AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.22 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45c03-il-1000000-n5.txt Download as CSV file: xf-ag45c03-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -03f
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5926 0.10450 0.10297 0.0296 1.0000 0.0047
-7.750 -0.5897 0.10058 0.09906 0.0277 1.0000 0.0045
-7.500 -0.5874 0.09641 0.09490 0.0255 1.0000 0.0043
-7.250 -0.5859 0.09196 0.09047 0.0230 1.0000 0.0041
-7.000 -0.5854 0.08716 0.08569 0.0199 1.0000 0.0039
-6.500 -0.5834 0.06755 0.06608 -0.0014 1.0000 0.0032
-6.250 -0.5993 0.02068 0.01742 -0.0309 1.0000 0.0034
-6.000 -0.5743 0.01909 0.01561 -0.0310 1.0000 0.0035
-5.750 -0.5488 0.01770 0.01401 -0.0311 1.0000 0.0037
-5.500 -0.5150 0.01627 0.01231 -0.0328 0.9401 0.0039
-5.250 -0.4962 0.01579 0.01105 -0.0308 0.7529 0.0040
-5.000 -0.4700 0.01471 0.00966 -0.0306 0.7327 0.0042
-4.750 -0.4433 0.01377 0.00849 -0.0305 0.7223 0.0043
-4.500 -0.4163 0.01296 0.00748 -0.0303 0.7145 0.0045
-4.250 -0.3891 0.01223 0.00658 -0.0301 0.7090 0.0046
-4.000 -0.3617 0.01160 0.00580 -0.0300 0.7039 0.0048
-3.750 -0.3340 0.01115 0.00526 -0.0299 0.6987 0.0050
-3.500 -0.3062 0.01076 0.00478 -0.0298 0.6922 0.0051
-3.250 -0.2783 0.01038 0.00434 -0.0297 0.6859 0.0052
-3.000 -0.2506 0.00971 0.00354 -0.0295 0.6785 0.0054
-2.750 -0.2226 0.00921 0.00295 -0.0294 0.6700 0.0056
-2.500 -0.1945 0.00887 0.00253 -0.0293 0.6608 0.0060
-2.250 -0.1664 0.00863 0.00222 -0.0292 0.6502 0.0066
-2.000 -0.1383 0.00842 0.00195 -0.0291 0.6381 0.0076
-1.750 -0.1101 0.00824 0.00170 -0.0290 0.6252 0.0091
-1.500 -0.0820 0.00809 0.00150 -0.0289 0.6113 0.0119
-1.250 -0.0538 0.00795 0.00133 -0.0289 0.5965 0.0174
-1.000 -0.0258 0.00781 0.00119 -0.0288 0.5814 0.0301
-0.750 0.0023 0.00763 0.00106 -0.0288 0.5659 0.0572
-0.500 0.0304 0.00749 0.00096 -0.0288 0.5499 0.0879
-0.250 0.0584 0.00733 0.00087 -0.0288 0.5340 0.1290
0.000 0.0865 0.00717 0.00081 -0.0289 0.5183 0.1783
0.250 0.1146 0.00705 0.00077 -0.0289 0.5027 0.2270
0.500 0.1427 0.00690 0.00072 -0.0290 0.4872 0.2849
0.750 0.1707 0.00674 0.00070 -0.0291 0.4720 0.3543
1.000 0.1986 0.00653 0.00069 -0.0291 0.4571 0.4449
1.250 0.2263 0.00630 0.00070 -0.0292 0.4418 0.5472
1.500 0.2538 0.00607 0.00071 -0.0292 0.4263 0.6544
1.750 0.2804 0.00581 0.00076 -0.0289 0.4108 0.7724
2.000 0.3043 0.00557 0.00080 -0.0277 0.3952 0.8800
2.250 0.3317 0.00548 0.00081 -0.0273 0.3781 0.9773
2.500 0.3620 0.00559 0.00084 -0.0278 0.3603 1.0000
2.750 0.3901 0.00573 0.00089 -0.0278 0.3428 1.0000
3.000 0.4182 0.00587 0.00095 -0.0278 0.3255 1.0000
3.250 0.4462 0.00601 0.00102 -0.0278 0.3074 1.0000
3.500 0.4742 0.00616 0.00110 -0.0278 0.2904 1.0000
4.000 0.5300 0.00651 0.00128 -0.0278 0.2555 1.0000
4.250 0.5579 0.00669 0.00140 -0.0278 0.2366 1.0000
4.500 0.5857 0.00688 0.00152 -0.0278 0.2198 1.0000
4.750 0.6134 0.00710 0.00166 -0.0278 0.2012 1.0000
5.000 0.6411 0.00731 0.00180 -0.0278 0.1856 1.0000
5.250 0.6687 0.00753 0.00198 -0.0278 0.1682 1.0000
5.500 0.6962 0.00777 0.00215 -0.0278 0.1527 1.0000
5.750 0.7236 0.00803 0.00234 -0.0277 0.1362 1.0000
6.000 0.7510 0.00828 0.00254 -0.0277 0.1225 1.0000
6.250 0.7783 0.00856 0.00278 -0.0277 0.1081 1.0000
6.500 0.8055 0.00883 0.00301 -0.0277 0.0959 1.0000
6.750 0.8326 0.00914 0.00326 -0.0277 0.0829 1.0000
7.000 0.8597 0.00943 0.00352 -0.0276 0.0721 1.0000
7.250 0.8865 0.00976 0.00382 -0.0276 0.0608 1.0000
7.500 0.9133 0.01011 0.00413 -0.0275 0.0503 1.0000
7.750 0.9399 0.01046 0.00446 -0.0275 0.0418 1.0000
8.000 0.9664 0.01086 0.00483 -0.0274 0.0333 1.0000
8.250 0.9926 0.01127 0.00522 -0.0273 0.0263 1.0000
8.500 1.0190 0.01164 0.00561 -0.0272 0.0223 1.0000
8.750 1.0450 0.01208 0.00605 -0.0271 0.0174 1.0000
9.000 1.0710 0.01251 0.00649 -0.0270 0.0144 1.0000
9.250 1.0967 0.01298 0.00698 -0.0268 0.0116 1.0000
9.500 1.1225 0.01340 0.00745 -0.0267 0.0102 1.0000
9.750 1.1477 0.01394 0.00800 -0.0265 0.0085 1.0000
10.000 1.1729 0.01445 0.00858 -0.0263 0.0074 1.0000
10.250 1.1980 0.01493 0.00912 -0.0262 0.0065 1.0000
10.500 1.2226 0.01551 0.00974 -0.0260 0.0057 1.0000
10.750 1.2465 0.01621 0.01051 -0.0257 0.0050 1.0000
11.000 1.2707 0.01682 0.01119 -0.0254 0.0046 1.0000
11.250 1.2945 0.01743 0.01189 -0.0252 0.0043 1.0000
11.500 1.3179 0.01810 0.01264 -0.0249 0.0040 1.0000
11.750 1.3408 0.01882 0.01346 -0.0245 0.0037 1.0000
12.000 1.3629 0.01961 0.01432 -0.0242 0.0034 1.0000
12.250 1.3837 0.02061 0.01542 -0.0237 0.0030 1.0000
12.500 1.4041 0.02160 0.01652 -0.0233 0.0028 1.0000
12.750 1.4250 0.02242 0.01744 -0.0228 0.0027 1.0000
13.000 1.4449 0.02335 0.01847 -0.0224 0.0025 1.0000
13.250 1.4636 0.02438 0.01961 -0.0218 0.0024 1.0000
13.500 1.4811 0.02550 0.02085 -0.0212 0.0022 1.0000
13.750 1.4972 0.02671 0.02217 -0.0205 0.0021 1.0000
14.000 1.5116 0.02802 0.02362 -0.0198 0.0020 1.0000
14.250 1.5236 0.02947 0.02519 -0.0190 0.0019 1.0000
14.500 1.5324 0.03114 0.02699 -0.0182 0.0018 1.0000
14.750 1.5333 0.03309 0.02907 -0.0167 0.0018 1.0000
15.000 1.5293 0.03593 0.03207 -0.0168 0.0017 1.0000
15.250 1.5237 0.04022 0.03652 -0.0196 0.0017 1.0000
15.500 1.5149 0.04530 0.04177 -0.0229 0.0016 1.0000
15.750 1.5012 0.05136 0.04800 -0.0266 0.0016 1.0000
16.000 1.4827 0.05836 0.05517 -0.0307 0.0016 1.0000
16.250 1.4612 0.06597 0.06293 -0.0349 0.0016 1.0000
16.500 1.4354 0.07441 0.07152 -0.0394 0.0016 1.0000
16.750 1.4060 0.08362 0.08088 -0.0440 0.0017 1.0000
17.000 1.3751 0.09322 0.09061 -0.0486 0.0017 1.0000
17.250 1.3402 0.10383 0.10137 -0.0538 0.0018 1.0000
17.500 1.3051 0.11495 0.11262 -0.0591 0.0018 1.0000
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Polar data table (+)
Polar graphs
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