AG09 (ag09-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 200,000 Max Cl/Cd: 55.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag09-il-200000-n5.txt Download as CSV file: xf-ag09-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5980 0.11062 0.10714 0.0221 1.0000 0.0215
-8.500 -0.5932 0.10665 0.10319 0.0201 1.0000 0.0216
-8.250 -0.5885 0.10264 0.09920 0.0179 1.0000 0.0216
-8.000 -0.5837 0.09859 0.09518 0.0155 1.0000 0.0216
-7.750 -0.5775 0.09433 0.09094 0.0124 1.0000 0.0216
-7.500 -0.5684 0.08969 0.08631 0.0084 1.0000 0.0215
-7.250 -0.5679 0.08592 0.08256 0.0124 1.0000 0.0191
-7.000 -0.5548 0.07678 0.07338 0.0012 1.0000 0.0146
-6.750 -0.5425 0.07184 0.06842 -0.0031 1.0000 0.0143
-6.500 -0.5261 0.06643 0.06296 -0.0084 1.0000 0.0141
-6.250 -0.5068 0.06062 0.05707 -0.0138 1.0000 0.0140
-6.000 -0.4848 0.05441 0.05072 -0.0192 1.0000 0.0139
-5.750 -0.4581 0.04665 0.04271 -0.0250 1.0000 0.0146
-5.500 -0.4338 0.03979 0.03554 -0.0290 1.0000 0.0154
-5.250 -0.4074 0.03118 0.02633 -0.0322 1.0000 0.0154
-5.000 -0.3810 0.02500 0.01938 -0.0337 1.0000 0.0154
-4.750 -0.3545 0.02170 0.01554 -0.0341 1.0000 0.0159
-4.500 -0.3276 0.01949 0.01288 -0.0342 1.0000 0.0166
-4.250 -0.3005 0.01769 0.01073 -0.0341 1.0000 0.0176
-4.000 -0.2733 0.01626 0.00900 -0.0339 1.0000 0.0191
-3.750 -0.2460 0.01544 0.00794 -0.0336 1.0000 0.0215
-3.500 -0.2193 0.01403 0.00639 -0.0333 1.0000 0.0237
-3.250 -0.1923 0.01325 0.00552 -0.0330 1.0000 0.0263
-3.000 -0.1653 0.01267 0.00483 -0.0327 1.0000 0.0304
-2.750 -0.1386 0.01200 0.00417 -0.0325 1.0000 0.0364
-2.500 -0.1117 0.01150 0.00361 -0.0322 1.0000 0.0434
-2.250 -0.0849 0.01114 0.00324 -0.0319 1.0000 0.0542
-2.000 -0.0583 0.01078 0.00291 -0.0316 1.0000 0.0672
-1.750 -0.0318 0.01047 0.00267 -0.0313 1.0000 0.0822
-1.500 -0.0055 0.01020 0.00248 -0.0310 1.0000 0.1009
-1.250 0.0208 0.00996 0.00229 -0.0307 1.0000 0.1215
-1.000 0.0468 0.00971 0.00217 -0.0304 1.0000 0.1512
-0.750 0.0786 0.00941 0.00206 -0.0314 0.9922 0.1999
-0.500 0.1158 0.00885 0.00197 -0.0337 0.9718 0.3321
-0.250 0.1488 0.00700 0.00191 -0.0341 0.9475 1.0000
0.000 0.1848 0.00703 0.00181 -0.0355 0.9119 1.0000
0.250 0.2152 0.00709 0.00171 -0.0355 0.8684 1.0000
0.500 0.2412 0.00721 0.00165 -0.0345 0.8213 1.0000
0.750 0.2659 0.00739 0.00160 -0.0333 0.7735 1.0000
1.000 0.2908 0.00760 0.00158 -0.0322 0.7246 1.0000
1.250 0.3161 0.00785 0.00158 -0.0313 0.6752 1.0000
1.500 0.3418 0.00812 0.00161 -0.0306 0.6247 1.0000
1.750 0.3678 0.00841 0.00167 -0.0300 0.5745 1.0000
2.000 0.3940 0.00871 0.00175 -0.0296 0.5259 1.0000
2.250 0.4204 0.00902 0.00185 -0.0292 0.4799 1.0000
2.500 0.4469 0.00933 0.00198 -0.0289 0.4381 1.0000
2.750 0.4736 0.00964 0.00216 -0.0287 0.4003 1.0000
3.000 0.5003 0.00996 0.00233 -0.0285 0.3652 1.0000
3.250 0.5272 0.01027 0.00253 -0.0283 0.3334 1.0000
3.500 0.5540 0.01059 0.00276 -0.0281 0.3036 1.0000
3.750 0.5808 0.01092 0.00303 -0.0279 0.2752 1.0000
4.000 0.6075 0.01126 0.00330 -0.0277 0.2485 1.0000
4.250 0.6342 0.01162 0.00360 -0.0275 0.2226 1.0000
4.500 0.6607 0.01200 0.00392 -0.0274 0.1971 1.0000
4.750 0.6872 0.01240 0.00427 -0.0272 0.1716 1.0000
5.000 0.7136 0.01283 0.00469 -0.0270 0.1457 1.0000
5.250 0.7398 0.01333 0.00512 -0.0268 0.1186 1.0000
5.500 0.7656 0.01392 0.00561 -0.0267 0.0901 1.0000
5.750 0.7911 0.01459 0.00619 -0.0264 0.0632 1.0000
6.000 0.8162 0.01543 0.00696 -0.0262 0.0413 1.0000
6.250 0.8413 0.01630 0.00786 -0.0258 0.0293 1.0000
6.500 0.8660 0.01725 0.00888 -0.0254 0.0221 1.0000
6.750 0.8905 0.01828 0.01008 -0.0249 0.0190 1.0000
7.000 0.9148 0.01924 0.01116 -0.0245 0.0163 1.0000
7.250 0.9374 0.02059 0.01267 -0.0240 0.0140 1.0000
7.500 0.9605 0.02185 0.01413 -0.0234 0.0129 1.0000
7.750 0.9827 0.02333 0.01581 -0.0227 0.0120 1.0000
8.000 1.0042 0.02495 0.01763 -0.0220 0.0113 1.0000
8.250 1.0250 0.02672 0.01962 -0.0212 0.0108 1.0000
8.500 1.0446 0.02870 0.02185 -0.0205 0.0104 1.0000
8.750 1.0623 0.03107 0.02450 -0.0197 0.0101 1.0000
9.000 1.0772 0.03401 0.02783 -0.0189 0.0098 1.0000
9.250 1.0882 0.03762 0.03186 -0.0180 0.0097 1.0000
9.750 1.0975 0.04569 0.04085 -0.0165 0.0094 1.0000
10.000 1.0957 0.04985 0.04545 -0.0162 0.0092 1.0000
10.250 1.0858 0.05444 0.05040 -0.0165 0.0091 1.0000
10.500 1.0691 0.05945 0.05566 -0.0184 0.0091 1.0000
10.750 1.0517 0.06677 0.06318 -0.0252 0.0092 1.0000
11.000 1.0346 0.07635 0.07289 -0.0341 0.0094 1.0000
11.250 0.9117 0.07222 0.06889 -0.0238 0.0101 1.0000
11.500 0.8707 0.08636 0.08316 -0.0309 0.0104 1.0000
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Polar data table (+)
Polar graphs
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