AG35 (ag35-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.32 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag35-il-1000000-n5.txt Download as CSV file: xf-ag35-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG35
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5816 0.14406 0.14238 0.0207 1.0000 0.0042
-13.750 -0.5771 0.14021 0.13854 0.0191 1.0000 0.0043
-12.750 -0.9162 0.03398 0.03168 -0.0510 1.0000 0.0052
-12.500 -0.9098 0.02958 0.02691 -0.0517 1.0000 0.0053
-12.250 -0.8956 0.02682 0.02385 -0.0516 1.0000 0.0055
-12.000 -0.8779 0.02472 0.02150 -0.0514 1.0000 0.0056
-11.750 -0.8583 0.02297 0.01952 -0.0510 1.0000 0.0057
-11.500 -0.8372 0.02153 0.01787 -0.0506 1.0000 0.0058
-11.250 -0.8149 0.02033 0.01651 -0.0502 1.0000 0.0058
-11.000 -0.7948 0.01849 0.01441 -0.0496 1.0000 0.0060
-10.750 -0.7717 0.01743 0.01321 -0.0491 1.0000 0.0063
-10.500 -0.7475 0.01665 0.01233 -0.0487 1.0000 0.0064
-10.250 -0.7229 0.01601 0.01159 -0.0482 1.0000 0.0066
-10.000 -0.6966 0.01539 0.01089 -0.0480 0.9983 0.0068
-9.750 -0.6660 0.01474 0.01015 -0.0488 0.9924 0.0071
-9.500 -0.6354 0.01411 0.00942 -0.0495 0.9850 0.0073
-9.250 -0.6055 0.01350 0.00871 -0.0500 0.9764 0.0076
-9.000 -0.5758 0.01294 0.00805 -0.0504 0.9662 0.0079
-8.750 -0.5478 0.01250 0.00750 -0.0504 0.9537 0.0081
-8.500 -0.5213 0.01216 0.00707 -0.0499 0.9402 0.0083
-8.250 -0.4962 0.01151 0.00630 -0.0493 0.9263 0.0088
-7.750 -0.4443 0.01080 0.00542 -0.0482 0.8974 0.0095
-7.500 -0.4178 0.01050 0.00502 -0.0477 0.8834 0.0099
-7.250 -0.3910 0.01021 0.00464 -0.0473 0.8695 0.0103
-7.000 -0.3641 0.00993 0.00427 -0.0470 0.8546 0.0108
-6.750 -0.3370 0.00969 0.00393 -0.0466 0.8380 0.0112
-6.500 -0.3096 0.00948 0.00362 -0.0464 0.8206 0.0116
-6.250 -0.2824 0.00919 0.00325 -0.0461 0.8051 0.0127
-6.000 -0.2548 0.00900 0.00299 -0.0459 0.7922 0.0136
-5.750 -0.2270 0.00883 0.00275 -0.0457 0.7805 0.0144
-5.500 -0.1989 0.00868 0.00253 -0.0456 0.7692 0.0153
-5.250 -0.1710 0.00849 0.00228 -0.0455 0.7575 0.0168
-5.000 -0.1429 0.00835 0.00210 -0.0454 0.7451 0.0187
-4.750 -0.1148 0.00824 0.00194 -0.0453 0.7330 0.0205
-4.500 -0.0867 0.00810 0.00177 -0.0452 0.7192 0.0247
-4.250 -0.0585 0.00801 0.00163 -0.0452 0.7030 0.0286
-4.000 -0.0305 0.00792 0.00149 -0.0451 0.6779 0.0350
-3.750 -0.0034 0.00799 0.00136 -0.0449 0.6105 0.0450
-3.500 0.0244 0.00796 0.00128 -0.0449 0.5850 0.0609
-3.250 0.0525 0.00787 0.00120 -0.0449 0.5684 0.0844
-3.000 0.0805 0.00775 0.00113 -0.0450 0.5552 0.1170
-2.750 0.1086 0.00760 0.00108 -0.0450 0.5441 0.1597
-2.500 0.1367 0.00747 0.00103 -0.0451 0.5336 0.2033
-2.250 0.1649 0.00731 0.00101 -0.0452 0.5244 0.2563
-2.000 0.1930 0.00716 0.00099 -0.0453 0.5151 0.3164
-1.750 0.2210 0.00702 0.00098 -0.0454 0.5049 0.3774
-1.500 0.2491 0.00682 0.00098 -0.0456 0.4960 0.4513
-1.250 0.2768 0.00659 0.00099 -0.0456 0.4878 0.5464
-1.000 0.3042 0.00629 0.00101 -0.0456 0.4796 0.6595
-0.750 0.3306 0.00601 0.00105 -0.0453 0.4712 0.7713
-0.500 0.3550 0.00578 0.00109 -0.0444 0.4606 0.8712
-0.250 0.3789 0.00567 0.00113 -0.0431 0.4494 0.9463
0.000 0.4139 0.00572 0.00114 -0.0446 0.4363 0.9853
0.250 0.4471 0.00582 0.00117 -0.0459 0.4218 1.0000
0.500 0.4748 0.00593 0.00121 -0.0459 0.4074 1.0000
0.750 0.5024 0.00606 0.00127 -0.0459 0.3911 1.0000
1.000 0.5300 0.00621 0.00133 -0.0459 0.3734 1.0000
1.250 0.5576 0.00637 0.00142 -0.0459 0.3544 1.0000
1.500 0.5850 0.00657 0.00151 -0.0459 0.3321 1.0000
1.750 0.6123 0.00678 0.00163 -0.0459 0.3080 1.0000
2.000 0.6395 0.00701 0.00175 -0.0459 0.2852 1.0000
2.250 0.6668 0.00724 0.00189 -0.0460 0.2632 1.0000
2.500 0.6939 0.00748 0.00204 -0.0460 0.2424 1.0000
2.750 0.7211 0.00771 0.00220 -0.0460 0.2235 1.0000
3.000 0.7482 0.00796 0.00237 -0.0461 0.2054 1.0000
3.250 0.7753 0.00820 0.00255 -0.0461 0.1899 1.0000
3.500 0.8023 0.00845 0.00273 -0.0461 0.1745 1.0000
3.750 0.8292 0.00871 0.00293 -0.0462 0.1595 1.0000
4.000 0.8560 0.00898 0.00315 -0.0462 0.1443 1.0000
4.250 0.8826 0.00927 0.00338 -0.0462 0.1288 1.0000
4.500 0.9088 0.00961 0.00364 -0.0462 0.1109 1.0000
4.750 0.9347 0.01000 0.00393 -0.0461 0.0920 1.0000
5.000 0.9606 0.01037 0.00423 -0.0461 0.0768 1.0000
5.250 0.9864 0.01074 0.00455 -0.0460 0.0640 1.0000
5.500 1.0121 0.01113 0.00488 -0.0459 0.0528 1.0000
5.750 1.0375 0.01154 0.00525 -0.0458 0.0424 1.0000
6.000 1.0627 0.01196 0.00563 -0.0457 0.0333 1.0000
6.250 1.0878 0.01239 0.00603 -0.0455 0.0261 1.0000
6.500 1.1126 0.01284 0.00645 -0.0454 0.0205 1.0000
6.750 1.1372 0.01330 0.00690 -0.0452 0.0162 1.0000
7.000 1.1619 0.01373 0.00735 -0.0450 0.0132 1.0000
7.250 1.1862 0.01419 0.00782 -0.0448 0.0109 1.0000
7.500 1.2103 0.01466 0.00831 -0.0445 0.0094 1.0000
7.750 1.2340 0.01516 0.00884 -0.0442 0.0082 1.0000
8.000 1.2579 0.01562 0.00934 -0.0440 0.0076 1.0000
8.250 1.2812 0.01612 0.00990 -0.0437 0.0069 1.0000
8.500 1.3038 0.01669 0.01050 -0.0433 0.0063 1.0000
8.750 1.3256 0.01734 0.01121 -0.0427 0.0058 1.0000
9.000 1.3479 0.01789 0.01182 -0.0423 0.0055 1.0000
9.250 1.3694 0.01849 0.01248 -0.0418 0.0053 1.0000
9.500 1.3904 0.01911 0.01317 -0.0412 0.0050 1.0000
9.750 1.4107 0.01977 0.01390 -0.0406 0.0047 1.0000
10.000 1.4302 0.02048 0.01467 -0.0399 0.0045 1.0000
10.250 1.4482 0.02128 0.01554 -0.0390 0.0042 1.0000
10.500 1.4636 0.02230 0.01664 -0.0378 0.0039 1.0000
10.750 1.4796 0.02315 0.01758 -0.0367 0.0038 1.0000
11.000 1.4948 0.02402 0.01853 -0.0355 0.0037 1.0000
11.250 1.5073 0.02494 0.01954 -0.0339 0.0036 1.0000
11.500 1.5160 0.02594 0.02065 -0.0319 0.0036 1.0000
11.750 1.5233 0.02708 0.02190 -0.0299 0.0035 1.0000
12.000 1.5294 0.02841 0.02332 -0.0281 0.0034 1.0000
12.250 1.5343 0.02993 0.02495 -0.0266 0.0033 1.0000
12.500 1.5381 0.03166 0.02679 -0.0254 0.0032 1.0000
12.750 1.5407 0.03368 0.02892 -0.0245 0.0032 1.0000
13.000 1.5420 0.03598 0.03134 -0.0240 0.0031 1.0000
13.250 1.5420 0.03862 0.03410 -0.0238 0.0031 1.0000
13.500 1.5402 0.04166 0.03725 -0.0241 0.0030 1.0000
13.750 1.5360 0.04522 0.04094 -0.0249 0.0030 1.0000
14.000 1.5300 0.04927 0.04513 -0.0261 0.0029 1.0000
14.250 1.5220 0.05397 0.04996 -0.0280 0.0029 1.0000
14.500 1.5111 0.05920 0.05534 -0.0302 0.0029 1.0000
14.750 1.4967 0.06503 0.06130 -0.0326 0.0029 1.0000
15.000 1.4790 0.07139 0.06781 -0.0352 0.0029 1.0000
15.250 1.4587 0.07836 0.07492 -0.0381 0.0029 1.0000
15.500 1.4355 0.08609 0.08279 -0.0414 0.0029 1.0000
15.750 1.4115 0.09418 0.09102 -0.0449 0.0029 1.0000
16.000 1.3849 0.10306 0.10005 -0.0489 0.0029 1.0000
16.250 1.3585 0.11209 0.10921 -0.0529 0.0029 1.0000
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