AG04 (ag04-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 200,000 Max Cl/Cd: 58.86 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag04-il-200000.txt Download as CSV file: xf-ag04-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5651 0.09923 0.09586 0.0147 1.0000 0.0367
-8.000 -0.5626 0.09522 0.09190 0.0113 1.0000 0.0382
-7.750 -0.5608 0.09093 0.08766 0.0045 1.0000 0.0396
-7.500 -0.5497 0.08545 0.08220 -0.0060 1.0000 0.0402
-7.250 -0.5355 0.07950 0.07620 -0.0142 1.0000 0.0404
-7.000 -0.5332 0.07184 0.06855 -0.0180 1.0000 0.0413
-6.750 -0.5254 0.06921 0.06596 -0.0155 1.0000 0.0426
-6.500 -0.5124 0.06630 0.06305 -0.0160 1.0000 0.0448
-6.250 -0.4934 0.06124 0.05786 -0.0218 1.0000 0.0497
-6.000 -0.4701 0.05167 0.04785 -0.0327 1.0000 0.0540
-5.750 -0.4556 0.04999 0.04632 -0.0309 1.0000 0.0568
-5.500 -0.4345 0.04602 0.04218 -0.0330 1.0000 0.0605
-5.250 -0.4103 0.03993 0.03556 -0.0369 1.0000 0.0678
-5.000 -0.3887 0.03687 0.03245 -0.0372 1.0000 0.0702
-4.750 -0.3642 0.03325 0.02854 -0.0380 1.0000 0.0728
-4.500 -0.3284 0.02071 0.01400 -0.0371 1.0000 0.0281
-4.250 -0.3018 0.01845 0.01132 -0.0365 1.0000 0.0285
-4.000 -0.2756 0.01606 0.00862 -0.0358 1.0000 0.0300
-3.750 -0.2498 0.01490 0.00744 -0.0355 1.0000 0.0364
-3.500 -0.2236 0.01347 0.00586 -0.0347 1.0000 0.0422
-3.250 -0.1977 0.01245 0.00489 -0.0342 1.0000 0.0577
-3.000 -0.1716 0.01161 0.00413 -0.0338 1.0000 0.0906
-2.750 -0.1459 0.01089 0.00362 -0.0335 1.0000 0.1372
-2.500 -0.1202 0.01031 0.00328 -0.0332 1.0000 0.1946
-2.250 -0.0948 0.00972 0.00302 -0.0330 1.0000 0.2770
-2.000 -0.0696 0.00913 0.00287 -0.0327 1.0000 0.3933
-1.750 -0.0453 0.00847 0.00278 -0.0322 1.0000 0.5403
-1.500 -0.0264 0.00752 0.00274 -0.0297 1.0000 0.7752
-1.250 0.0091 0.00721 0.00261 -0.0306 1.0000 1.0000
-1.000 0.0342 0.00727 0.00253 -0.0302 1.0000 1.0000
-0.750 0.0592 0.00735 0.00251 -0.0299 1.0000 1.0000
-0.500 0.0840 0.00747 0.00254 -0.0296 1.0000 1.0000
-0.250 0.1255 0.00754 0.00252 -0.0327 0.9914 1.0000
0.000 0.1744 0.00755 0.00247 -0.0371 0.9772 1.0000
0.250 0.2194 0.00753 0.00241 -0.0405 0.9592 1.0000
0.500 0.2591 0.00751 0.00234 -0.0426 0.9362 1.0000
0.750 0.2916 0.00751 0.00229 -0.0429 0.9078 1.0000
1.000 0.3184 0.00755 0.00225 -0.0420 0.8756 1.0000
1.250 0.3428 0.00763 0.00222 -0.0406 0.8415 1.0000
1.500 0.3670 0.00776 0.00223 -0.0392 0.8054 1.0000
1.750 0.3915 0.00792 0.00225 -0.0379 0.7684 1.0000
2.000 0.4163 0.00812 0.00229 -0.0368 0.7309 1.0000
2.250 0.4415 0.00834 0.00235 -0.0359 0.6922 1.0000
2.500 0.4669 0.00859 0.00244 -0.0350 0.6524 1.0000
2.750 0.4925 0.00886 0.00258 -0.0343 0.6119 1.0000
3.000 0.5181 0.00915 0.00271 -0.0337 0.5702 1.0000
3.250 0.5438 0.00946 0.00287 -0.0331 0.5277 1.0000
3.500 0.5695 0.00981 0.00305 -0.0326 0.4853 1.0000
3.750 0.5953 0.01018 0.00330 -0.0321 0.4430 1.0000
4.000 0.6210 0.01058 0.00355 -0.0317 0.4022 1.0000
4.250 0.6469 0.01099 0.00384 -0.0313 0.3631 1.0000
4.500 0.6726 0.01143 0.00416 -0.0310 0.3261 1.0000
4.750 0.6983 0.01189 0.00451 -0.0307 0.2910 1.0000
5.000 0.7241 0.01236 0.00493 -0.0303 0.2577 1.0000
5.250 0.7497 0.01287 0.00535 -0.0301 0.2250 1.0000
5.500 0.7750 0.01343 0.00582 -0.0297 0.1943 1.0000
5.750 0.8003 0.01402 0.00635 -0.0294 0.1629 1.0000
6.000 0.8252 0.01472 0.00701 -0.0291 0.1329 1.0000
6.250 0.8497 0.01552 0.00773 -0.0287 0.1046 1.0000
6.500 0.8735 0.01653 0.00868 -0.0282 0.0821 1.0000
6.750 0.8971 0.01755 0.00968 -0.0276 0.0646 1.0000
7.000 0.9200 0.01879 0.01095 -0.0269 0.0524 1.0000
7.250 0.9425 0.02017 0.01243 -0.0261 0.0431 1.0000
7.500 0.9630 0.02218 0.01449 -0.0251 0.0367 1.0000
7.750 0.9864 0.02326 0.01578 -0.0244 0.0310 1.0000
8.000 1.0038 0.02688 0.01957 -0.0231 0.0274 1.0000
8.250 1.0262 0.02834 0.02137 -0.0221 0.0251 1.0000
8.500 1.0468 0.02990 0.02318 -0.0213 0.0221 1.0000
8.750 1.0645 0.03243 0.02600 -0.0203 0.0207 1.0000
9.000 1.0787 0.03568 0.02958 -0.0191 0.0198 1.0000
9.250 1.0878 0.03986 0.03422 -0.0178 0.0194 1.0000
9.500 1.0925 0.04430 0.03914 -0.0165 0.0193 1.0000
9.750 1.0921 0.04888 0.04421 -0.0152 0.0196 1.0000
10.000 1.0790 0.05484 0.05074 -0.0141 0.0204 1.0000
10.250 1.0478 0.06151 0.05787 -0.0142 0.0213 1.0000
10.500 1.0212 0.06816 0.06478 -0.0182 0.0217 1.0000
10.750 0.9954 0.07748 0.07429 -0.0269 0.0221 1.0000
11.000 0.9628 0.09220 0.08914 -0.0397 0.0231 1.0000
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Polar data table (+)
Polar graphs
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