SA7035 (sa7035-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 100,000 Max Cl/Cd: 52.78 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7035-il-100000.txt Download as CSV file: xf-sa7035-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3972 0.09599 0.09120 -0.0262 1.0000 0.0946
-8.250 -0.4030 0.09326 0.08856 -0.0290 1.0000 0.0975
-8.000 -0.4246 0.09107 0.08652 -0.0336 1.0000 0.0988
-7.750 -0.4116 0.08646 0.08195 -0.0311 1.0000 0.1016
-7.500 -0.4027 0.08365 0.07917 -0.0294 1.0000 0.1055
-7.250 -0.4105 0.08115 0.07676 -0.0296 1.0000 0.1087
-7.000 -0.4404 0.07777 0.07341 -0.0394 1.0000 0.1128
-6.750 -0.4335 0.07383 0.06959 -0.0360 1.0000 0.1150
-6.500 -0.3987 0.06171 0.05787 -0.0326 1.0000 0.1265
-6.250 -0.4485 0.06861 0.06414 -0.0399 1.0000 0.1273
-6.000 -0.4356 0.06476 0.06056 -0.0345 1.0000 0.1298
-5.750 -0.4356 0.06228 0.05793 -0.0358 1.0000 0.1403
-5.500 -0.4309 0.05875 0.05449 -0.0337 1.0000 0.1441
-5.000 -0.4177 0.05317 0.04883 -0.0319 1.0000 0.1612
-4.750 -0.4092 0.05026 0.04584 -0.0318 1.0000 0.1740
-4.500 -0.3677 0.03579 0.02957 -0.0393 1.0000 0.0688
-4.250 -0.3437 0.03131 0.02426 -0.0386 1.0000 0.0567
-4.000 -0.3215 0.02825 0.02079 -0.0381 1.0000 0.0538
-3.750 -0.2971 0.02573 0.01776 -0.0373 1.0000 0.0518
-3.500 -0.2727 0.02393 0.01559 -0.0366 1.0000 0.0525
-3.250 -0.2491 0.02274 0.01410 -0.0357 1.0000 0.0566
-3.000 -0.2254 0.02162 0.01272 -0.0348 1.0000 0.0591
-2.750 -0.2024 0.02000 0.01118 -0.0341 1.0000 0.0643
-2.500 -0.1799 0.01899 0.01014 -0.0332 1.0000 0.0749
-2.250 -0.1570 0.01786 0.00920 -0.0326 1.0000 0.1127
-2.000 -0.1273 0.01503 0.00886 -0.0336 0.9965 0.5655
-1.750 -0.0977 0.01449 0.00926 -0.0316 0.9882 0.8807
-1.500 -0.0334 0.01466 0.00899 -0.0392 0.9793 1.0000
-1.250 0.0180 0.01507 0.00902 -0.0444 0.9702 1.0000
-1.000 0.0628 0.01532 0.00899 -0.0482 0.9587 1.0000
-0.750 0.1066 0.01554 0.00896 -0.0516 0.9471 1.0000
-0.500 0.1510 0.01572 0.00895 -0.0551 0.9357 1.0000
-0.250 0.1978 0.01583 0.00890 -0.0588 0.9251 1.0000
0.000 0.2482 0.01583 0.00875 -0.0631 0.9154 1.0000
0.250 0.2909 0.01579 0.00862 -0.0659 0.9031 1.0000
0.500 0.3315 0.01571 0.00846 -0.0680 0.8906 1.0000
0.750 0.3703 0.01558 0.00827 -0.0696 0.8779 1.0000
1.000 0.4069 0.01542 0.00806 -0.0707 0.8648 1.0000
1.250 0.4412 0.01523 0.00785 -0.0712 0.8511 1.0000
1.500 0.4731 0.01504 0.00762 -0.0712 0.8365 1.0000
1.750 0.5035 0.01484 0.00739 -0.0708 0.8211 1.0000
2.000 0.5326 0.01465 0.00717 -0.0701 0.8051 1.0000
2.250 0.5612 0.01448 0.00698 -0.0693 0.7888 1.0000
2.500 0.5870 0.01443 0.00690 -0.0682 0.7697 1.0000
2.750 0.6131 0.01440 0.00682 -0.0671 0.7502 1.0000
3.000 0.6403 0.01435 0.00670 -0.0661 0.7314 1.0000
3.250 0.6648 0.01445 0.00681 -0.0649 0.7087 1.0000
3.500 0.6908 0.01452 0.00681 -0.0638 0.6874 1.0000
3.750 0.7154 0.01468 0.00692 -0.0627 0.6637 1.0000
4.000 0.7401 0.01488 0.00707 -0.0617 0.6397 1.0000
4.250 0.7651 0.01509 0.00724 -0.0606 0.6163 1.0000
4.500 0.7895 0.01536 0.00745 -0.0596 0.5916 1.0000
4.750 0.8134 0.01567 0.00773 -0.0586 0.5662 1.0000
5.000 0.8373 0.01600 0.00802 -0.0575 0.5407 1.0000
5.250 0.8611 0.01637 0.00835 -0.0565 0.5151 1.0000
5.500 0.8846 0.01676 0.00868 -0.0555 0.4893 1.0000
5.750 0.9076 0.01720 0.00907 -0.0544 0.4629 1.0000
6.000 0.9301 0.01767 0.00952 -0.0534 0.4360 1.0000
6.250 0.9523 0.01818 0.01004 -0.0523 0.4092 1.0000
6.500 0.9742 0.01874 0.01058 -0.0512 0.3824 1.0000
6.750 0.9955 0.01933 0.01116 -0.0500 0.3555 1.0000
7.000 1.0162 0.01996 0.01175 -0.0488 0.3283 1.0000
7.250 1.0361 0.02063 0.01240 -0.0475 0.3011 1.0000
7.500 1.0554 0.02137 0.01314 -0.0462 0.2741 1.0000
7.750 1.0737 0.02217 0.01391 -0.0449 0.2473 1.0000
8.000 1.0913 0.02308 0.01477 -0.0434 0.2210 1.0000
8.250 1.1078 0.02411 0.01573 -0.0419 0.1950 1.0000
8.500 1.1230 0.02527 0.01683 -0.0402 0.1693 1.0000
8.750 1.1369 0.02656 0.01813 -0.0384 0.1444 1.0000
9.000 1.1504 0.02812 0.01968 -0.0365 0.1228 1.0000
9.250 1.1631 0.02967 0.02117 -0.0347 0.1046 1.0000
9.500 1.1763 0.03163 0.02303 -0.0332 0.0892 1.0000
9.750 1.1898 0.03369 0.02512 -0.0315 0.0767 1.0000
10.000 1.2007 0.03537 0.02702 -0.0294 0.0669 1.0000
10.250 1.2156 0.03819 0.03009 -0.0279 0.0594 1.0000
10.500 1.2308 0.04118 0.03298 -0.0271 0.0527 1.0000
10.750 1.2380 0.04374 0.03605 -0.0246 0.0492 1.0000
11.000 1.2454 0.04676 0.03940 -0.0226 0.0464 1.0000
11.250 1.2524 0.04952 0.04223 -0.0211 0.0434 1.0000
11.500 1.2490 0.05391 0.04689 -0.0190 0.0416 1.0000
11.750 1.2363 0.05652 0.04987 -0.0157 0.0408 1.0000
12.000 1.2221 0.05982 0.05351 -0.0134 0.0403 1.0000
12.250 1.2053 0.06360 0.05761 -0.0119 0.0400 1.0000
12.500 1.1874 0.06792 0.06222 -0.0114 0.0399 1.0000
12.750 1.1672 0.07284 0.06741 -0.0119 0.0399 1.0000
13.000 1.1463 0.07835 0.07315 -0.0136 0.0401 1.0000
13.250 1.1252 0.08446 0.07946 -0.0163 0.0405 1.0000
13.500 1.1024 0.09144 0.08661 -0.0201 0.0408 1.0000
13.750 1.0800 0.09913 0.09445 -0.0247 0.0412 1.0000
14.000 1.0594 0.10733 0.10274 -0.0294 0.0417 1.0000
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Polar data table (+)
Polar graphs
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