AG35 (ag35-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 200,000 Max Cl/Cd: 68.45 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag35-il-200000.txt Download as CSV file: xf-ag35-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4063 0.09392 0.09067 -0.0201 1.0000 0.0467
-10.500 -0.4097 0.08955 0.08632 -0.0229 1.0000 0.0469
-9.500 -0.4994 0.07950 0.07614 -0.0329 1.0000 0.0471
-9.250 -0.4917 0.07886 0.07561 -0.0221 1.0000 0.0492
-9.000 -0.4823 0.07607 0.07283 -0.0226 1.0000 0.0514
-8.750 -0.4744 0.07159 0.06833 -0.0270 1.0000 0.0536
-8.500 -0.4638 0.06379 0.06028 -0.0394 1.0000 0.0583
-8.250 -0.4624 0.05658 0.05275 -0.0438 1.0000 0.0598
-8.000 -0.4497 0.05340 0.04972 -0.0426 1.0000 0.0612
-7.750 -0.4368 0.05105 0.04739 -0.0417 1.0000 0.0630
-7.500 -0.4243 0.04809 0.04433 -0.0416 1.0000 0.0662
-7.250 -0.4153 0.04292 0.03857 -0.0430 1.0000 0.0737
-7.000 -0.4021 0.04041 0.03615 -0.0416 1.0000 0.0756
-6.750 -0.3859 0.03112 0.02547 -0.0399 1.0000 0.0474
-6.500 -0.3696 0.02772 0.02193 -0.0386 1.0000 0.0453
-6.250 -0.3517 0.02467 0.01850 -0.0373 1.0000 0.0440
-6.000 -0.3310 0.02193 0.01533 -0.0361 1.0000 0.0424
-5.750 -0.3085 0.01997 0.01300 -0.0350 1.0000 0.0423
-5.500 -0.2851 0.01854 0.01129 -0.0341 1.0000 0.0432
-5.250 -0.2493 0.01766 0.01015 -0.0355 0.9971 0.0464
-5.000 -0.2103 0.01576 0.00816 -0.0377 0.9942 0.0500
-4.750 -0.1712 0.01480 0.00718 -0.0399 0.9890 0.0553
-4.500 -0.1303 0.01385 0.00624 -0.0425 0.9846 0.0653
-4.250 -0.0910 0.01302 0.00546 -0.0448 0.9786 0.0816
-4.000 -0.0503 0.01193 0.00473 -0.0476 0.9731 0.1480
-3.750 -0.0105 0.01076 0.00445 -0.0507 0.9681 0.3595
-3.500 0.0236 0.00976 0.00430 -0.0521 0.9600 0.5713
-3.250 0.0504 0.00885 0.00436 -0.0503 0.9529 0.8564
-3.000 0.1160 0.00864 0.00410 -0.0571 0.9494 1.0000
-2.750 0.1517 0.00855 0.00386 -0.0585 0.9368 1.0000
-2.500 0.1822 0.00848 0.00366 -0.0586 0.9217 1.0000
-2.250 0.2090 0.00843 0.00348 -0.0579 0.9045 1.0000
-2.000 0.2338 0.00839 0.00332 -0.0568 0.8861 1.0000
-1.750 0.2579 0.00837 0.00317 -0.0554 0.8671 1.0000
-1.500 0.2816 0.00838 0.00306 -0.0541 0.8442 1.0000
-1.250 0.3057 0.00840 0.00294 -0.0528 0.8209 1.0000
-1.000 0.3301 0.00846 0.00284 -0.0516 0.7967 1.0000
-0.750 0.3550 0.00856 0.00279 -0.0507 0.7709 1.0000
-0.500 0.3803 0.00869 0.00277 -0.0499 0.7456 1.0000
-0.250 0.4059 0.00883 0.00275 -0.0491 0.7214 1.0000
0.000 0.4319 0.00896 0.00276 -0.0486 0.6965 1.0000
0.250 0.4581 0.00910 0.00280 -0.0481 0.6734 1.0000
0.500 0.4845 0.00923 0.00282 -0.0477 0.6512 1.0000
0.750 0.5108 0.00940 0.00286 -0.0473 0.6317 1.0000
1.000 0.5371 0.00963 0.00295 -0.0469 0.6140 1.0000
1.250 0.5634 0.00990 0.00312 -0.0466 0.5972 1.0000
1.500 0.5899 0.01018 0.00331 -0.0463 0.5813 1.0000
1.750 0.6164 0.01045 0.00351 -0.0461 0.5657 1.0000
2.000 0.6430 0.01071 0.00372 -0.0458 0.5504 1.0000
2.250 0.6695 0.01096 0.00395 -0.0456 0.5348 1.0000
2.500 0.6959 0.01120 0.00416 -0.0453 0.5188 1.0000
2.750 0.7222 0.01140 0.00437 -0.0451 0.5014 1.0000
3.000 0.7485 0.01158 0.00459 -0.0448 0.4822 1.0000
3.250 0.7746 0.01176 0.00477 -0.0445 0.4617 1.0000
3.500 0.8006 0.01193 0.00495 -0.0442 0.4385 1.0000
3.750 0.8262 0.01215 0.00515 -0.0439 0.4132 1.0000
4.000 0.8514 0.01244 0.00540 -0.0435 0.3847 1.0000
4.250 0.8762 0.01280 0.00570 -0.0432 0.3540 1.0000
4.500 0.9005 0.01325 0.00605 -0.0428 0.3227 1.0000
4.750 0.9245 0.01376 0.00647 -0.0424 0.2927 1.0000
5.000 0.9482 0.01432 0.00696 -0.0419 0.2643 1.0000
5.250 0.9717 0.01491 0.00748 -0.0415 0.2376 1.0000
5.500 0.9948 0.01553 0.00804 -0.0411 0.2124 1.0000
5.750 1.0174 0.01622 0.00864 -0.0406 0.1879 1.0000
6.000 1.0402 0.01687 0.00928 -0.0402 0.1630 1.0000
6.250 1.0625 0.01758 0.00995 -0.0397 0.1389 1.0000
6.500 1.0838 0.01839 0.01071 -0.0391 0.1160 1.0000
6.750 1.1035 0.01941 0.01161 -0.0384 0.0943 1.0000
7.000 1.1231 0.02045 0.01265 -0.0376 0.0739 1.0000
7.250 1.1385 0.02197 0.01408 -0.0362 0.0580 1.0000
7.500 1.1540 0.02343 0.01555 -0.0349 0.0472 1.0000
7.750 1.1708 0.02472 0.01697 -0.0335 0.0407 1.0000
8.000 1.1821 0.02667 0.01892 -0.0318 0.0361 1.0000
8.250 1.1988 0.02785 0.02027 -0.0305 0.0325 1.0000
8.500 1.2122 0.02941 0.02187 -0.0291 0.0300 1.0000
8.750 1.2218 0.03230 0.02480 -0.0272 0.0281 1.0000
9.000 1.2363 0.03401 0.02678 -0.0257 0.0270 1.0000
9.250 1.2487 0.03598 0.02897 -0.0242 0.0258 1.0000
9.500 1.2592 0.03785 0.03103 -0.0226 0.0245 1.0000
9.750 1.2655 0.03955 0.03286 -0.0207 0.0234 1.0000
10.000 1.2705 0.04158 0.03498 -0.0189 0.0224 1.0000
10.250 1.2733 0.04465 0.03822 -0.0171 0.0218 1.0000
10.500 1.2701 0.04842 0.04226 -0.0152 0.0215 1.0000
10.750 1.2609 0.05248 0.04662 -0.0135 0.0213 1.0000
11.250 1.2358 0.06060 0.05526 -0.0119 0.0212 1.0000
11.500 1.2212 0.06514 0.06005 -0.0123 0.0212 1.0000
11.750 1.2047 0.07026 0.06542 -0.0135 0.0212 1.0000
12.000 1.1891 0.07547 0.07085 -0.0155 0.0213 1.0000
12.250 1.1733 0.08114 0.07671 -0.0184 0.0213 1.0000
12.500 1.1567 0.08733 0.08309 -0.0219 0.0214 1.0000
12.750 1.1392 0.09405 0.09001 -0.0261 0.0215 1.0000
13.000 1.1195 0.10172 0.09787 -0.0312 0.0217 1.0000
13.250 1.0857 0.11383 0.11027 -0.0398 0.0224 1.0000
13.500 0.8415 0.12058 0.11734 -0.0286 0.0271 1.0000
13.750 0.8056 0.12923 0.12602 -0.0326 0.0282 1.0000
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Polar data table (+)
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