AG35 (ag35-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 500,000 Max Cl/Cd: 90.82 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag35-il-500000.txt Download as CSV file: xf-ag35-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG35
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5188 0.07600 0.07392 -0.0225 1.0000 0.0209
-9.500 -0.5176 0.07026 0.06817 -0.0279 1.0000 0.0213
-9.250 -0.5096 0.06600 0.06389 -0.0316 1.0000 0.0216
-9.000 -0.4998 0.06178 0.05963 -0.0351 1.0000 0.0220
-8.750 -0.4890 0.05718 0.05497 -0.0385 1.0000 0.0226
-8.500 -0.4777 0.05212 0.04979 -0.0416 1.0000 0.0233
-8.250 -0.4669 0.04665 0.04414 -0.0438 1.0000 0.0245
-8.000 -0.4512 0.04170 0.03868 -0.0444 1.0000 0.0273
-7.750 -0.4652 0.02793 0.02414 -0.0428 1.0000 0.0193
-7.500 -0.4466 0.02394 0.01965 -0.0423 0.9988 0.0194
-7.250 -0.4140 0.02010 0.01525 -0.0440 0.9958 0.0195
-7.000 -0.3799 0.01768 0.01242 -0.0454 0.9930 0.0198
-6.750 -0.3449 0.01624 0.01071 -0.0468 0.9892 0.0203
-6.500 -0.3099 0.01432 0.00851 -0.0484 0.9859 0.0211
-6.250 -0.2742 0.01313 0.00728 -0.0502 0.9832 0.0229
-6.000 -0.2416 0.01240 0.00649 -0.0511 0.9766 0.0243
-5.750 -0.2074 0.01167 0.00567 -0.0522 0.9711 0.0258
-5.500 -0.1764 0.01118 0.00512 -0.0527 0.9622 0.0272
-5.250 -0.1468 0.01024 0.00412 -0.0529 0.9529 0.0303
-5.000 -0.1187 0.00992 0.00378 -0.0527 0.9421 0.0340
-4.750 -0.0923 0.00946 0.00325 -0.0520 0.9297 0.0386
-4.500 -0.0660 0.00915 0.00291 -0.0514 0.9173 0.0458
-4.250 -0.0401 0.00879 0.00256 -0.0507 0.9039 0.0616
-4.000 -0.0142 0.00836 0.00229 -0.0501 0.8910 0.1068
-3.750 0.0116 0.00793 0.00211 -0.0497 0.8777 0.1868
-3.500 0.0377 0.00756 0.00198 -0.0493 0.8641 0.2706
-3.250 0.0640 0.00722 0.00188 -0.0490 0.8497 0.3574
-3.000 0.0899 0.00682 0.00178 -0.0486 0.8340 0.4644
-2.750 0.1145 0.00626 0.00172 -0.0479 0.8172 0.6278
-2.500 0.1349 0.00567 0.00172 -0.0458 0.8005 0.8165
-2.250 0.1606 0.00547 0.00172 -0.0443 0.7827 0.9543
-2.000 0.2109 0.00551 0.00163 -0.0490 0.7615 1.0000
-1.750 0.2368 0.00560 0.00156 -0.0484 0.7382 1.0000
-1.500 0.2629 0.00569 0.00151 -0.0479 0.7110 1.0000
-1.250 0.2890 0.00581 0.00145 -0.0475 0.6749 1.0000
-1.000 0.3147 0.00599 0.00139 -0.0469 0.6284 1.0000
-0.750 0.3408 0.00620 0.00140 -0.0465 0.6040 1.0000
-0.500 0.3675 0.00638 0.00145 -0.0463 0.5870 1.0000
-0.250 0.3946 0.00653 0.00150 -0.0461 0.5732 1.0000
0.000 0.4217 0.00668 0.00156 -0.0460 0.5610 1.0000
0.250 0.4491 0.00682 0.00163 -0.0459 0.5493 1.0000
0.500 0.4766 0.00693 0.00170 -0.0458 0.5383 1.0000
0.750 0.5041 0.00706 0.00178 -0.0458 0.5276 1.0000
1.000 0.5315 0.00719 0.00186 -0.0457 0.5170 1.0000
1.250 0.5591 0.00731 0.00195 -0.0457 0.5059 1.0000
1.500 0.5868 0.00742 0.00204 -0.0457 0.4942 1.0000
1.750 0.6144 0.00754 0.00214 -0.0457 0.4820 1.0000
2.000 0.6419 0.00765 0.00223 -0.0457 0.4679 1.0000
2.250 0.6694 0.00777 0.00234 -0.0456 0.4517 1.0000
2.500 0.6967 0.00792 0.00244 -0.0456 0.4333 1.0000
2.750 0.7239 0.00810 0.00256 -0.0456 0.4129 1.0000
3.000 0.7508 0.00832 0.00271 -0.0455 0.3892 1.0000
3.250 0.7774 0.00856 0.00288 -0.0455 0.3632 1.0000
3.500 0.8038 0.00886 0.00309 -0.0454 0.3352 1.0000
3.750 0.8299 0.00920 0.00332 -0.0453 0.3066 1.0000
4.000 0.8559 0.00957 0.00359 -0.0452 0.2782 1.0000
4.250 0.8817 0.00995 0.00388 -0.0451 0.2517 1.0000
4.500 0.9073 0.01036 0.00419 -0.0450 0.2271 1.0000
4.750 0.9328 0.01077 0.00451 -0.0449 0.2040 1.0000
5.000 0.9584 0.01118 0.00486 -0.0448 0.1821 1.0000
5.250 0.9834 0.01164 0.00523 -0.0447 0.1600 1.0000
5.500 1.0086 0.01208 0.00561 -0.0445 0.1385 1.0000
5.750 1.0332 0.01258 0.00602 -0.0443 0.1182 1.0000
6.000 1.0576 0.01310 0.00648 -0.0441 0.0986 1.0000
6.250 1.0814 0.01369 0.00699 -0.0438 0.0809 1.0000
6.500 1.1052 0.01426 0.00752 -0.0435 0.0655 1.0000
6.750 1.1280 0.01495 0.00813 -0.0432 0.0498 1.0000
7.000 1.1499 0.01576 0.00888 -0.0426 0.0358 1.0000
7.250 1.1710 0.01664 0.00976 -0.0419 0.0269 1.0000
7.500 1.1904 0.01774 0.01088 -0.0410 0.0214 1.0000
7.750 1.2123 0.01843 0.01166 -0.0404 0.0190 1.0000
8.000 1.2318 0.01938 0.01265 -0.0396 0.0167 1.0000
8.250 1.2489 0.02056 0.01395 -0.0384 0.0152 1.0000
8.500 1.2677 0.02146 0.01497 -0.0375 0.0141 1.0000
8.750 1.2851 0.02246 0.01605 -0.0364 0.0132 1.0000
9.000 1.3001 0.02363 0.01730 -0.0351 0.0125 1.0000
9.250 1.3074 0.02548 0.01926 -0.0329 0.0118 1.0000
9.500 1.3139 0.02731 0.02125 -0.0307 0.0114 1.0000
9.750 1.3235 0.02853 0.02259 -0.0287 0.0111 1.0000
10.000 1.3297 0.02996 0.02416 -0.0264 0.0109 1.0000
10.250 1.3344 0.03160 0.02594 -0.0244 0.0106 1.0000
10.500 1.3383 0.03339 0.02787 -0.0226 0.0103 1.0000
10.750 1.3416 0.03531 0.02993 -0.0212 0.0100 1.0000
11.000 1.3441 0.03742 0.03217 -0.0202 0.0097 1.0000
11.250 1.3460 0.03970 0.03457 -0.0196 0.0094 1.0000
11.500 1.3465 0.04227 0.03725 -0.0193 0.0092 1.0000
11.750 1.3450 0.04525 0.04034 -0.0193 0.0090 1.0000
12.000 1.3407 0.04872 0.04394 -0.0196 0.0088 1.0000
12.250 1.3340 0.05269 0.04806 -0.0202 0.0087 1.0000
12.500 1.3249 0.05719 0.05272 -0.0212 0.0086 1.0000
12.750 1.3142 0.06215 0.05786 -0.0227 0.0085 1.0000
13.000 1.3015 0.06754 0.06342 -0.0245 0.0085 1.0000
13.250 1.2875 0.07329 0.06934 -0.0267 0.0085 1.0000
13.500 1.2725 0.07932 0.07555 -0.0292 0.0084 1.0000
13.750 1.2588 0.08545 0.08183 -0.0320 0.0084 1.0000
14.000 1.2428 0.09226 0.08880 -0.0353 0.0084 1.0000
14.250 1.2275 0.09921 0.09591 -0.0389 0.0084 1.0000
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