AG37 (ag37-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 200,000 Max Cl/Cd: 62.49 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag37-il-200000-n5.txt Download as CSV file: xf-ag37-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG37
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4106 0.08166 0.07830 -0.0136 1.0000 0.0186
-9.500 -0.5165 0.08714 0.08362 -0.0096 1.0000 0.0163
-9.250 -0.5151 0.08350 0.08002 -0.0114 1.0000 0.0160
-9.000 -0.5131 0.07921 0.07576 -0.0148 1.0000 0.0157
-8.750 -0.5079 0.07414 0.07070 -0.0198 1.0000 0.0154
-8.500 -0.5009 0.06853 0.06506 -0.0251 1.0000 0.0151
-8.250 -0.4920 0.06248 0.05894 -0.0302 1.0000 0.0148
-8.000 -0.4816 0.05611 0.05245 -0.0346 1.0000 0.0146
-7.750 -0.4691 0.04978 0.04590 -0.0379 1.0000 0.0150
-7.500 -0.4556 0.04296 0.03875 -0.0400 1.0000 0.0156
-7.250 -0.4409 0.03689 0.03223 -0.0407 1.0000 0.0159
-7.000 -0.4243 0.03207 0.02695 -0.0406 1.0000 0.0158
-6.750 -0.4053 0.02790 0.02225 -0.0401 1.0000 0.0158
-6.500 -0.3843 0.02454 0.01831 -0.0393 1.0000 0.0160
-6.250 -0.3616 0.02201 0.01527 -0.0385 1.0000 0.0164
-6.000 -0.3382 0.02010 0.01296 -0.0376 1.0000 0.0168
-5.750 -0.3150 0.01849 0.01116 -0.0369 1.0000 0.0176
-5.500 -0.2915 0.01780 0.01040 -0.0362 1.0000 0.0190
-5.250 -0.2674 0.01701 0.00946 -0.0354 1.0000 0.0208
-5.000 -0.2429 0.01601 0.00830 -0.0346 1.0000 0.0219
-4.750 -0.2150 0.01508 0.00725 -0.0345 0.9988 0.0229
-4.500 -0.1784 0.01405 0.00620 -0.0365 0.9945 0.0252
-4.250 -0.1420 0.01351 0.00561 -0.0383 0.9886 0.0291
-4.000 -0.1043 0.01277 0.00482 -0.0404 0.9837 0.0325
-3.750 -0.0690 0.01228 0.00430 -0.0419 0.9761 0.0386
-3.500 -0.0321 0.01178 0.00380 -0.0438 0.9687 0.0501
-3.250 0.0022 0.01128 0.00341 -0.0451 0.9578 0.0806
-3.000 0.0352 0.01063 0.00314 -0.0464 0.9450 0.1712
-2.750 0.0669 0.00990 0.00296 -0.0475 0.9295 0.3248
-2.500 0.0946 0.00895 0.00283 -0.0476 0.9090 0.5469
-2.250 0.1148 0.00803 0.00282 -0.0449 0.8804 0.8139
-2.000 0.1672 0.00775 0.00257 -0.0489 0.8538 1.0000
-1.750 0.1951 0.00778 0.00237 -0.0484 0.8225 1.0000
-1.500 0.2213 0.00787 0.00224 -0.0477 0.7917 1.0000
-1.250 0.2472 0.00799 0.00216 -0.0470 0.7613 1.0000
-1.000 0.2731 0.00813 0.00210 -0.0464 0.7300 1.0000
-0.750 0.2990 0.00829 0.00206 -0.0458 0.6963 1.0000
-0.500 0.3249 0.00846 0.00203 -0.0452 0.6560 1.0000
-0.250 0.3505 0.00867 0.00201 -0.0446 0.6227 1.0000
0.000 0.3765 0.00890 0.00203 -0.0441 0.5979 1.0000
0.250 0.4030 0.00911 0.00209 -0.0438 0.5774 1.0000
0.500 0.4297 0.00931 0.00218 -0.0435 0.5590 1.0000
0.750 0.4565 0.00951 0.00229 -0.0433 0.5421 1.0000
1.000 0.4834 0.00970 0.00239 -0.0431 0.5258 1.0000
1.250 0.5103 0.00990 0.00252 -0.0429 0.5097 1.0000
1.500 0.5372 0.01009 0.00265 -0.0428 0.4934 1.0000
1.750 0.5643 0.01027 0.00280 -0.0426 0.4761 1.0000
2.000 0.5913 0.01044 0.00295 -0.0425 0.4569 1.0000
2.250 0.6180 0.01065 0.00310 -0.0423 0.4362 1.0000
2.500 0.6447 0.01086 0.00326 -0.0421 0.4135 1.0000
2.750 0.6710 0.01111 0.00346 -0.0419 0.3898 1.0000
3.250 0.7233 0.01171 0.00390 -0.0415 0.3390 1.0000
3.500 0.7492 0.01205 0.00417 -0.0414 0.3131 1.0000
3.750 0.7750 0.01241 0.00448 -0.0412 0.2867 1.0000
4.000 0.8005 0.01281 0.00479 -0.0410 0.2596 1.0000
4.250 0.8260 0.01323 0.00514 -0.0408 0.2320 1.0000
4.500 0.8511 0.01369 0.00554 -0.0406 0.2032 1.0000
4.750 0.8759 0.01421 0.00597 -0.0403 0.1731 1.0000
5.000 0.9003 0.01480 0.00645 -0.0401 0.1434 1.0000
5.250 0.9242 0.01546 0.00699 -0.0398 0.1152 1.0000
5.500 0.9480 0.01613 0.00761 -0.0394 0.0926 1.0000
5.750 0.9715 0.01686 0.00828 -0.0391 0.0752 1.0000
6.000 0.9946 0.01760 0.00900 -0.0386 0.0622 1.0000
6.250 1.0180 0.01829 0.00975 -0.0382 0.0535 1.0000
6.500 1.0406 0.01906 0.01058 -0.0377 0.0470 1.0000
6.750 1.0628 0.01986 0.01145 -0.0371 0.0414 1.0000
7.000 1.0841 0.02076 0.01244 -0.0364 0.0376 1.0000
7.250 1.1057 0.02160 0.01341 -0.0357 0.0344 1.0000
7.500 1.1258 0.02258 0.01445 -0.0350 0.0312 1.0000
7.750 1.1446 0.02370 0.01568 -0.0341 0.0288 1.0000
8.000 1.1640 0.02473 0.01690 -0.0331 0.0270 1.0000
8.250 1.1825 0.02581 0.01810 -0.0322 0.0251 1.0000
8.500 1.1999 0.02694 0.01933 -0.0312 0.0234 1.0000
8.750 1.2137 0.02853 0.02101 -0.0299 0.0219 1.0000
9.000 1.2299 0.02980 0.02249 -0.0287 0.0207 1.0000
9.250 1.2439 0.03129 0.02416 -0.0273 0.0197 1.0000
9.500 1.2567 0.03276 0.02581 -0.0259 0.0186 1.0000
9.750 1.2683 0.03415 0.02735 -0.0245 0.0176 1.0000
10.000 1.2766 0.03572 0.02902 -0.0229 0.0168 1.0000
10.250 1.2775 0.03785 0.03128 -0.0204 0.0161 1.0000
10.500 1.2807 0.03973 0.03343 -0.0184 0.0155 1.0000
10.750 1.2806 0.04207 0.03601 -0.0165 0.0151 1.0000
11.000 1.2782 0.04475 0.03894 -0.0151 0.0146 1.0000
11.250 1.2738 0.04783 0.04226 -0.0144 0.0143 1.0000
11.500 1.2678 0.05137 0.04602 -0.0145 0.0140 1.0000
11.750 1.2600 0.05541 0.05029 -0.0154 0.0137 1.0000
12.000 1.2507 0.05999 0.05508 -0.0171 0.0135 1.0000
12.250 1.2398 0.06522 0.06053 -0.0196 0.0133 1.0000
12.500 1.2267 0.07116 0.06667 -0.0228 0.0132 1.0000
12.750 1.2112 0.07779 0.07350 -0.0265 0.0131 1.0000
13.000 1.1921 0.08534 0.08125 -0.0307 0.0131 1.0000
13.250 1.1691 0.09403 0.09014 -0.0357 0.0132 1.0000
13.500 1.1408 0.10435 0.10066 -0.0416 0.0134 1.0000
13.750 1.1073 0.11668 0.11318 -0.0487 0.0138 1.0000
14.000 1.0655 0.13243 0.12909 -0.0575 0.0143 1.0000
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Polar data table (+)
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