TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 200,000 Max Cl/Cd: 55.41 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi8-il-200000-n5.txt Download as CSV file: xf-tsagi8-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5594 0.08431 0.08093 -0.0114 1.0000 0.0111
-8.500 -0.5657 0.07937 0.07605 -0.0149 1.0000 0.0107
-8.250 -0.5754 0.07455 0.07125 -0.0181 1.0000 0.0107
-8.000 -0.5829 0.06983 0.06651 -0.0198 1.0000 0.0106
-7.750 -0.5948 0.06180 0.05837 -0.0221 1.0000 0.0092
-7.500 -0.5913 0.05859 0.05507 -0.0222 1.0000 0.0097
-7.250 -0.5891 0.05408 0.05042 -0.0219 1.0000 0.0100
-7.000 -0.5842 0.04992 0.04608 -0.0212 1.0000 0.0104
-6.750 -0.5797 0.04510 0.04100 -0.0197 1.0000 0.0104
-6.500 -0.5720 0.04112 0.03676 -0.0178 1.0000 0.0110
-6.250 -0.5655 0.03646 0.03172 -0.0152 1.0000 0.0109
-6.000 -0.5580 0.03199 0.02679 -0.0120 1.0000 0.0108
-5.750 -0.5476 0.02829 0.02261 -0.0089 1.0000 0.0108
-5.500 -0.5341 0.02527 0.01912 -0.0061 1.0000 0.0109
-5.250 -0.5179 0.02281 0.01623 -0.0037 1.0000 0.0113
-5.000 -0.4997 0.02079 0.01385 -0.0015 1.0000 0.0119
-4.750 -0.4803 0.01926 0.01204 0.0003 1.0000 0.0127
-4.500 -0.4599 0.01847 0.01102 0.0019 1.0000 0.0142
-4.250 -0.4367 0.01651 0.00882 0.0029 0.9981 0.0154
-4.000 -0.4042 0.01507 0.00726 0.0018 0.9906 0.0178
-3.750 -0.3701 0.01431 0.00640 0.0004 0.9823 0.0226
-3.500 -0.3370 0.01344 0.00542 -0.0008 0.9732 0.0280
-3.250 -0.3032 0.01278 0.00472 -0.0022 0.9631 0.0411
-3.000 -0.2691 0.01223 0.00418 -0.0036 0.9522 0.0615
-2.750 -0.2361 0.01166 0.00375 -0.0049 0.9394 0.1030
-2.500 -0.2037 0.01110 0.00336 -0.0061 0.9253 0.1613
-2.250 -0.1740 0.01049 0.00305 -0.0068 0.9090 0.2578
-2.000 -0.1516 0.00948 0.00276 -0.0060 0.8908 0.4515
-1.750 -0.1099 0.00817 0.00294 -0.0080 0.8801 0.8494
-1.500 -0.0504 0.00835 0.00301 -0.0140 0.8675 0.9089
-1.250 -0.0092 0.00849 0.00298 -0.0164 0.8491 0.9292
-1.000 0.0351 0.00881 0.00314 -0.0192 0.8311 0.9546
-0.750 0.0867 0.00904 0.00321 -0.0239 0.8133 0.9709
-0.500 0.1344 0.00914 0.00316 -0.0280 0.7946 0.9831
-0.250 0.1760 0.00914 0.00303 -0.0310 0.7754 0.9906
0.000 0.2114 0.00913 0.00290 -0.0327 0.7567 0.9955
0.250 0.2447 0.00909 0.00276 -0.0340 0.7382 0.9990
0.500 0.2707 0.00910 0.00269 -0.0338 0.7205 1.0000
0.750 0.2935 0.00914 0.00266 -0.0328 0.7037 1.0000
1.000 0.3165 0.00919 0.00263 -0.0319 0.6877 1.0000
1.250 0.3395 0.00924 0.00263 -0.0310 0.6720 1.0000
1.500 0.3628 0.00929 0.00265 -0.0301 0.6563 1.0000
1.750 0.3861 0.00936 0.00270 -0.0292 0.6407 1.0000
2.000 0.4095 0.00943 0.00275 -0.0284 0.6250 1.0000
2.250 0.4330 0.00951 0.00283 -0.0275 0.6094 1.0000
2.500 0.4564 0.00960 0.00293 -0.0267 0.5930 1.0000
2.750 0.4798 0.00971 0.00304 -0.0258 0.5757 1.0000
3.000 0.5031 0.00982 0.00316 -0.0249 0.5569 1.0000
3.250 0.5264 0.00994 0.00330 -0.0240 0.5362 1.0000
3.500 0.5493 0.01010 0.00347 -0.0230 0.5110 1.0000
3.750 0.5713 0.01031 0.00362 -0.0219 0.4757 1.0000
4.000 0.5914 0.01068 0.00377 -0.0204 0.4125 1.0000
4.250 0.6088 0.01141 0.00400 -0.0187 0.3015 1.0000
4.500 0.6237 0.01267 0.00454 -0.0171 0.1516 1.0000
4.750 0.6386 0.01406 0.00537 -0.0153 0.0429 1.0000
5.000 0.6580 0.01486 0.00614 -0.0138 0.0253 1.0000
5.250 0.6778 0.01555 0.00695 -0.0123 0.0198 1.0000
5.500 0.6973 0.01626 0.00780 -0.0108 0.0170 1.0000
5.750 0.7150 0.01719 0.00886 -0.0090 0.0151 1.0000
6.000 0.7289 0.01864 0.01042 -0.0067 0.0132 1.0000
6.250 0.7462 0.01970 0.01162 -0.0049 0.0119 1.0000
6.500 0.7633 0.02097 0.01302 -0.0029 0.0112 1.0000
6.750 0.7808 0.02239 0.01458 -0.0011 0.0108 1.0000
7.000 0.7987 0.02406 0.01643 0.0007 0.0102 1.0000
7.250 0.8166 0.02591 0.01851 0.0025 0.0099 1.0000
7.500 0.8336 0.02780 0.02065 0.0043 0.0095 1.0000
7.750 0.8494 0.02917 0.02219 0.0059 0.0086 1.0000
8.000 0.8626 0.03090 0.02408 0.0076 0.0080 1.0000
8.500 0.8761 0.03728 0.03117 0.0127 0.0074 1.0000
8.750 0.8803 0.04007 0.03433 0.0154 0.0074 1.0000
9.000 0.8804 0.04313 0.03773 0.0182 0.0074 1.0000
9.250 0.8765 0.04626 0.04115 0.0211 0.0074 1.0000
9.500 0.8679 0.04941 0.04459 0.0240 0.0073 1.0000
9.750 0.8551 0.05216 0.04752 0.0272 0.0074 1.0000
10.000 0.8393 0.05527 0.05078 0.0294 0.0074 1.0000
10.250 0.8239 0.05881 0.05448 0.0299 0.0074 1.0000
10.500 0.8078 0.06317 0.05900 0.0288 0.0075 1.0000
10.750 0.7909 0.06828 0.06424 0.0261 0.0075 1.0000
11.000 0.6972 0.06212 0.05836 0.0276 0.0076 1.0000
11.250 0.6818 0.06824 0.06460 0.0245 0.0077 1.0000
11.500 0.6625 0.07597 0.07245 0.0204 0.0078 1.0000
11.750 0.6386 0.08606 0.08265 0.0151 0.0081 1.0000
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Polar data table (+)
Polar graphs
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