RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 50,000 Max Cl/Cd: 26.42 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30md-il-50000.txt Download as CSV file: xf-raf30md-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.6943 0.05779 0.05048 -0.0135 1.0000 0.1463
-6.750 -0.6878 0.05170 0.04382 -0.0142 1.0000 0.1317
-6.500 -0.6770 0.04662 0.03796 -0.0137 1.0000 0.1224
-6.250 -0.6606 0.04242 0.03327 -0.0128 1.0000 0.1188
-6.000 -0.6426 0.03889 0.02920 -0.0116 1.0000 0.1192
-5.750 -0.6226 0.03593 0.02562 -0.0103 1.0000 0.1228
-5.500 -0.5996 0.03309 0.02217 -0.0090 1.0000 0.1246
-5.250 -0.5743 0.03015 0.01907 -0.0082 1.0000 0.1285
-5.000 -0.5493 0.02813 0.01673 -0.0071 1.0000 0.1393
-4.750 -0.5222 0.02599 0.01453 -0.0062 1.0000 0.1510
-4.500 -0.4943 0.02401 0.01251 -0.0053 1.0000 0.1669
-4.250 -0.4698 0.02214 0.01095 -0.0042 1.0000 0.2003
-4.000 -0.4523 0.01909 0.00907 -0.0021 1.0000 0.3217
-3.750 -0.4578 0.01733 0.00943 0.0083 1.0000 0.6897
-3.500 -0.4411 0.01790 0.01008 0.0159 1.0000 0.8127
-3.250 -0.2459 0.02058 0.01123 -0.0044 1.0000 0.9651
-3.000 -0.1605 0.01919 0.00924 -0.0176 1.0000 1.0000
-2.750 -0.1473 0.01846 0.00840 -0.0171 1.0000 1.0000
-2.500 -0.1338 0.01784 0.00767 -0.0165 1.0000 1.0000
-2.250 -0.1201 0.01730 0.00704 -0.0156 1.0000 1.0000
-2.000 -0.1063 0.01683 0.00646 -0.0145 1.0000 1.0000
-1.750 -0.0926 0.01643 0.00600 -0.0132 1.0000 1.0000
-1.500 -0.0791 0.01609 0.00560 -0.0118 1.0000 1.0000
-1.250 -0.0657 0.01581 0.00528 -0.0101 1.0000 1.0000
-1.000 -0.0525 0.01558 0.00502 -0.0082 1.0000 1.0000
-0.750 -0.0395 0.01541 0.00483 -0.0063 1.0000 1.0000
-0.500 -0.0265 0.01529 0.00468 -0.0042 1.0000 1.0000
-0.250 -0.0134 0.01522 0.00459 -0.0021 1.0000 1.0000
0.000 0.0000 0.01519 0.00456 0.0000 1.0000 1.0000
0.250 0.0134 0.01522 0.00459 0.0021 1.0000 1.0000
0.500 0.0266 0.01529 0.00468 0.0042 1.0000 1.0000
0.750 0.0395 0.01541 0.00483 0.0063 1.0000 1.0000
1.000 0.0525 0.01558 0.00502 0.0082 1.0000 1.0000
1.250 0.0657 0.01581 0.00528 0.0101 1.0000 1.0000
1.500 0.0791 0.01609 0.00560 0.0118 1.0000 1.0000
1.750 0.0926 0.01643 0.00600 0.0132 1.0000 1.0000
2.000 0.1063 0.01683 0.00646 0.0145 1.0000 1.0000
2.250 0.1201 0.01730 0.00703 0.0156 1.0000 1.0000
2.500 0.1338 0.01784 0.00767 0.0165 1.0000 1.0000
2.750 0.1473 0.01846 0.00840 0.0171 1.0000 1.0000
3.000 0.1604 0.01918 0.00924 0.0176 1.0000 1.0000
3.250 0.2455 0.02057 0.01122 0.0045 0.9654 1.0000
3.500 0.4410 0.01789 0.01007 -0.0158 0.8124 1.0000
3.750 0.4579 0.01733 0.00943 -0.0082 0.6890 1.0000
4.000 0.4523 0.01910 0.00908 0.0021 0.3212 1.0000
4.250 0.4699 0.02215 0.01096 0.0042 0.2002 1.0000
4.500 0.4943 0.02401 0.01251 0.0052 0.1669 1.0000
4.750 0.5222 0.02599 0.01454 0.0062 0.1509 1.0000
5.000 0.5494 0.02813 0.01672 0.0071 0.1394 1.0000
5.250 0.5744 0.03015 0.01907 0.0081 0.1284 1.0000
5.500 0.5996 0.03309 0.02217 0.0090 0.1246 1.0000
5.750 0.6227 0.03593 0.02562 0.0103 0.1229 1.0000
6.000 0.6426 0.03889 0.02920 0.0116 0.1191 1.0000
6.250 0.6606 0.04242 0.03327 0.0128 0.1188 1.0000
6.500 0.6770 0.04661 0.03796 0.0137 0.1224 1.0000
6.750 0.6877 0.05173 0.04385 0.0142 0.1317 1.0000
7.000 0.6942 0.05776 0.05045 0.0135 0.1462 1.0000
7.500 0.5879 0.08637 0.07956 -0.0268 0.4075 1.0000
7.750 0.5882 0.08981 0.08294 -0.0266 0.3948 1.0000
8.000 0.6084 0.09431 0.08747 -0.0255 0.3768 1.0000
8.250 0.6076 0.09754 0.09064 -0.0250 0.3606 1.0000
8.500 0.6057 0.10054 0.09358 -0.0248 0.3447 1.0000
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Polar data table (+)
Polar graphs
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