TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 500,000 Max Cl/Cd: 65.07 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi8-il-500000-n5.txt Download as CSV file: xf-tsagi8-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 8% 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5721 0.08276 0.08059 -0.0110 1.0000 0.0045
-8.750 -0.5812 0.07716 0.07505 -0.0150 1.0000 0.0046
-8.500 -0.5923 0.07236 0.07026 -0.0187 1.0000 0.0045
-8.250 -0.6030 0.06744 0.06531 -0.0203 1.0000 0.0045
-8.000 -0.6087 0.06212 0.05991 -0.0219 1.0000 0.0044
-7.750 -0.6106 0.05715 0.05484 -0.0224 1.0000 0.0042
-7.500 -0.6135 0.05114 0.04866 -0.0220 1.0000 0.0042
-7.250 -0.6156 0.04471 0.04199 -0.0205 1.0000 0.0041
-7.000 -0.6196 0.03725 0.03417 -0.0174 1.0000 0.0041
-6.750 -0.6323 0.02728 0.02345 -0.0112 1.0000 0.0040
-6.500 -0.6270 0.02277 0.01832 -0.0072 1.0000 0.0042
-6.250 -0.6144 0.02006 0.01517 -0.0043 1.0000 0.0044
-6.000 -0.5985 0.01812 0.01287 -0.0019 1.0000 0.0047
-5.750 -0.5719 0.01668 0.01114 -0.0018 0.9972 0.0050
-5.500 -0.5429 0.01509 0.00930 -0.0023 0.9913 0.0054
-5.250 -0.5114 0.01438 0.00852 -0.0034 0.9855 0.0061
-5.000 -0.4805 0.01340 0.00740 -0.0041 0.9785 0.0066
-4.750 -0.4489 0.01249 0.00633 -0.0050 0.9704 0.0071
-4.500 -0.4160 0.01176 0.00546 -0.0062 0.9604 0.0079
-4.250 -0.3826 0.01092 0.00448 -0.0074 0.9475 0.0092
-4.000 -0.3483 0.01042 0.00393 -0.0089 0.9311 0.0117
-3.750 -0.3161 0.01003 0.00342 -0.0098 0.9107 0.0140
-3.500 -0.2885 0.00966 0.00297 -0.0096 0.8876 0.0216
-3.250 -0.2625 0.00945 0.00267 -0.0092 0.8645 0.0299
-2.750 -0.2128 0.00908 0.00218 -0.0078 0.8221 0.0535
-2.500 -0.1886 0.00885 0.00198 -0.0071 0.8031 0.0873
-2.250 -0.1641 0.00865 0.00180 -0.0064 0.7855 0.1169
-2.000 -0.1397 0.00844 0.00164 -0.0057 0.7685 0.1570
-1.750 -0.1157 0.00818 0.00149 -0.0050 0.7519 0.2138
-1.500 -0.0920 0.00791 0.00137 -0.0043 0.7364 0.2800
-1.250 -0.0708 0.00742 0.00123 -0.0031 0.7216 0.4042
-0.750 -0.0414 0.00578 0.00112 0.0027 0.6945 0.8405
-0.500 -0.0055 0.00578 0.00116 0.0011 0.6806 0.8887
-0.250 0.0394 0.00590 0.00124 -0.0025 0.6663 0.9189
0.000 0.0865 0.00614 0.00140 -0.0065 0.6521 0.9446
0.500 0.1552 0.00653 0.00165 -0.0090 0.6254 0.9664
0.750 0.1967 0.00669 0.00173 -0.0120 0.6116 0.9706
1.000 0.2285 0.00679 0.00177 -0.0129 0.5977 0.9744
1.250 0.2570 0.00687 0.00181 -0.0131 0.5839 0.9776
1.500 0.2893 0.00693 0.00182 -0.0142 0.5697 0.9791
1.750 0.3208 0.00700 0.00185 -0.0151 0.5550 0.9810
2.000 0.3512 0.00708 0.00190 -0.0158 0.5381 0.9832
2.250 0.3800 0.00719 0.00196 -0.0161 0.5192 0.9859
2.500 0.4109 0.00730 0.00202 -0.0170 0.4991 0.9877
2.750 0.4424 0.00742 0.00209 -0.0179 0.4747 0.9893
3.000 0.4729 0.00759 0.00217 -0.0187 0.4430 0.9912
3.250 0.5027 0.00776 0.00228 -0.0193 0.4135 0.9931
3.500 0.5303 0.00815 0.00243 -0.0197 0.3491 0.9950
3.750 0.5575 0.00882 0.00264 -0.0202 0.2387 0.9965
4.000 0.5830 0.00978 0.00304 -0.0205 0.1114 0.9981
4.250 0.6102 0.01052 0.00345 -0.0210 0.0405 0.9995
4.500 0.6348 0.01098 0.00384 -0.0206 0.0181 1.0000
4.750 0.6567 0.01138 0.00429 -0.0195 0.0126 1.0000
5.000 0.6788 0.01172 0.00471 -0.0184 0.0109 1.0000
5.250 0.7003 0.01210 0.00514 -0.0174 0.0090 1.0000
5.500 0.7197 0.01281 0.00595 -0.0158 0.0076 1.0000
5.750 0.7398 0.01338 0.00661 -0.0144 0.0071 1.0000
6.000 0.7593 0.01402 0.00738 -0.0129 0.0065 1.0000
6.250 0.7778 0.01476 0.00822 -0.0112 0.0061 1.0000
6.500 0.7977 0.01528 0.00877 -0.0099 0.0054 1.0000
6.750 0.8167 0.01588 0.00941 -0.0086 0.0050 1.0000
7.000 0.8320 0.01704 0.01069 -0.0064 0.0046 1.0000
7.250 0.8487 0.01806 0.01184 -0.0045 0.0044 1.0000
7.500 0.8654 0.01914 0.01307 -0.0026 0.0042 1.0000
7.750 0.8811 0.02052 0.01463 -0.0005 0.0039 1.0000
8.000 0.8962 0.02207 0.01638 0.0016 0.0037 1.0000
8.250 0.9105 0.02373 0.01826 0.0037 0.0036 1.0000
8.500 0.9227 0.02582 0.02067 0.0061 0.0035 1.0000
8.750 0.9328 0.02806 0.02320 0.0086 0.0034 1.0000
9.000 0.9377 0.03116 0.02667 0.0117 0.0034 1.0000
9.250 0.9371 0.03478 0.03068 0.0153 0.0034 1.0000
9.500 0.9299 0.03890 0.03518 0.0191 0.0034 1.0000
9.750 0.9183 0.04299 0.03959 0.0229 0.0034 1.0000
10.000 0.9079 0.04556 0.04234 0.0265 0.0034 1.0000
10.250 0.8870 0.04902 0.04599 0.0302 0.0034 1.0000
10.500 0.8840 0.05028 0.04733 0.0311 0.0032 1.0000
10.750 0.8801 0.05199 0.04911 0.0311 0.0031 1.0000
11.000 0.8317 0.06267 0.06012 0.0275 0.0034 1.0000
11.250 0.8041 0.07124 0.06885 0.0219 0.0037 1.0000
11.500 0.7836 0.08013 0.07785 0.0153 0.0037 1.0000
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Polar data table (+)
Polar graphs
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