SM701 (sm701-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 50,000 Max Cl/Cd: 30.52 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sm701-il-50000-n5.txt Download as CSV file: xf-sm701-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SM701
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3818 0.11072 0.10371 -0.0515 1.0000 0.0580
-10.500 -0.3921 0.10670 0.09978 -0.0517 1.0000 0.0574
-10.250 -0.4052 0.10240 0.09558 -0.0520 1.0000 0.0567
-10.000 -0.4227 0.09740 0.09066 -0.0529 1.0000 0.0559
-9.750 -0.4485 0.09161 0.08495 -0.0542 1.0000 0.0550
-9.500 -0.4857 0.08587 0.07925 -0.0554 1.0000 0.0539
-9.250 -0.5302 0.08113 0.07453 -0.0551 1.0000 0.0530
-9.000 -0.5816 0.07773 0.07110 -0.0526 1.0000 0.0522
-8.750 -0.6109 0.07135 0.06430 -0.0569 0.9907 0.0514
-8.500 -0.6153 0.06629 0.05879 -0.0598 0.9830 0.0512
-8.250 -0.6117 0.06240 0.05456 -0.0610 0.9757 0.0512
-8.000 -0.5997 0.05877 0.05060 -0.0626 0.9702 0.0515
-7.750 -0.5888 0.05592 0.04749 -0.0628 0.9639 0.0520
-7.500 -0.5700 0.05354 0.04492 -0.0639 0.9592 0.0533
-7.250 -0.5540 0.05123 0.04233 -0.0642 0.9538 0.0548
-7.000 -0.5361 0.04885 0.03960 -0.0645 0.9484 0.0564
-6.750 -0.5118 0.04642 0.03672 -0.0655 0.9444 0.0579
-6.500 -0.4915 0.04441 0.03432 -0.0652 0.9397 0.0589
-6.250 -0.4684 0.04266 0.03220 -0.0649 0.9350 0.0601
-6.000 -0.4409 0.04116 0.03059 -0.0653 0.9313 0.0617
-5.750 -0.4143 0.04012 0.02951 -0.0656 0.9276 0.0647
-5.500 -0.3943 0.03923 0.02848 -0.0644 0.9224 0.0682
-5.250 -0.3678 0.03839 0.02745 -0.0639 0.9183 0.0719
-5.000 -0.3396 0.03754 0.02667 -0.0640 0.9150 0.0759
-4.750 -0.3219 0.03689 0.02593 -0.0625 0.9094 0.0804
-4.500 -0.2998 0.03612 0.02514 -0.0620 0.9045 0.0878
-4.250 -0.2724 0.03526 0.02429 -0.0627 0.9007 0.1004
-4.000 -0.2535 0.03432 0.02345 -0.0622 0.8951 0.1184
-3.750 -0.2309 0.03301 0.02246 -0.0629 0.8900 0.1618
-3.500 -0.2082 0.03069 0.02197 -0.0644 0.8862 0.3857
-3.250 -0.1942 0.03155 0.02327 -0.0603 0.8801 0.5644
-3.000 -0.1758 0.03240 0.02399 -0.0575 0.8739 0.6166
-2.750 -0.1510 0.03325 0.02469 -0.0553 0.8693 0.6549
-2.500 -0.1421 0.03395 0.02534 -0.0505 0.8620 0.6783
-2.250 -0.1250 0.03462 0.02591 -0.0469 0.8561 0.7076
-2.000 -0.1091 0.03522 0.02643 -0.0427 0.8507 0.7320
-1.750 -0.0978 0.03551 0.02663 -0.0391 0.8429 0.7508
-1.500 -0.0689 0.03552 0.02644 -0.0390 0.8380 0.7623
-1.250 -0.0483 0.03549 0.02625 -0.0386 0.8305 0.7707
-1.000 -0.0211 0.03542 0.02601 -0.0388 0.8241 0.7771
-0.750 0.0136 0.03530 0.02571 -0.0403 0.8192 0.7834
-0.500 0.0329 0.03534 0.02563 -0.0400 0.8100 0.7901
-0.250 0.0672 0.03520 0.02534 -0.0411 0.8047 0.7952
0.000 0.0865 0.03529 0.02534 -0.0405 0.7952 0.8013
0.250 0.1228 0.03514 0.02505 -0.0424 0.7891 0.8070
0.500 0.1431 0.03521 0.02506 -0.0416 0.7797 0.8123
0.750 0.1778 0.03504 0.02479 -0.0429 0.7729 0.8182
1.000 0.2010 0.03513 0.02481 -0.0429 0.7631 0.8241
1.250 0.2354 0.03487 0.02448 -0.0438 0.7562 0.8295
1.500 0.2571 0.03499 0.02456 -0.0435 0.7453 0.8363
1.750 0.2945 0.03461 0.02412 -0.0448 0.7390 0.8421
2.000 0.3136 0.03475 0.02425 -0.0438 0.7271 0.8488
2.250 0.3548 0.03421 0.02366 -0.0456 0.7215 0.8555
2.500 0.3712 0.03436 0.02383 -0.0441 0.7086 0.8631
2.750 0.3962 0.03432 0.02378 -0.0439 0.6976 0.8714
3.000 0.4306 0.03374 0.02321 -0.0443 0.6901 0.8789
3.250 0.4506 0.03381 0.02330 -0.0434 0.6770 0.8885
3.750 0.5106 0.03294 0.02249 -0.0432 0.6573 0.9094
4.000 0.5327 0.03292 0.02252 -0.0426 0.6435 0.9228
4.250 0.5602 0.03274 0.02241 -0.0427 0.6303 0.9379
4.500 0.5966 0.03230 0.02202 -0.0441 0.6184 0.9564
4.750 0.6388 0.03144 0.02119 -0.0461 0.6074 0.9931
5.000 0.6670 0.03141 0.02119 -0.0468 0.5923 1.0000
5.250 0.6969 0.03133 0.02110 -0.0476 0.5770 1.0000
5.750 0.7607 0.03102 0.02077 -0.0492 0.5460 1.0000
6.000 0.7941 0.03083 0.02053 -0.0501 0.5299 1.0000
6.250 0.8277 0.03067 0.02032 -0.0509 0.5134 1.0000
6.500 0.8605 0.03062 0.02019 -0.0516 0.4965 1.0000
6.750 0.8919 0.03069 0.02016 -0.0522 0.4791 1.0000
7.000 0.9212 0.03095 0.02034 -0.0526 0.4621 1.0000
7.500 0.9729 0.03192 0.02113 -0.0527 0.4290 1.0000
7.750 0.9955 0.03262 0.02180 -0.0525 0.4137 1.0000
8.000 1.0167 0.03341 0.02256 -0.0521 0.3989 1.0000
8.250 1.0372 0.03424 0.02338 -0.0517 0.3850 1.0000
8.500 1.0585 0.03508 0.02420 -0.0514 0.3722 1.0000
8.750 1.0820 0.03584 0.02493 -0.0513 0.3604 1.0000
9.000 1.1036 0.03669 0.02578 -0.0510 0.3487 1.0000
9.250 1.1200 0.03781 0.02697 -0.0502 0.3376 1.0000
9.500 1.1427 0.03867 0.02784 -0.0500 0.3276 1.0000
9.750 1.1610 0.03972 0.02894 -0.0495 0.3176 1.0000
10.000 1.1772 0.04092 0.03022 -0.0488 0.3083 1.0000
10.250 1.2004 0.04178 0.03108 -0.0486 0.2996 1.0000
10.500 1.2107 0.04331 0.03279 -0.0475 0.2912 1.0000
10.750 1.2339 0.04417 0.03363 -0.0473 0.2832 1.0000
11.000 1.2402 0.04597 0.03562 -0.0460 0.2756 1.0000
11.250 1.2593 0.04707 0.03677 -0.0455 0.2685 1.0000
11.500 1.2673 0.04885 0.03873 -0.0444 0.2616 1.0000
11.750 1.2766 0.05053 0.04053 -0.0434 0.2549 1.0000
12.000 1.2947 0.05176 0.04181 -0.0430 0.2487 1.0000
12.250 1.2899 0.05447 0.04478 -0.0414 0.2428 1.0000
12.500 1.3059 0.05576 0.04612 -0.0409 0.2369 1.0000
12.750 1.3066 0.05826 0.04882 -0.0398 0.2316 1.0000
13.000 1.2961 0.06168 0.05249 -0.0386 0.2264 1.0000
13.250 1.3127 0.06297 0.05383 -0.0382 0.2211 1.0000
13.500 1.3050 0.06643 0.05749 -0.0374 0.2167 1.0000
13.750 1.2706 0.07271 0.06409 -0.0369 0.2126 1.0000
14.000 1.2627 0.07658 0.06811 -0.0369 0.2079 1.0000
14.250 1.2894 0.07671 0.06824 -0.0365 0.2031 1.0000
14.500 1.0551 0.11653 0.10848 -0.0519 0.1945 1.0000
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