RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.87 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30md-il-1000000.txt Download as CSV file: xf-raf30md-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8816 0.03905 0.03662 -0.0201 1.0000 0.0067
-9.250 -0.9210 0.02702 0.02357 -0.0147 1.0000 0.0067
-9.000 -0.9106 0.02412 0.02031 -0.0128 1.0000 0.0071
-8.750 -0.8948 0.02215 0.01807 -0.0113 1.0000 0.0073
-8.500 -0.8740 0.02125 0.01702 -0.0104 1.0000 0.0075
-8.250 -0.8587 0.01894 0.01437 -0.0087 1.0000 0.0077
-8.000 -0.8451 0.01625 0.01134 -0.0066 1.0000 0.0083
-7.750 -0.8241 0.01530 0.01029 -0.0055 1.0000 0.0086
-7.500 -0.8015 0.01473 0.00966 -0.0047 1.0000 0.0091
-7.250 -0.7787 0.01417 0.00904 -0.0038 1.0000 0.0096
-7.000 -0.7560 0.01362 0.00842 -0.0029 1.0000 0.0102
-6.750 -0.7320 0.01331 0.00805 -0.0022 1.0000 0.0109
-6.500 -0.7074 0.01313 0.00783 -0.0016 1.0000 0.0113
-6.250 -0.6907 0.01153 0.00607 0.0004 1.0000 0.0125
-6.000 -0.6674 0.01116 0.00570 0.0013 1.0000 0.0135
-5.750 -0.6436 0.01088 0.00541 0.0020 1.0000 0.0146
-5.500 -0.6199 0.01059 0.00509 0.0029 1.0000 0.0157
-5.250 -0.5953 0.01049 0.00496 0.0036 1.0000 0.0164
-5.000 -0.5751 0.00968 0.00411 0.0050 1.0000 0.0192
-4.750 -0.5514 0.00947 0.00390 0.0058 1.0000 0.0212
-4.500 -0.5278 0.00929 0.00371 0.0067 1.0000 0.0230
-4.250 -0.5036 0.00923 0.00364 0.0075 1.0000 0.0238
-4.000 -0.4831 0.00855 0.00289 0.0089 1.0000 0.0281
-3.750 -0.4602 0.00833 0.00265 0.0099 1.0000 0.0307
-3.500 -0.4301 0.00812 0.00243 0.0093 0.9990 0.0329
-3.250 -0.3941 0.00793 0.00221 0.0075 0.9965 0.0350
-3.000 -0.3578 0.00766 0.00193 0.0056 0.9940 0.0404
-2.750 -0.3235 0.00742 0.00172 0.0041 0.9900 0.0495
-2.500 -0.2901 0.00666 0.00145 0.0025 0.9858 0.1669
-2.250 -0.2565 0.00588 0.00124 0.0007 0.9817 0.3148
-2.000 -0.2249 0.00538 0.00110 -0.0004 0.9742 0.4139
-1.750 -0.1913 0.00494 0.00099 -0.0019 0.9664 0.5082
-1.500 -0.1576 0.00467 0.00092 -0.0032 0.9551 0.5715
-1.250 -0.1270 0.00449 0.00085 -0.0037 0.9381 0.6145
-1.000 -0.0990 0.00434 0.00080 -0.0036 0.9159 0.6575
-0.750 -0.0728 0.00426 0.00076 -0.0030 0.8910 0.6903
-0.500 -0.0481 0.00419 0.00075 -0.0021 0.8659 0.7324
-0.250 -0.0235 0.00414 0.00074 -0.0012 0.8421 0.7706
0.000 0.0001 0.00410 0.00075 0.0000 0.8127 0.8127
0.500 0.0482 0.00419 0.00075 0.0021 0.7317 0.8659
0.750 0.0730 0.00426 0.00077 0.0030 0.6907 0.8909
1.000 0.0991 0.00435 0.00080 0.0036 0.6570 0.9159
1.250 0.1271 0.00449 0.00085 0.0037 0.6149 0.9380
1.500 0.1577 0.00467 0.00092 0.0031 0.5729 0.9551
1.750 0.1913 0.00494 0.00099 0.0019 0.5078 0.9661
2.000 0.2249 0.00537 0.00110 0.0004 0.4145 0.9742
2.250 0.2566 0.00588 0.00124 -0.0007 0.3151 0.9815
2.500 0.2900 0.00664 0.00145 -0.0024 0.1689 0.9857
2.750 0.3234 0.00742 0.00172 -0.0041 0.0491 0.9900
3.000 0.3577 0.00767 0.00193 -0.0055 0.0403 0.9939
3.250 0.3939 0.00793 0.00222 -0.0074 0.0351 0.9964
3.500 0.4300 0.00813 0.00243 -0.0093 0.0329 0.9989
3.750 0.4606 0.00833 0.00266 -0.0100 0.0306 1.0000
4.000 0.4834 0.00855 0.00289 -0.0090 0.0281 1.0000
4.250 0.5040 0.00921 0.00362 -0.0076 0.0238 1.0000
4.500 0.5281 0.00928 0.00370 -0.0068 0.0230 1.0000
4.750 0.5518 0.00947 0.00390 -0.0059 0.0212 1.0000
5.000 0.5754 0.00970 0.00412 -0.0051 0.0192 1.0000
5.250 0.5957 0.01046 0.00493 -0.0037 0.0164 1.0000
5.500 0.6200 0.01062 0.00512 -0.0029 0.0158 1.0000
5.750 0.6438 0.01089 0.00542 -0.0021 0.0147 1.0000
6.000 0.6675 0.01119 0.00573 -0.0013 0.0135 1.0000
6.250 0.6909 0.01154 0.00609 -0.0005 0.0126 1.0000
6.500 0.7079 0.01308 0.00779 0.0015 0.0113 1.0000
6.750 0.7324 0.01327 0.00801 0.0022 0.0108 1.0000
7.000 0.7560 0.01364 0.00844 0.0029 0.0102 1.0000
7.250 0.7789 0.01414 0.00900 0.0038 0.0096 1.0000
7.500 0.8016 0.01471 0.00964 0.0047 0.0091 1.0000
7.750 0.8242 0.01529 0.01028 0.0055 0.0086 1.0000
8.000 0.8450 0.01624 0.01133 0.0066 0.0082 1.0000
8.250 0.8600 0.01860 0.01399 0.0085 0.0078 1.0000
8.500 0.8741 0.02119 0.01695 0.0103 0.0075 1.0000
8.750 0.8930 0.02253 0.01849 0.0115 0.0073 1.0000
9.000 0.9113 0.02391 0.02007 0.0127 0.0070 1.0000
9.250 0.9210 0.02697 0.02352 0.0147 0.0068 1.0000
9.500 0.8818 0.03896 0.03653 0.0202 0.0067 1.0000
9.750 0.8290 0.05053 0.04864 0.0232 0.0070 1.0000
10.000 0.7957 0.05621 0.05448 0.0245 0.0070 1.0000
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Polar data table (+)
Polar graphs
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