RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 500,000 Max Cl/Cd: 52.26 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30md-il-500000-n5.txt Download as CSV file: xf-raf30md-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.8850 0.04224 0.03943 -0.0203 1.0000 0.0043
-9.500 -0.9053 0.03500 0.03162 -0.0177 1.0000 0.0043
-9.250 -0.9058 0.03051 0.02663 -0.0155 1.0000 0.0044
-9.000 -0.8979 0.02719 0.02288 -0.0136 1.0000 0.0045
-8.750 -0.8847 0.02469 0.02002 -0.0120 1.0000 0.0047
-8.500 -0.8690 0.02255 0.01755 -0.0106 1.0000 0.0049
-8.250 -0.8509 0.02087 0.01559 -0.0093 1.0000 0.0052
-8.000 -0.8316 0.01940 0.01389 -0.0081 1.0000 0.0054
-7.750 -0.8108 0.01829 0.01254 -0.0070 1.0000 0.0056
-7.500 -0.7917 0.01685 0.01090 -0.0057 1.0000 0.0060
-7.250 -0.7706 0.01592 0.00987 -0.0047 1.0000 0.0064
-7.000 -0.7476 0.01540 0.00931 -0.0040 1.0000 0.0070
-6.750 -0.7246 0.01487 0.00870 -0.0033 1.0000 0.0077
-6.500 -0.7025 0.01417 0.00789 -0.0023 1.0000 0.0083
-6.250 -0.6801 0.01353 0.00715 -0.0013 1.0000 0.0088
-6.000 -0.6594 0.01263 0.00615 0.0001 1.0000 0.0102
-5.750 -0.6363 0.01219 0.00568 0.0009 1.0000 0.0116
-5.500 -0.6126 0.01187 0.00534 0.0017 1.0000 0.0135
-5.250 -0.5899 0.01137 0.00478 0.0026 1.0000 0.0162
-5.000 -0.5663 0.01103 0.00445 0.0035 1.0000 0.0205
-4.750 -0.5421 0.01083 0.00421 0.0042 1.0000 0.0244
-4.500 -0.5177 0.01072 0.00406 0.0048 1.0000 0.0260
-4.250 -0.4949 0.01032 0.00360 0.0058 1.0000 0.0287
-4.000 -0.4717 0.01002 0.00328 0.0066 1.0000 0.0316
-3.750 -0.4483 0.00978 0.00301 0.0075 1.0000 0.0337
-3.500 -0.4143 0.00955 0.00273 0.0060 0.9964 0.0360
-3.250 -0.3811 0.00932 0.00246 0.0048 0.9920 0.0382
-3.000 -0.3474 0.00904 0.00220 0.0034 0.9873 0.0459
-2.750 -0.3160 0.00857 0.00195 0.0024 0.9810 0.0984
-2.500 -0.2839 0.00810 0.00173 0.0011 0.9743 0.1615
-2.250 -0.2512 0.00762 0.00154 -0.0002 0.9662 0.2417
-2.000 -0.2185 0.00719 0.00139 -0.0016 0.9556 0.3193
-1.750 -0.1858 0.00677 0.00124 -0.0028 0.9416 0.3977
-1.500 -0.1536 0.00639 0.00114 -0.0039 0.9235 0.4775
-1.250 -0.1242 0.00616 0.00105 -0.0042 0.8988 0.5360
-1.000 -0.0981 0.00594 0.00099 -0.0037 0.8719 0.6001
-0.750 -0.0739 0.00577 0.00097 -0.0027 0.8462 0.6610
-0.500 -0.0502 0.00562 0.00097 -0.0016 0.8232 0.7195
-0.250 -0.0256 0.00556 0.00097 -0.0007 0.8013 0.7577
0.000 0.0000 0.00556 0.00097 0.0000 0.7805 0.7804
0.250 0.0257 0.00556 0.00097 0.0006 0.7585 0.8013
0.500 0.0503 0.00562 0.00097 0.0016 0.7192 0.8231
0.750 0.0740 0.00576 0.00097 0.0027 0.6628 0.8460
1.000 0.0982 0.00594 0.00099 0.0036 0.6010 0.8720
1.250 0.1242 0.00616 0.00106 0.0042 0.5354 0.8990
1.500 0.1536 0.00639 0.00114 0.0039 0.4783 0.9233
1.750 0.1858 0.00677 0.00124 0.0028 0.3985 0.9415
2.000 0.2185 0.00718 0.00139 0.0016 0.3198 0.9556
2.250 0.2511 0.00763 0.00154 0.0002 0.2395 0.9662
2.500 0.2838 0.00810 0.00173 -0.0011 0.1619 0.9742
2.750 0.3159 0.00857 0.00195 -0.0023 0.0994 0.9809
3.000 0.3473 0.00905 0.00220 -0.0034 0.0455 0.9872
3.250 0.3810 0.00932 0.00245 -0.0048 0.0384 0.9919
3.500 0.4142 0.00955 0.00274 -0.0060 0.0360 0.9963
3.750 0.4481 0.00978 0.00301 -0.0075 0.0337 0.9999
4.000 0.4719 0.01002 0.00328 -0.0067 0.0316 1.0000
4.250 0.4951 0.01032 0.00360 -0.0058 0.0288 1.0000
4.500 0.5179 0.01071 0.00406 -0.0049 0.0260 1.0000
4.750 0.5423 0.01083 0.00421 -0.0042 0.0244 1.0000
5.000 0.5665 0.01103 0.00445 -0.0035 0.0204 1.0000
5.250 0.5900 0.01137 0.00478 -0.0027 0.0161 1.0000
5.500 0.6128 0.01186 0.00532 -0.0017 0.0135 1.0000
5.750 0.6365 0.01218 0.00569 -0.0009 0.0116 1.0000
6.000 0.6595 0.01263 0.00615 -0.0001 0.0102 1.0000
6.250 0.6802 0.01353 0.00716 0.0012 0.0088 1.0000
6.500 0.7025 0.01417 0.00789 0.0022 0.0083 1.0000
6.750 0.7246 0.01488 0.00871 0.0033 0.0077 1.0000
7.000 0.7471 0.01550 0.00943 0.0041 0.0071 1.0000
7.250 0.7703 0.01598 0.00994 0.0048 0.0064 1.0000
7.500 0.7916 0.01685 0.01091 0.0058 0.0060 1.0000
7.750 0.8106 0.01831 0.01255 0.0071 0.0056 1.0000
8.000 0.8313 0.01943 0.01392 0.0081 0.0054 1.0000
8.250 0.8507 0.02087 0.01560 0.0093 0.0052 1.0000
8.500 0.8686 0.02260 0.01761 0.0106 0.0049 1.0000
8.750 0.8846 0.02465 0.01998 0.0120 0.0047 1.0000
9.000 0.8974 0.02723 0.02293 0.0137 0.0045 1.0000
9.250 0.9059 0.03042 0.02654 0.0155 0.0044 1.0000
9.500 0.9044 0.03512 0.03175 0.0178 0.0043 1.0000
10.500 0.7397 0.08238 0.08022 0.0023 0.0049 1.0000
10.750 0.7235 0.09095 0.08874 -0.0028 0.0050 1.0000
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Polar data table (+)
Polar graphs
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