AG09 (ag09-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 100,000 Max Cl/Cd: 44.1 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag09-il-100000-n5.txt Download as CSV file: xf-ag09-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG09
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4663 0.09016 0.08559 0.0094 1.0000 0.0487
-7.750 -0.4657 0.08627 0.08174 0.0080 1.0000 0.0496
-7.250 -0.5606 0.09033 0.08563 0.0115 1.0000 0.0456
-7.000 -0.5506 0.08644 0.08175 0.0084 1.0000 0.0472
-6.750 -0.5388 0.08207 0.07739 0.0041 1.0000 0.0479
-6.250 -0.5015 0.06767 0.06277 -0.0118 1.0000 0.0297
-6.000 -0.4849 0.06297 0.05801 -0.0149 1.0000 0.0287
-5.750 -0.4645 0.05779 0.05271 -0.0189 1.0000 0.0278
-5.500 -0.4414 0.05230 0.04701 -0.0229 1.0000 0.0271
-5.250 -0.4162 0.04664 0.04108 -0.0266 1.0000 0.0265
-5.000 -0.3895 0.04088 0.03496 -0.0297 1.0000 0.0262
-4.750 -0.3620 0.03548 0.02910 -0.0319 1.0000 0.0265
-4.500 -0.3337 0.03071 0.02371 -0.0333 1.0000 0.0287
-4.250 -0.3049 0.02662 0.01886 -0.0340 1.0000 0.0302
-4.000 -0.2770 0.02342 0.01502 -0.0341 1.0000 0.0311
-3.750 -0.2503 0.02117 0.01248 -0.0342 1.0000 0.0329
-3.500 -0.2233 0.01991 0.01100 -0.0340 1.0000 0.0370
-3.250 -0.1956 0.01850 0.00916 -0.0335 1.0000 0.0417
-3.000 -0.1691 0.01708 0.00770 -0.0332 1.0000 0.0460
-2.750 -0.1422 0.01627 0.00673 -0.0328 1.0000 0.0550
-2.500 -0.1159 0.01537 0.00585 -0.0325 1.0000 0.0639
-2.250 -0.0895 0.01474 0.00518 -0.0321 1.0000 0.0784
-2.000 -0.0633 0.01413 0.00456 -0.0317 1.0000 0.0943
-1.750 -0.0373 0.01359 0.00413 -0.0313 1.0000 0.1144
-1.500 -0.0113 0.01313 0.00374 -0.0309 1.0000 0.1403
-1.250 0.0147 0.01268 0.00340 -0.0306 1.0000 0.1747
-1.000 0.0404 0.01217 0.00317 -0.0303 1.0000 0.2393
-0.750 0.0652 0.00976 0.00301 -0.0291 1.0000 1.0000
-0.500 0.0908 0.00979 0.00284 -0.0285 1.0000 1.0000
-0.250 0.1161 0.00984 0.00275 -0.0280 1.0000 1.0000
0.000 0.1412 0.00990 0.00270 -0.0276 1.0000 1.0000
0.250 0.1662 0.00998 0.00271 -0.0271 1.0000 1.0000
0.500 0.2100 0.01005 0.00271 -0.0305 0.9754 1.0000
0.750 0.2519 0.01012 0.00272 -0.0333 0.9446 1.0000
1.000 0.2906 0.01018 0.00272 -0.0351 0.9060 1.0000
1.250 0.3246 0.01027 0.00272 -0.0358 0.8601 1.0000
1.500 0.3530 0.01041 0.00273 -0.0351 0.8092 1.0000
1.750 0.3784 0.01062 0.00278 -0.0338 0.7563 1.0000
2.000 0.4030 0.01088 0.00284 -0.0324 0.7019 1.0000
2.250 0.4278 0.01118 0.00293 -0.0313 0.6464 1.0000
2.500 0.4528 0.01152 0.00306 -0.0303 0.5911 1.0000
2.750 0.4781 0.01190 0.00326 -0.0295 0.5377 1.0000
3.000 0.5036 0.01231 0.00347 -0.0288 0.4880 1.0000
3.250 0.5292 0.01273 0.00372 -0.0282 0.4426 1.0000
3.500 0.5549 0.01316 0.00401 -0.0277 0.4015 1.0000
3.750 0.5807 0.01362 0.00439 -0.0273 0.3640 1.0000
4.000 0.6067 0.01407 0.00476 -0.0269 0.3293 1.0000
4.250 0.6326 0.01455 0.00517 -0.0266 0.2972 1.0000
4.500 0.6584 0.01505 0.00561 -0.0262 0.2668 1.0000
4.750 0.6842 0.01556 0.00610 -0.0259 0.2369 1.0000
5.000 0.7100 0.01610 0.00668 -0.0256 0.2075 1.0000
5.250 0.7356 0.01669 0.00725 -0.0253 0.1773 1.0000
5.500 0.7609 0.01735 0.00788 -0.0250 0.1456 1.0000
5.750 0.7859 0.01813 0.00860 -0.0247 0.1123 1.0000
6.000 0.8103 0.01912 0.00955 -0.0244 0.0803 1.0000
6.250 0.8341 0.02036 0.01075 -0.0240 0.0569 1.0000
6.500 0.8573 0.02173 0.01214 -0.0235 0.0428 1.0000
6.750 0.8801 0.02327 0.01385 -0.0227 0.0355 1.0000
7.000 0.9015 0.02501 0.01565 -0.0221 0.0301 1.0000
7.250 0.9243 0.02655 0.01749 -0.0213 0.0263 1.0000
7.500 0.9457 0.02848 0.01968 -0.0205 0.0241 1.0000
7.750 0.9659 0.03068 0.02208 -0.0198 0.0226 1.0000
8.000 0.9837 0.03379 0.02545 -0.0190 0.0212 1.0000
8.250 1.0028 0.03628 0.02847 -0.0182 0.0197 1.0000
8.500 1.0189 0.03928 0.03196 -0.0174 0.0183 1.0000
8.750 1.0308 0.04303 0.03623 -0.0167 0.0176 1.0000
9.000 1.0378 0.04739 0.04112 -0.0162 0.0173 1.0000
9.250 1.0385 0.05228 0.04652 -0.0160 0.0172 1.0000
9.500 1.0321 0.05769 0.05237 -0.0165 0.0171 1.0000
9.750 1.0176 0.06349 0.05852 -0.0181 0.0172 1.0000
10.000 0.9962 0.07010 0.06535 -0.0224 0.0174 1.0000
10.250 0.9724 0.08104 0.07645 -0.0333 0.0179 1.0000
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Polar data table (+)
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