AG37 (ag37-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 500,000 Max Cl/Cd: 85.22 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag37-il-500000.txt Download as CSV file: xf-ag37-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4120 0.08406 0.08193 -0.0119 1.0000 0.0179
-9.750 -0.4112 0.08024 0.07812 -0.0128 1.0000 0.0182
-9.500 -0.4117 0.07622 0.07411 -0.0141 1.0000 0.0184
-9.250 -0.4130 0.07212 0.07004 -0.0155 1.0000 0.0187
-9.000 -0.4159 0.06788 0.06581 -0.0171 1.0000 0.0190
-8.750 -0.4209 0.06359 0.06155 -0.0191 1.0000 0.0192
-8.500 -0.4273 0.05890 0.05689 -0.0224 1.0000 0.0194
-8.250 -0.4286 0.05339 0.05136 -0.0271 1.0000 0.0196
-8.000 -0.4276 0.04778 0.04571 -0.0310 1.0000 0.0200
-7.750 -0.4250 0.04217 0.04002 -0.0338 1.0000 0.0206
-7.500 -0.4187 0.03588 0.03356 -0.0364 1.0000 0.0218
-7.250 -0.4067 0.03114 0.02849 -0.0372 1.0000 0.0226
-7.000 -0.3981 0.02707 0.02414 -0.0366 1.0000 0.0227
-6.750 -0.3974 0.01955 0.01634 -0.0368 1.0000 0.0239
-6.500 -0.3822 0.01790 0.01465 -0.0359 1.0000 0.0247
-6.250 -0.3660 0.01598 0.01259 -0.0350 1.0000 0.0257
-6.000 -0.3484 0.01398 0.01036 -0.0340 1.0000 0.0274
-5.750 -0.3251 0.01950 0.01461 -0.0355 1.0000 0.0206
-5.500 -0.3008 0.01623 0.01083 -0.0345 1.0000 0.0192
-5.250 -0.2758 0.01438 0.00868 -0.0336 1.0000 0.0191
-5.000 -0.2447 0.01325 0.00740 -0.0341 0.9989 0.0200
-4.750 -0.2067 0.01228 0.00632 -0.0361 0.9965 0.0213
-4.500 -0.1670 0.01180 0.00575 -0.0384 0.9938 0.0227
-4.250 -0.1307 0.01050 0.00441 -0.0402 0.9901 0.0259
-4.000 -0.0914 0.00995 0.00384 -0.0426 0.9863 0.0287
-3.750 -0.0506 0.00934 0.00318 -0.0452 0.9833 0.0332
-3.500 -0.0143 0.00893 0.00277 -0.0469 0.9767 0.0403
-3.250 0.0233 0.00835 0.00229 -0.0488 0.9706 0.0709
-3.000 0.0544 0.00761 0.00207 -0.0497 0.9594 0.2054
-2.750 0.0842 0.00698 0.00192 -0.0503 0.9456 0.3552
-2.500 0.1108 0.00621 0.00182 -0.0501 0.9278 0.5565
-2.250 0.1306 0.00535 0.00179 -0.0479 0.9005 0.8028
-2.000 0.1613 0.00501 0.00168 -0.0471 0.8649 0.9843
-1.750 0.1942 0.00510 0.00153 -0.0479 0.8308 1.0000
-1.500 0.2196 0.00524 0.00147 -0.0472 0.7994 1.0000
-1.250 0.2455 0.00539 0.00143 -0.0465 0.7687 1.0000
-1.000 0.2717 0.00553 0.00139 -0.0460 0.7356 1.0000
-0.750 0.2979 0.00570 0.00137 -0.0456 0.6974 1.0000
-0.500 0.3241 0.00589 0.00134 -0.0451 0.6482 1.0000
-0.250 0.3504 0.00612 0.00135 -0.0447 0.6131 1.0000
0.000 0.3773 0.00632 0.00140 -0.0445 0.5902 1.0000
0.250 0.4045 0.00650 0.00146 -0.0444 0.5715 1.0000
0.500 0.4319 0.00666 0.00153 -0.0443 0.5551 1.0000
0.750 0.4594 0.00681 0.00161 -0.0442 0.5398 1.0000
1.000 0.4869 0.00696 0.00169 -0.0441 0.5250 1.0000
1.250 0.5144 0.00710 0.00177 -0.0441 0.5097 1.0000
1.500 0.5420 0.00724 0.00185 -0.0440 0.4940 1.0000
1.750 0.5696 0.00738 0.00195 -0.0440 0.4772 1.0000
2.000 0.5972 0.00751 0.00204 -0.0440 0.4573 1.0000
2.250 0.6245 0.00767 0.00213 -0.0439 0.4346 1.0000
2.500 0.6517 0.00787 0.00224 -0.0439 0.4094 1.0000
2.750 0.6787 0.00810 0.00239 -0.0438 0.3830 1.0000
3.000 0.7056 0.00835 0.00255 -0.0438 0.3568 1.0000
3.250 0.7324 0.00863 0.00274 -0.0437 0.3313 1.0000
3.500 0.7590 0.00892 0.00295 -0.0437 0.3066 1.0000
3.750 0.7857 0.00922 0.00316 -0.0436 0.2808 1.0000
4.000 0.8122 0.00954 0.00340 -0.0436 0.2549 1.0000
4.250 0.8384 0.00989 0.00366 -0.0435 0.2270 1.0000
4.500 0.8645 0.01028 0.00396 -0.0434 0.1993 1.0000
4.750 0.8900 0.01075 0.00429 -0.0433 0.1680 1.0000
5.000 0.9152 0.01127 0.00467 -0.0431 0.1354 1.0000
5.250 0.9400 0.01186 0.00511 -0.0429 0.1042 1.0000
5.500 0.9643 0.01251 0.00564 -0.0426 0.0781 1.0000
5.750 0.9886 0.01317 0.00621 -0.0423 0.0608 1.0000
6.000 1.0126 0.01386 0.00687 -0.0419 0.0498 1.0000
6.250 1.0376 0.01434 0.00740 -0.0417 0.0438 1.0000
6.500 1.0609 0.01510 0.00820 -0.0412 0.0382 1.0000
6.750 1.0853 0.01563 0.00880 -0.0408 0.0348 1.0000
7.000 1.1069 0.01656 0.00976 -0.0401 0.0309 1.0000
7.250 1.1296 0.01730 0.01060 -0.0395 0.0287 1.0000
7.500 1.1529 0.01791 0.01129 -0.0391 0.0265 1.0000
7.750 1.1750 0.01864 0.01209 -0.0385 0.0246 1.0000
8.000 1.1891 0.02052 0.01408 -0.0368 0.0222 1.0000
8.250 1.2128 0.02096 0.01461 -0.0365 0.0212 1.0000
8.500 1.2339 0.02173 0.01549 -0.0358 0.0199 1.0000
8.750 1.2538 0.02260 0.01645 -0.0350 0.0187 1.0000
9.000 1.2725 0.02356 0.01747 -0.0341 0.0176 1.0000
9.250 1.2799 0.02612 0.02019 -0.0318 0.0163 1.0000
9.500 1.2989 0.02690 0.02112 -0.0309 0.0156 1.0000
9.750 1.3158 0.02786 0.02222 -0.0298 0.0148 1.0000
10.000 1.3300 0.02910 0.02360 -0.0285 0.0141 1.0000
10.250 1.3428 0.03032 0.02493 -0.0270 0.0134 1.0000
10.500 1.3534 0.03159 0.02630 -0.0254 0.0129 1.0000
10.750 1.3575 0.03314 0.02795 -0.0230 0.0124 1.0000
11.000 1.3527 0.03565 0.03062 -0.0200 0.0120 1.0000
11.500 1.3367 0.04189 0.03733 -0.0157 0.0115 1.0000
11.750 1.3357 0.04442 0.04004 -0.0153 0.0112 1.0000
12.000 1.3321 0.04758 0.04342 -0.0155 0.0110 1.0000
12.250 1.3270 0.05125 0.04727 -0.0165 0.0107 1.0000
12.500 1.3185 0.05577 0.05198 -0.0182 0.0105 1.0000
12.750 1.3091 0.06082 0.05721 -0.0207 0.0103 1.0000
13.000 1.2959 0.06681 0.06339 -0.0239 0.0103 1.0000
13.250 1.2817 0.07312 0.06986 -0.0273 0.0101 1.0000
13.500 1.2623 0.08053 0.07745 -0.0313 0.0102 1.0000
13.750 1.2413 0.08847 0.08556 -0.0356 0.0102 1.0000
14.000 1.2159 0.09764 0.09491 -0.0406 0.0103 1.0000
14.250 1.1884 0.10776 0.10518 -0.0462 0.0105 1.0000
14.500 1.1564 0.11958 0.11716 -0.0527 0.0108 1.0000
14.750 1.1188 0.13340 0.13112 -0.0601 0.0112 1.0000
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