AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 200,000 Max Cl/Cd: 58.07 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46c03-il-200000.txt Download as CSV file: xf-ag46c03-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -03f
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.4770 0.08412 0.08101 0.0108 1.0000 0.0355
-6.750 -0.4755 0.08025 0.07716 0.0098 1.0000 0.0363
-6.500 -0.4750 0.07626 0.07320 0.0084 1.0000 0.0372
-6.250 -0.4755 0.07216 0.06914 0.0066 1.0000 0.0381
-6.000 -0.4760 0.06781 0.06482 0.0037 1.0000 0.0390
-5.750 -0.4723 0.06267 0.05968 -0.0011 1.0000 0.0401
-5.500 -0.4650 0.05690 0.05388 -0.0074 1.0000 0.0418
-5.250 -0.4476 0.05014 0.04684 -0.0185 1.0000 0.0441
-5.000 -0.4322 0.04508 0.04148 -0.0220 1.0000 0.0445
-4.750 -0.4280 0.03785 0.03442 -0.0223 1.0000 0.0463
-4.500 -0.4130 0.03450 0.03108 -0.0224 1.0000 0.0483
-4.250 -0.3944 0.03059 0.02703 -0.0240 1.0000 0.0516
-4.000 -0.3705 0.02489 0.02071 -0.0275 1.0000 0.0585
-3.750 -0.3527 0.02191 0.01781 -0.0274 1.0000 0.0612
-3.500 -0.3293 0.01871 0.01420 -0.0285 1.0000 0.0725
-3.250 -0.3065 0.01649 0.01174 -0.0288 1.0000 0.0856
-3.000 -0.2850 0.02384 0.01777 -0.0285 1.0000 0.0421
-2.750 -0.2542 0.02030 0.01345 -0.0275 1.0000 0.0329
-2.500 -0.2266 0.01792 0.01078 -0.0271 1.0000 0.0318
-2.250 -0.1988 0.01606 0.00865 -0.0266 1.0000 0.0320
-2.000 -0.1716 0.01405 0.00649 -0.0261 1.0000 0.0336
-1.750 -0.1449 0.01302 0.00548 -0.0258 1.0000 0.0408
-1.500 -0.1180 0.01182 0.00428 -0.0253 1.0000 0.0490
-1.250 -0.0907 0.01091 0.00347 -0.0251 1.0000 0.0748
-1.000 -0.0642 0.00956 0.00287 -0.0252 1.0000 0.2261
-0.750 -0.0425 0.00787 0.00273 -0.0247 1.0000 0.6053
-0.500 -0.0127 0.00687 0.00261 -0.0234 1.0000 1.0000
-0.250 0.0137 0.00688 0.00247 -0.0232 1.0000 1.0000
0.000 0.0397 0.00691 0.00240 -0.0231 1.0000 1.0000
0.250 0.0867 0.00696 0.00230 -0.0273 0.9685 1.0000
0.500 0.1304 0.00701 0.00218 -0.0304 0.9229 1.0000
0.750 0.1628 0.00710 0.00207 -0.0308 0.8756 1.0000
1.000 0.1883 0.00725 0.00201 -0.0297 0.8374 1.0000
1.250 0.2132 0.00744 0.00199 -0.0287 0.8071 1.0000
1.500 0.2386 0.00764 0.00201 -0.0278 0.7816 1.0000
1.750 0.2641 0.00787 0.00205 -0.0270 0.7592 1.0000
2.000 0.2903 0.00809 0.00213 -0.0264 0.7374 1.0000
2.250 0.3162 0.00835 0.00224 -0.0257 0.7178 1.0000
2.500 0.3427 0.00857 0.00237 -0.0252 0.6972 1.0000
2.750 0.3695 0.00871 0.00246 -0.0248 0.6753 1.0000
3.000 0.3962 0.00880 0.00250 -0.0243 0.6532 1.0000
3.250 0.4230 0.00887 0.00253 -0.0239 0.6281 1.0000
3.500 0.4497 0.00897 0.00258 -0.0234 0.6008 1.0000
3.750 0.4762 0.00911 0.00262 -0.0230 0.5709 1.0000
4.000 0.5028 0.00929 0.00270 -0.0225 0.5377 1.0000
4.250 0.5292 0.00952 0.00282 -0.0221 0.5020 1.0000
4.500 0.5556 0.00980 0.00300 -0.0217 0.4633 1.0000
4.750 0.5818 0.01012 0.00319 -0.0214 0.4226 1.0000
5.000 0.6080 0.01049 0.00342 -0.0211 0.3799 1.0000
5.250 0.6341 0.01092 0.00370 -0.0209 0.3362 1.0000
5.500 0.6600 0.01142 0.00405 -0.0207 0.2924 1.0000
5.750 0.6858 0.01197 0.00444 -0.0205 0.2510 1.0000
6.000 0.7117 0.01255 0.00490 -0.0203 0.2148 1.0000
6.250 0.7373 0.01318 0.00541 -0.0201 0.1844 1.0000
6.500 0.7630 0.01383 0.00600 -0.0199 0.1597 1.0000
6.750 0.7882 0.01455 0.00666 -0.0197 0.1383 1.0000
7.000 0.8137 0.01523 0.00736 -0.0195 0.1196 1.0000
7.250 0.8388 0.01599 0.00810 -0.0192 0.1030 1.0000
7.500 0.8632 0.01692 0.00900 -0.0189 0.0881 1.0000
7.750 0.8875 0.01790 0.01000 -0.0185 0.0751 1.0000
8.000 0.9122 0.01874 0.01096 -0.0182 0.0638 1.0000
8.250 0.9362 0.01988 0.01222 -0.0177 0.0547 1.0000
8.500 0.9590 0.02132 0.01375 -0.0171 0.0471 1.0000
8.750 0.9823 0.02260 0.01513 -0.0166 0.0413 1.0000
9.000 1.0036 0.02473 0.01747 -0.0159 0.0366 1.0000
9.250 1.0262 0.02619 0.01915 -0.0153 0.0326 1.0000
9.500 1.0465 0.02834 0.02148 -0.0147 0.0299 1.0000
9.750 1.0602 0.03313 0.02676 -0.0137 0.0282 1.0000
10.000 1.0789 0.03498 0.02906 -0.0129 0.0263 1.0000
10.250 1.0929 0.03800 0.03252 -0.0122 0.0245 1.0000
10.500 1.1005 0.04223 0.03725 -0.0115 0.0238 1.0000
10.750 1.1005 0.04724 0.04277 -0.0110 0.0235 1.0000
11.000 1.0909 0.05299 0.04900 -0.0112 0.0237 1.0000
11.250 1.0723 0.05877 0.05513 -0.0122 0.0240 1.0000
11.500 1.0493 0.06503 0.06163 -0.0164 0.0243 1.0000
11.750 1.0250 0.07359 0.07038 -0.0244 0.0249 1.0000
12.000 0.9979 0.08505 0.08196 -0.0346 0.0257 1.0000
12.250 0.9683 0.09837 0.09527 -0.0440 0.0269 1.0000
12.500 0.9354 0.11465 0.11150 -0.0520 0.0304 1.0000
12.750 0.9322 0.11940 0.11624 -0.0540 0.0296 1.0000
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Polar data table (+)
Polar graphs
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