 0.0414
-5.250 -0.2630 0.01835 0.01096 -0.0348 1.0000 0.0417
-5.000 -0.2393 0.01689 0.00938 -0.0340 1.0000 0.0430
-4.750 -0.2158 0.01598 0.00841 -0.0332 1.0000 0.0456
-4.500 -0.1923 0.01541 0.00776 -0.0324 1.0000 0.0501
-4.250 -0.1671 0.01443 0.00671 -0.0319 1.0000 0.0533
-4.000 -0.1317 0.01358 0.00591 -0.0336 0.9971 0.0618
-3.750 -0.0894 0.01277 0.00512 -0.0365 0.9921 0.0781
-3.500 -0.0482 0.01143 0.00437 -0.0397 0.9867 0.1831
-3.250 -0.0087 0.01003 0.00420 -0.0429 0.9818 0.4858
-3.000 0.0181 0.00879 0.00430 -0.0414 0.9750 0.8536
-2.750 0.0788 0.00860 0.00404 -0.0475 0.9715 1.0000
-2.500 0.1223 0.00850 0.00379 -0.0506 0.9603 1.0000
-2.250 0.1628 0.00840 0.00356 -0.0530 0.9471 1.0000
-2.000 0.1988 0.00830 0.00334 -0.0543 0.9311 1.0000
-1.750 0.2307 0.00821 0.00314 -0.0546 0.9127 1.0000
-1.500 0.2573 0.00815 0.00299 -0.0539 0.8886 1.0000
-1.250 0.2833 0.00812 0.00282 -0.0529 0.8645 1.0000
-1.000 0.3082 0.00815 0.00270 -0.0516 0.8390 1.0000
-0.750 0.3328 0.00824 0.00263 -0.0505 0.8117 1.0000
-0.500 0.3577 0.00837 0.00261 -0.0495 0.7836 1.0000
-0.250 0.3830 0.00852 0.00261 -0.0487 0.7560 1.0000
0.000 0.4087 0.00867 0.00263 -0.0480 0.7295 1.0000
0.250 0.4346 0.00882 0.00265 -0.0474 0.7043 1.0000
0.500 0.4607 0.00898 0.00269 -0.0469 0.6797 1.0000
0.750 0.4869 0.00913 0.00273 -0.0464 0.6555 1.0000
1.000 0.5130 0.00933 0.00279 -0.0459 0.6344 1.0000
1.250 0.5392 0.00958 0.00291 -0.0455 0.6145 1.0000
1.500 0.5655 0.00987 0.00309 -0.0452 0.5962 1.0000
1.750 0.5919 0.01015 0.00329 -0.0449 0.5781 1.0000
2.000 0.6184 0.01039 0.00350 -0.0446 0.5599 1.0000
2.250 0.6448 0.01064 0.00371 -0.0443 0.5418 1.0000
2.500 0.6711 0.01088 0.00393 -0.0440 0.5238 1.0000
2.750 0.6974 0.01111 0.00414 -0.0437 0.5051 1.0000
3.000 0.7237 0.01129 0.00435 -0.0435 0.4840 1.0000
3.250 0.7498 0.01150 0.00456 -0.0432 0.4624 1.0000
3.500 0.7759 0.01168 0.00475 -0.0429 0.4374 1.0000
3.750 0.8015 0.01192 0.00496 -0.0425 0.4099 1.0000
4.000 0.8267 0.01224 0.00522 -0.0422 0.3800 1.0000
4.250 0.8515 0.01263 0.00554 -0.0418 0.3480 1.0000
4.500 0.8760 0.01308 0.00592 -0.0414 0.3147 1.0000
4.750 0.9000 0.01361 0.00635 -0.0410 0.2812 1.0000
5.000 0.9238 0.01418 0.00682 -0.0405 0.2468 1.0000
5.250 0.9472 0.01480 0.00735 -0.0402 0.2125 1.0000
5.500 0.9702 0.01548 0.00792 -0.0397 0.1813 1.0000
5.750 0.9929 0.01623 0.00857 -0.0393 0.1522 1.0000
6.000 1.0153 0.01701 0.00928 -0.0388 0.1220 1.0000
6.250 1.0361 0.01804 0.01016 -0.0381 0.0886 1.0000
6.500 1.0537 0.01957 0.01153 -0.0370 0.0604 1.0000
6.750 1.0719 0.02097 0.01295 -0.0358 0.0462 1.0000
7.000 1.0872 0.02272 0.01469 -0.0343 0.0389 1.0000
7.250 1.1069 0.02380 0.01589 -0.0333 0.0336 1.0000
7.500 1.1194 0.02610 0.01818 -0.0315 0.0302 1.0000
7.750 1.1381 0.02756 0.01983 -0.0303 0.0284 1.0000
8.000 1.1557 0.02934 0.02179 -0.0290 0.0267 1.0000
8.250 1.1727 0.03108 0.02366 -0.0278 0.0251 1.0000
8.500 1.1875 0.03326 0.02588 -0.0267 0.0235 1.0000
8.750 1.1993 0.03653 0.02943 -0.0253 0.0224 1.0000
9.000 1.2111 0.03883 0.03206 -0.0236 0.0219 1.0000
9.250 1.2189 0.04165 0.03523 -0.0218 0.0215 1.0000
9.500 1.2218 0.04478 0.03872 -0.0197 0.0214 1.0000
9.750 1.2190 0.04809 0.04238 -0.0173 0.0213 1.0000
10.000 1.2091 0.05135 0.04594 -0.0144 0.0213 1.0000
10.250 1.1960 0.05493 0.04979 -0.0124 0.0214 1.0000
10.500 1.1805 0.05898 0.05410 -0.0114 0.0215 1.0000
10.750 1.1632 0.06361 0.05897 -0.0117 0.0216 1.0000
11.000 1.1447 0.06891 0.06450 -0.0133 0.0218 1.0000
11.250 1.1251 0.07497 0.07076 -0.0162 0.0219 1.0000
11.500 1.1048 0.08182 0.07779 -0.0201 0.0220 1.0000
11.750 1.0833 0.08945 0.08558 -0.0247 0.0222 1.0000
12.000 1.0611 0.09778 0.09404 -0.0297 0.0224 1.0000
12.750 0.7686 0.12795 0.12477 -0.0339 0.0290 1.0000
13.000 0.7362 0.13843 0.13525 -0.0377 0.0319 1.0000
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Polar data table (+)
Polar graphs
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