SM701 (sm701-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 50,000 Max Cl/Cd: 26.97 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sm701-il-50000.txt Download as CSV file: xf-sm701-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3494 0.11241 0.10638 -0.0110 1.0000 0.3692
-7.750 -0.3580 0.11051 0.10457 -0.0088 1.0000 0.3776
-6.750 -0.6366 0.07391 0.06787 -0.0339 1.0000 0.1570
-6.500 -0.6442 0.06685 0.06025 -0.0363 1.0000 0.1413
-6.250 -0.6355 0.06278 0.05606 -0.0360 1.0000 0.1371
-6.000 -0.6277 0.05752 0.05019 -0.0376 1.0000 0.1311
-5.750 -0.6114 0.05366 0.04536 -0.0390 1.0000 0.1266
-5.500 -0.5931 0.05059 0.04196 -0.0392 1.0000 0.1262
-5.250 -0.5730 0.04777 0.03881 -0.0392 1.0000 0.1256
-5.000 -0.5515 0.04526 0.03594 -0.0392 1.0000 0.1252
-4.750 -0.5291 0.04313 0.03344 -0.0390 1.0000 0.1254
-4.500 -0.5057 0.04142 0.03128 -0.0387 1.0000 0.1270
-4.250 -0.4853 0.03963 0.02954 -0.0381 1.0000 0.1312
-4.000 -0.4641 0.03846 0.02828 -0.0374 1.0000 0.1369
-3.750 -0.4418 0.03745 0.02699 -0.0364 1.0000 0.1422
-3.500 -0.4227 0.03637 0.02608 -0.0347 1.0000 0.1489
-3.250 -0.4028 0.03565 0.02533 -0.0331 1.0000 0.1600
-3.000 -0.3839 0.03480 0.02468 -0.0317 1.0000 0.1787
-2.750 -0.3621 0.03342 0.02371 -0.0312 1.0000 0.2233
-2.500 -0.3577 0.03258 0.02571 -0.0240 1.0000 0.6377
-2.250 -0.3684 0.03433 0.02753 -0.0128 1.0000 0.7009
-2.000 -0.3775 0.03547 0.02867 -0.0026 1.0000 0.7457
-1.750 -0.3850 0.03615 0.02932 0.0066 1.0000 0.7841
-1.500 -0.3896 0.03647 0.02957 0.0145 1.0000 0.8177
-1.250 -0.3913 0.03659 0.02959 0.0214 1.0000 0.8491
-1.000 -0.3896 0.03661 0.02951 0.0273 1.0000 0.8813
-0.750 -0.2084 0.04185 0.03398 0.0051 1.0000 0.9736
-0.500 -0.1610 0.04247 0.03436 -0.0014 1.0000 0.9850
-0.250 -0.1233 0.04302 0.03473 -0.0063 1.0000 0.9945
0.000 -0.1030 0.04335 0.03493 -0.0083 1.0000 1.0000
0.250 -0.1045 0.04312 0.03466 -0.0062 1.0000 1.0000
0.500 -0.1065 0.04288 0.03438 -0.0041 1.0000 1.0000
0.750 0.0159 0.04592 0.03707 -0.0237 0.9473 1.0000
1.000 0.0535 0.04668 0.03770 -0.0278 0.9279 1.0000
1.250 0.0723 0.04684 0.03779 -0.0286 0.9100 1.0000
1.500 0.0918 0.04709 0.03797 -0.0293 0.8924 1.0000
1.750 0.1106 0.04734 0.03816 -0.0299 0.8751 1.0000
2.000 0.1292 0.04758 0.03833 -0.0302 0.8577 1.0000
2.250 0.1469 0.04780 0.03850 -0.0303 0.8406 1.0000
2.500 0.1671 0.04807 0.03871 -0.0307 0.8233 1.0000
2.750 0.1958 0.04852 0.03908 -0.0324 0.8057 1.0000
3.000 0.2310 0.04908 0.03957 -0.0349 0.7883 1.0000
3.250 0.2693 0.04965 0.04009 -0.0378 0.7710 1.0000
3.500 0.3040 0.05022 0.04060 -0.0402 0.7531 1.0000
3.750 0.3337 0.05086 0.04122 -0.0420 0.7348 1.0000
4.000 0.3668 0.05150 0.04184 -0.0441 0.7169 1.0000
4.250 0.4013 0.05211 0.04243 -0.0462 0.6991 1.0000
4.500 0.4366 0.05268 0.04299 -0.0483 0.6819 1.0000
4.750 0.4719 0.05317 0.04348 -0.0502 0.6649 1.0000
5.000 0.5069 0.05365 0.04395 -0.0519 0.6485 1.0000
5.250 0.5420 0.05400 0.04431 -0.0534 0.6320 1.0000
5.500 0.5762 0.05433 0.04465 -0.0546 0.6162 1.0000
6.000 0.6479 0.05444 0.04480 -0.0566 0.5863 1.0000
6.250 0.7068 0.05244 0.04285 -0.0582 0.5759 1.0000
6.500 0.7354 0.05264 0.04308 -0.0583 0.5607 1.0000
6.750 0.7616 0.05305 0.04351 -0.0582 0.5459 1.0000
7.000 0.7865 0.05355 0.04406 -0.0580 0.5314 1.0000
7.250 0.9028 0.04566 0.03623 -0.0610 0.5276 1.0000
7.500 0.9363 0.04543 0.03605 -0.0611 0.5127 1.0000
7.750 0.9710 0.04523 0.03588 -0.0613 0.4980 1.0000
8.000 1.0054 0.04522 0.03592 -0.0616 0.4835 1.0000
8.250 1.0444 0.04506 0.03579 -0.0624 0.4691 1.0000
8.500 1.0846 0.04503 0.03577 -0.0634 0.4548 1.0000
8.750 1.1280 0.04508 0.03584 -0.0649 0.4408 1.0000
9.000 1.1748 0.04524 0.03598 -0.0670 0.4265 1.0000
9.250 1.2256 0.04544 0.03613 -0.0696 0.4125 1.0000
9.500 1.1487 0.05144 0.04241 -0.0599 0.4074 1.0000
9.750 1.2094 0.05079 0.04176 -0.0628 0.3942 1.0000
10.000 0.4960 0.12411 0.11607 -0.0583 0.5265 1.0000
10.250 0.4910 0.12541 0.11742 -0.0581 0.5144 1.0000
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