AG10 (ag10-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 200,000 Max Cl/Cd: 52.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag10-il-200000-n5.txt Download as CSV file: xf-ag10-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG10
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 -0.6175 0.11134 0.10776 0.0296 1.0000 0.0241
-8.500 -0.6152 0.10749 0.10394 0.0264 1.0000 0.0242
-8.250 -0.6119 0.10354 0.10001 0.0234 1.0000 0.0243
-8.000 -0.6082 0.09953 0.09603 0.0203 1.0000 0.0244
-7.750 -0.6023 0.09526 0.09178 0.0165 1.0000 0.0244
-7.500 -0.5927 0.09056 0.08709 0.0118 1.0000 0.0245
-7.250 -0.5811 0.08567 0.08220 0.0070 1.0000 0.0245
-7.000 -0.5680 0.08071 0.07722 0.0025 1.0000 0.0245
-6.750 -0.5647 0.07659 0.07311 0.0052 1.0000 0.0181
-6.250 -0.5263 0.06046 0.05676 -0.0111 1.0000 0.0149
-6.000 -0.5050 0.05486 0.05103 -0.0157 1.0000 0.0148
-5.750 -0.4793 0.04718 0.04309 -0.0212 1.0000 0.0149
-5.500 -0.4574 0.04520 0.04103 -0.0227 1.0000 0.0159
-5.250 -0.4315 0.04081 0.03642 -0.0253 1.0000 0.0169
-5.000 -0.4023 0.03285 0.02793 -0.0286 1.0000 0.0167
-4.750 -0.3729 0.02495 0.01913 -0.0306 1.0000 0.0167
-4.500 -0.3443 0.02083 0.01426 -0.0312 1.0000 0.0173
-4.250 -0.3160 0.01822 0.01107 -0.0312 1.0000 0.0183
-4.000 -0.2883 0.01666 0.00917 -0.0312 1.0000 0.0198
-3.750 -0.2610 0.01599 0.00842 -0.0311 1.0000 0.0219
-3.500 -0.2333 0.01483 0.00705 -0.0309 1.0000 0.0236
-3.250 -0.2058 0.01379 0.00589 -0.0307 1.0000 0.0255
-3.000 -0.1785 0.01329 0.00537 -0.0305 1.0000 0.0289
-2.750 -0.1510 0.01257 0.00457 -0.0303 1.0000 0.0320
-2.500 -0.1237 0.01204 0.00407 -0.0301 1.0000 0.0367
-2.250 -0.0963 0.01152 0.00353 -0.0299 1.0000 0.0426
-2.000 -0.0689 0.01117 0.00316 -0.0297 1.0000 0.0507
-1.750 -0.0416 0.01078 0.00283 -0.0295 1.0000 0.0623
-1.500 -0.0144 0.01045 0.00258 -0.0293 1.0000 0.0786
-1.250 0.0126 0.01015 0.00238 -0.0291 1.0000 0.1012
-1.000 0.0395 0.00987 0.00223 -0.0289 1.0000 0.1320
-0.500 0.0926 0.00915 0.00208 -0.0286 1.0000 0.2701
-0.250 0.1173 0.00801 0.00205 -0.0284 0.9989 0.5796
0.000 0.1535 0.00704 0.00196 -0.0291 0.9668 1.0000
0.250 0.1923 0.00708 0.00188 -0.0312 0.9222 1.0000
0.500 0.2243 0.00718 0.00181 -0.0314 0.8590 1.0000
0.750 0.2486 0.00739 0.00174 -0.0298 0.7855 1.0000
1.000 0.2721 0.00771 0.00171 -0.0283 0.7072 1.0000
1.250 0.2968 0.00810 0.00172 -0.0272 0.6297 1.0000
1.500 0.3224 0.00848 0.00176 -0.0265 0.5587 1.0000
1.750 0.3488 0.00885 0.00183 -0.0261 0.4989 1.0000
2.000 0.3756 0.00919 0.00193 -0.0258 0.4502 1.0000
2.250 0.4026 0.00950 0.00206 -0.0256 0.4090 1.0000
2.500 0.4298 0.00981 0.00221 -0.0255 0.3739 1.0000
2.750 0.4571 0.01009 0.00237 -0.0253 0.3424 1.0000
3.000 0.4843 0.01038 0.00255 -0.0252 0.3124 1.0000
3.250 0.5116 0.01068 0.00274 -0.0250 0.2842 1.0000
3.500 0.5388 0.01099 0.00298 -0.0249 0.2569 1.0000
3.750 0.5660 0.01131 0.00322 -0.0248 0.2299 1.0000
4.000 0.5931 0.01165 0.00349 -0.0246 0.2037 1.0000
4.250 0.6201 0.01202 0.00380 -0.0245 0.1788 1.0000
4.500 0.6470 0.01242 0.00413 -0.0244 0.1544 1.0000
4.750 0.6738 0.01284 0.00449 -0.0243 0.1307 1.0000
5.000 0.7005 0.01330 0.00490 -0.0241 0.1084 1.0000
5.250 0.7270 0.01383 0.00537 -0.0240 0.0872 1.0000
5.500 0.7534 0.01437 0.00589 -0.0238 0.0676 1.0000
5.750 0.7795 0.01504 0.00649 -0.0237 0.0514 1.0000
6.000 0.8055 0.01573 0.00721 -0.0234 0.0394 1.0000
6.250 0.8312 0.01652 0.00804 -0.0232 0.0314 1.0000
6.500 0.8566 0.01739 0.00894 -0.0229 0.0256 1.0000
6.750 0.8819 0.01824 0.00994 -0.0225 0.0224 1.0000
7.000 0.9061 0.01938 0.01116 -0.0222 0.0200 1.0000
7.250 0.9309 0.02030 0.01226 -0.0218 0.0178 1.0000
7.500 0.9549 0.02130 0.01334 -0.0214 0.0161 1.0000
7.750 0.9775 0.02275 0.01494 -0.0209 0.0152 1.0000
8.000 1.0001 0.02425 0.01669 -0.0203 0.0144 1.0000
8.250 1.0220 0.02591 0.01859 -0.0196 0.0137 1.0000
8.500 1.0430 0.02772 0.02064 -0.0190 0.0132 1.0000
8.750 1.0629 0.02967 0.02284 -0.0184 0.0127 1.0000
9.000 1.0815 0.03174 0.02518 -0.0178 0.0123 1.0000
9.250 1.0973 0.03426 0.02791 -0.0172 0.0119 1.0000
9.500 1.1107 0.03733 0.03153 -0.0164 0.0114 1.0000
9.750 1.1192 0.04104 0.03579 -0.0158 0.0110 1.0000
10.000 1.1218 0.04534 0.04059 -0.0154 0.0107 1.0000
10.250 1.1160 0.05045 0.04616 -0.0156 0.0106 1.0000
10.500 1.1009 0.05603 0.05210 -0.0167 0.0106 1.0000
10.750 1.0793 0.06304 0.05938 -0.0220 0.0107 1.0000
11.000 1.0550 0.07626 0.07281 -0.0358 0.0109 1.0000
11.250 1.0282 0.08893 0.08554 -0.0450 0.0114 1.0000
11.500 1.0052 0.09946 0.09605 -0.0510 0.0117 1.0000
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Polar data table (+)
Polar graphs
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