RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 200,000 Max Cl/Cd: 42.71 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30md-il-200000.txt Download as CSV file: xf-raf30md-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 MOD AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6667 0.09489 0.09138 -0.0003 1.0000 0.0485
-9.500 -0.6650 0.09113 0.08763 -0.0015 1.0000 0.0496
-9.250 -0.6673 0.08659 0.08313 -0.0040 1.0000 0.0507
-9.000 -0.6742 0.08110 0.07767 -0.0081 1.0000 0.0519
-8.750 -0.6915 0.07433 0.07091 -0.0145 1.0000 0.0516
-8.500 -0.7058 0.06952 0.06605 -0.0163 1.0000 0.0522
-8.250 -0.7141 0.06478 0.06118 -0.0177 1.0000 0.0536
-8.000 -0.7316 0.06167 0.05743 -0.0182 1.0000 0.0580
-7.750 -0.7350 0.05465 0.05026 -0.0183 1.0000 0.0596
-7.500 -0.7192 0.05135 0.04710 -0.0179 1.0000 0.0618
-7.250 -0.7078 0.04854 0.04417 -0.0172 1.0000 0.0655
-7.000 -0.7042 0.04473 0.03988 -0.0160 1.0000 0.0733
-6.750 -0.6873 0.04210 0.03728 -0.0153 1.0000 0.0773
-6.500 -0.6786 0.02915 0.02240 -0.0096 1.0000 0.0357
-6.250 -0.6597 0.02660 0.01963 -0.0085 1.0000 0.0373
-6.000 -0.6386 0.02465 0.01748 -0.0074 1.0000 0.0391
-5.750 -0.6162 0.02219 0.01463 -0.0059 1.0000 0.0391
-5.500 -0.5929 0.02035 0.01255 -0.0047 1.0000 0.0404
-5.250 -0.5693 0.01896 0.01098 -0.0035 1.0000 0.0430
-5.000 -0.5452 0.01826 0.01009 -0.0025 1.0000 0.0460
-4.750 -0.5245 0.01606 0.00792 -0.0011 1.0000 0.0494
-4.500 -0.5028 0.01514 0.00700 0.0001 1.0000 0.0539
-4.250 -0.4808 0.01436 0.00614 0.0014 1.0000 0.0593
-4.000 -0.4604 0.01344 0.00526 0.0028 1.0000 0.0653
-3.750 -0.4387 0.01279 0.00461 0.0040 1.0000 0.0748
-3.500 -0.4170 0.01211 0.00401 0.0052 1.0000 0.0927
-3.250 -0.4036 0.01024 0.00330 0.0072 1.0000 0.3139
-3.000 -0.3896 0.00914 0.00309 0.0096 1.0000 0.5143
-2.750 -0.3714 0.00869 0.00302 0.0118 1.0000 0.6168
-2.500 -0.3521 0.00841 0.00298 0.0139 1.0000 0.6873
-2.250 -0.3326 0.00821 0.00297 0.0160 1.0000 0.7457
-2.000 -0.3121 0.00808 0.00295 0.0179 1.0000 0.7891
-1.750 -0.2915 0.00798 0.00297 0.0200 1.0000 0.8368
-1.500 -0.2650 0.00802 0.00314 0.0212 1.0000 0.8976
-1.250 -0.2126 0.00828 0.00340 0.0171 1.0000 0.9455
-1.000 -0.1594 0.00843 0.00346 0.0121 1.0000 0.9658
-0.750 -0.1073 0.00850 0.00346 0.0070 1.0000 0.9773
-0.500 -0.0557 0.00850 0.00342 0.0019 1.0000 0.9884
-0.250 -0.0025 0.00847 0.00335 -0.0036 1.0000 0.9987
0.000 0.0000 0.00839 0.00328 0.0000 1.0000 1.0000
0.250 0.0025 0.00847 0.00335 0.0036 0.9987 1.0000
0.500 0.0558 0.00850 0.00342 -0.0019 0.9884 1.0000
0.750 0.1072 0.00850 0.00346 -0.0070 0.9773 1.0000
1.000 0.1594 0.00843 0.00346 -0.0121 0.9658 1.0000
1.250 0.2127 0.00828 0.00340 -0.0171 0.9455 1.0000
1.500 0.2647 0.00803 0.00316 -0.0212 0.8999 1.0000
1.750 0.2918 0.00798 0.00297 -0.0200 0.8376 1.0000
2.000 0.3124 0.00808 0.00295 -0.0180 0.7893 1.0000
2.250 0.3329 0.00821 0.00297 -0.0161 0.7456 1.0000
2.500 0.3524 0.00841 0.00298 -0.0140 0.6872 1.0000
2.750 0.3716 0.00870 0.00302 -0.0119 0.6165 1.0000
3.000 0.3898 0.00915 0.00309 -0.0097 0.5140 1.0000
3.250 0.4038 0.01025 0.00330 -0.0072 0.3109 1.0000
3.500 0.4173 0.01212 0.00401 -0.0053 0.0924 1.0000
3.750 0.4389 0.01279 0.00461 -0.0041 0.0746 1.0000
4.000 0.4606 0.01344 0.00527 -0.0028 0.0653 1.0000
4.250 0.4809 0.01439 0.00617 -0.0014 0.0591 1.0000
4.500 0.5029 0.01514 0.00700 -0.0002 0.0538 1.0000
4.750 0.5247 0.01607 0.00793 0.0010 0.0493 1.0000
5.000 0.5454 0.01817 0.01001 0.0024 0.0461 1.0000
5.250 0.5694 0.01898 0.01100 0.0035 0.0430 1.0000
5.500 0.5930 0.02036 0.01256 0.0046 0.0405 1.0000
5.750 0.6163 0.02221 0.01465 0.0059 0.0392 1.0000
6.000 0.6386 0.02468 0.01753 0.0074 0.0393 1.0000
6.250 0.6596 0.02676 0.01986 0.0086 0.0377 1.0000
6.500 0.6785 0.02919 0.02245 0.0096 0.0356 1.0000
7.250 0.6766 0.03872 0.03413 0.0169 0.0712 1.0000
9.750 0.5639 0.09144 0.08812 0.0006 0.0555 1.0000
10.000 0.5566 0.09698 0.09363 -0.0022 0.0536 1.0000
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Polar data table (+)
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