AG10 (ag10-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 200,000 Max Cl/Cd: 52.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag10-il-200000.txt Download as CSV file: xf-ag10-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6014 0.10172 0.09823 0.0266 1.0000 0.0347
-7.750 -0.5966 0.09819 0.09473 0.0247 1.0000 0.0356
-7.500 -0.5922 0.09460 0.09115 0.0223 1.0000 0.0365
-7.250 -0.5848 0.09063 0.08721 0.0180 1.0000 0.0378
-7.000 -0.5678 0.08568 0.08223 0.0065 1.0000 0.0395
-6.750 -0.5432 0.08021 0.07665 -0.0054 1.0000 0.0401
-6.500 -0.5339 0.07389 0.07033 -0.0078 1.0000 0.0407
-6.250 -0.5257 0.07040 0.06688 -0.0060 1.0000 0.0416
-6.000 -0.5113 0.06708 0.06356 -0.0066 1.0000 0.0429
-5.750 -0.4921 0.06322 0.05964 -0.0095 1.0000 0.0450
-5.500 -0.4488 0.05757 0.05355 -0.0206 1.0000 0.0505
-5.250 -0.4317 0.05113 0.04703 -0.0232 1.0000 0.0518
-5.000 -0.4174 0.04898 0.04498 -0.0220 1.0000 0.0543
-4.750 -0.3913 0.04568 0.04153 -0.0241 1.0000 0.0597
-4.500 -0.3595 0.04012 0.03553 -0.0281 1.0000 0.0649
-4.250 -0.3371 0.03749 0.03290 -0.0285 1.0000 0.0674
-4.000 -0.3035 0.03411 0.02887 -0.0306 1.0000 0.0775
-3.750 -0.2653 0.02383 0.01737 -0.0312 1.0000 0.0403
-3.500 -0.2369 0.02019 0.01324 -0.0316 1.0000 0.0409
-3.250 -0.2091 0.01796 0.01077 -0.0317 1.0000 0.0429
-3.000 -0.1806 0.01625 0.00880 -0.0314 1.0000 0.0446
-2.750 -0.1524 0.01523 0.00757 -0.0310 1.0000 0.0491
-2.500 -0.1245 0.01374 0.00593 -0.0307 1.0000 0.0533
-2.250 -0.0970 0.01305 0.00522 -0.0304 1.0000 0.0607
-2.000 -0.0697 0.01208 0.00428 -0.0301 1.0000 0.0694
-1.750 -0.0424 0.01142 0.00368 -0.0298 1.0000 0.0835
-1.500 -0.0152 0.01088 0.00318 -0.0295 1.0000 0.1043
-1.250 0.0119 0.01025 0.00274 -0.0293 1.0000 0.1377
-1.000 0.0388 0.00961 0.00245 -0.0292 1.0000 0.2036
-0.750 0.0585 0.00697 0.00231 -0.0272 1.0000 1.0000
-0.500 0.0853 0.00698 0.00215 -0.0267 1.0000 1.0000
-0.250 0.1118 0.00701 0.00206 -0.0263 1.0000 1.0000
0.000 0.1382 0.00704 0.00202 -0.0259 1.0000 1.0000
0.250 0.1644 0.00709 0.00202 -0.0255 1.0000 1.0000
0.500 0.1904 0.00715 0.00205 -0.0252 1.0000 1.0000
0.750 0.2164 0.00723 0.00213 -0.0248 1.0000 1.0000
1.000 0.2424 0.00733 0.00224 -0.0245 1.0000 1.0000
1.250 0.2942 0.00732 0.00224 -0.0295 0.9717 1.0000
1.500 0.3392 0.00732 0.00223 -0.0325 0.9172 1.0000
1.750 0.3673 0.00745 0.00220 -0.0314 0.8350 1.0000
2.000 0.3883 0.00781 0.00220 -0.0288 0.7389 1.0000
2.250 0.4110 0.00832 0.00227 -0.0271 0.6394 1.0000
2.500 0.4355 0.00886 0.00238 -0.0262 0.5529 1.0000
2.750 0.4613 0.00936 0.00256 -0.0256 0.4859 1.0000
3.000 0.4875 0.00982 0.00276 -0.0253 0.4338 1.0000
3.250 0.5142 0.01025 0.00301 -0.0250 0.3901 1.0000
3.500 0.5410 0.01064 0.00326 -0.0248 0.3510 1.0000
3.750 0.5678 0.01106 0.00353 -0.0246 0.3153 1.0000
4.000 0.5947 0.01144 0.00382 -0.0244 0.2801 1.0000
4.250 0.6215 0.01186 0.00416 -0.0242 0.2467 1.0000
4.500 0.6482 0.01232 0.00450 -0.0241 0.2146 1.0000
4.750 0.6748 0.01282 0.00489 -0.0239 0.1835 1.0000
5.000 0.7014 0.01334 0.00534 -0.0237 0.1530 1.0000
5.250 0.7277 0.01395 0.00589 -0.0236 0.1230 1.0000
5.500 0.7538 0.01469 0.00655 -0.0233 0.0943 1.0000
5.750 0.7794 0.01565 0.00743 -0.0230 0.0703 1.0000
6.000 0.8047 0.01673 0.00847 -0.0227 0.0542 1.0000
6.250 0.8297 0.01788 0.00966 -0.0222 0.0441 1.0000
6.500 0.8540 0.01949 0.01137 -0.0215 0.0386 1.0000
6.750 0.8784 0.02087 0.01277 -0.0210 0.0346 1.0000
7.000 0.9023 0.02273 0.01483 -0.0203 0.0313 1.0000
7.250 0.9266 0.02450 0.01685 -0.0196 0.0293 1.0000
7.500 0.9499 0.02657 0.01918 -0.0189 0.0281 1.0000
7.750 0.9719 0.02910 0.02201 -0.0182 0.0273 1.0000
8.000 0.9918 0.03236 0.02570 -0.0174 0.0271 1.0000
8.250 1.0055 0.03767 0.03187 -0.0162 0.0280 1.0000
8.500 1.0080 0.04543 0.04057 -0.0155 0.0297 1.0000
8.750 1.0070 0.05233 0.04802 -0.0157 0.0307 1.0000
9.000 1.0018 0.05888 0.05493 -0.0166 0.0316 1.0000
9.250 0.9941 0.06500 0.06125 -0.0179 0.0324 1.0000
9.500 0.7760 0.08885 0.08568 -0.0312 0.0653 1.0000
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