AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 38.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-100000-n5.txt Download as CSV file: xf-ag47ct02r-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG47ct -02f rot.
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6492 0.13607 0.13105 0.0378 1.0000 0.0373
-10.000 -0.6477 0.13293 0.12795 0.0346 1.0000 0.0377
-9.750 -0.6452 0.12952 0.12458 0.0317 1.0000 0.0379
-9.500 -0.6422 0.12593 0.12103 0.0290 1.0000 0.0381
-9.250 -0.6388 0.12220 0.11733 0.0263 1.0000 0.0382
-9.000 -0.6354 0.11836 0.11353 0.0236 1.0000 0.0382
-8.750 -0.6317 0.11440 0.10961 0.0207 1.0000 0.0383
-8.500 -0.6268 0.10831 0.10356 0.0221 1.0000 0.0390
-8.250 -0.6197 0.10402 0.09924 0.0230 1.0000 0.0398
-8.000 -0.6138 0.10018 0.09542 0.0222 1.0000 0.0404
-7.750 -0.6087 0.09636 0.09164 0.0206 1.0000 0.0410
-7.500 -0.6036 0.09245 0.08776 0.0181 1.0000 0.0415
-7.250 -0.5956 0.08813 0.08347 0.0143 1.0000 0.0419
-7.000 -0.5857 0.08352 0.07886 0.0097 1.0000 0.0421
-6.750 -0.5735 0.07857 0.07390 0.0046 1.0000 0.0421
-6.500 -0.5504 0.06962 0.06475 -0.0057 1.0000 0.0259
-6.250 -0.5385 0.06516 0.06026 -0.0077 1.0000 0.0245
-6.000 -0.5211 0.05994 0.05494 -0.0114 1.0000 0.0233
-5.750 -0.5007 0.05431 0.04913 -0.0154 1.0000 0.0220
-5.500 -0.4779 0.04842 0.04297 -0.0190 1.0000 0.0209
-5.250 -0.4532 0.04236 0.03651 -0.0218 1.0000 0.0199
-5.000 -0.4285 0.03784 0.03160 -0.0234 1.0000 0.0202
-4.750 -0.4034 0.03445 0.02784 -0.0243 1.0000 0.0219
-4.500 -0.3768 0.03085 0.02374 -0.0248 1.0000 0.0233
-4.250 -0.3496 0.02738 0.01971 -0.0250 1.0000 0.0236
-4.000 -0.3219 0.02441 0.01614 -0.0248 1.0000 0.0239
-3.750 -0.2941 0.02197 0.01321 -0.0245 1.0000 0.0246
-3.500 -0.2665 0.02000 0.01086 -0.0239 1.0000 0.0257
-3.250 -0.2398 0.01825 0.00891 -0.0235 1.0000 0.0283
-3.000 -0.2133 0.01717 0.00779 -0.0232 1.0000 0.0336
-2.750 -0.1866 0.01597 0.00643 -0.0225 1.0000 0.0377
-2.500 -0.1603 0.01499 0.00543 -0.0222 1.0000 0.0485
-2.250 -0.1337 0.01408 0.00450 -0.0217 1.0000 0.0647
-2.000 -0.1074 0.01317 0.00383 -0.0215 1.0000 0.1097
-1.750 -0.0818 0.01207 0.00340 -0.0214 1.0000 0.2569
-1.500 -0.0617 0.01040 0.00322 -0.0199 1.0000 0.6333
-1.250 -0.0269 0.00951 0.00291 -0.0197 1.0000 1.0000
-1.000 -0.0006 0.00950 0.00269 -0.0194 1.0000 1.0000
-0.750 0.0257 0.00949 0.00253 -0.0190 1.0000 1.0000
-0.500 0.0518 0.00950 0.00241 -0.0187 1.0000 1.0000
-0.250 0.0778 0.00952 0.00232 -0.0184 1.0000 1.0000
0.000 0.1037 0.00955 0.00229 -0.0180 1.0000 1.0000
0.250 0.1294 0.00959 0.00230 -0.0177 1.0000 1.0000
0.500 0.1597 0.00966 0.00235 -0.0185 0.9911 1.0000
0.750 0.2046 0.00976 0.00241 -0.0220 0.9427 1.0000
1.000 0.2463 0.00987 0.00245 -0.0244 0.8800 1.0000
1.250 0.2793 0.01005 0.00246 -0.0247 0.8173 1.0000
1.500 0.3056 0.01031 0.00253 -0.0236 0.7662 1.0000
1.750 0.3309 0.01060 0.00263 -0.0225 0.7252 1.0000
2.000 0.3564 0.01089 0.00278 -0.0216 0.6879 1.0000
2.250 0.3819 0.01113 0.00294 -0.0208 0.6450 1.0000
2.500 0.4072 0.01139 0.00307 -0.0199 0.5965 1.0000
2.750 0.4324 0.01169 0.00323 -0.0190 0.5399 1.0000
3.000 0.4575 0.01208 0.00339 -0.0182 0.4765 1.0000
3.250 0.4825 0.01255 0.00360 -0.0176 0.4087 1.0000
3.500 0.5076 0.01311 0.00389 -0.0171 0.3414 1.0000
3.750 0.5328 0.01372 0.00425 -0.0167 0.2807 1.0000
4.000 0.5581 0.01436 0.00474 -0.0164 0.2298 1.0000
4.250 0.5836 0.01501 0.00525 -0.0161 0.1893 1.0000
4.500 0.6091 0.01568 0.00581 -0.0158 0.1581 1.0000
4.750 0.6346 0.01637 0.00646 -0.0155 0.1343 1.0000
5.000 0.6598 0.01713 0.00718 -0.0152 0.1143 1.0000
5.250 0.6850 0.01793 0.00802 -0.0149 0.1000 1.0000
5.500 0.7101 0.01875 0.00888 -0.0145 0.0863 1.0000
5.750 0.7347 0.01967 0.00984 -0.0141 0.0752 1.0000
6.000 0.7597 0.02066 0.01101 -0.0136 0.0663 1.0000
6.250 0.7842 0.02170 0.01221 -0.0132 0.0575 1.0000
6.500 0.8082 0.02291 0.01351 -0.0128 0.0515 1.0000
6.750 0.8320 0.02454 0.01537 -0.0121 0.0466 1.0000
7.000 0.8559 0.02567 0.01667 -0.0118 0.0407 1.0000
7.250 0.8780 0.02774 0.01891 -0.0113 0.0375 1.0000
7.500 0.9005 0.03021 0.02187 -0.0105 0.0350 1.0000
7.750 0.9217 0.03258 0.02468 -0.0100 0.0320 1.0000
8.000 0.9422 0.03408 0.02640 -0.0098 0.0289 1.0000
8.250 0.9581 0.03768 0.03040 -0.0094 0.0274 1.0000
8.500 0.9708 0.04211 0.03554 -0.0091 0.0265 1.0000
8.750 0.9769 0.04761 0.04174 -0.0093 0.0258 1.0000
9.000 0.9754 0.05393 0.04864 -0.0104 0.0255 1.0000
9.250 0.9663 0.06078 0.05593 -0.0128 0.0254 1.0000
9.500 0.9504 0.06798 0.06341 -0.0171 0.0256 1.0000
9.750 0.9309 0.07679 0.07234 -0.0259 0.0260 1.0000
10.000 0.9133 0.08828 0.08381 -0.0356 0.0265 1.0000
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Polar data table (+)
Polar graphs
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