TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 500,000 Max Cl/Cd: 72.21 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi8-il-500000.txt Download as CSV file: xf-tsagi8-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5643 0.08259 0.08040 -0.0123 1.0000 0.0169
-8.500 -0.5723 0.07753 0.07538 -0.0167 1.0000 0.0171
-8.250 -0.5836 0.07312 0.07096 -0.0189 1.0000 0.0171
-8.000 -0.5901 0.06847 0.06627 -0.0205 1.0000 0.0173
-7.750 -0.5925 0.06352 0.06124 -0.0217 1.0000 0.0177
-5.750 -0.5608 0.02779 0.02361 -0.0062 1.0000 0.0174
-5.500 -0.5585 0.02168 0.01675 -0.0007 1.0000 0.0150
-5.250 -0.5395 0.02141 0.01644 0.0008 1.0000 0.0168
-5.000 -0.5260 0.01853 0.01315 0.0040 1.0000 0.0161
-4.750 -0.5096 0.01642 0.01072 0.0067 1.0000 0.0161
-4.500 -0.4843 0.01494 0.00904 0.0074 0.9988 0.0169
-4.250 -0.4475 0.01369 0.00760 0.0056 0.9951 0.0181
-4.000 -0.4112 0.01290 0.00670 0.0038 0.9904 0.0193
-3.750 -0.3774 0.01146 0.00519 0.0024 0.9851 0.0231
-3.500 -0.3417 0.01083 0.00451 0.0007 0.9790 0.0266
-3.250 -0.3063 0.01020 0.00381 -0.0009 0.9721 0.0304
-3.000 -0.2712 0.00961 0.00319 -0.0025 0.9640 0.0401
-2.750 -0.2348 0.00907 0.00265 -0.0043 0.9551 0.0550
-2.500 -0.2024 0.00845 0.00231 -0.0054 0.9414 0.1203
-2.250 -0.1748 0.00770 0.00205 -0.0057 0.9231 0.2535
-2.000 -0.1542 0.00677 0.00181 -0.0045 0.9014 0.4561
-1.750 -0.1434 0.00577 0.00163 -0.0008 0.8782 0.6913
-1.500 -0.1157 0.00528 0.00173 0.0000 0.8601 0.8767
-1.250 -0.0648 0.00548 0.00189 -0.0045 0.8446 0.9273
-1.000 -0.0293 0.00569 0.00197 -0.0058 0.8256 0.9431
-0.750 0.0118 0.00603 0.00219 -0.0082 0.8076 0.9563
-0.500 0.0584 0.00628 0.00231 -0.0120 0.7897 0.9611
-0.250 0.1035 0.00661 0.00251 -0.0154 0.7722 0.9713
0.000 0.1559 0.00683 0.00263 -0.0206 0.7538 0.9786
0.250 0.1996 0.00695 0.00264 -0.0239 0.7358 0.9850
0.500 0.2454 0.00696 0.00256 -0.0279 0.7181 0.9903
0.750 0.2826 0.00699 0.00251 -0.0300 0.7006 0.9946
1.000 0.3201 0.00690 0.00236 -0.0322 0.6828 0.9977
1.250 0.3538 0.00687 0.00227 -0.0337 0.6653 1.0000
1.500 0.3764 0.00690 0.00225 -0.0327 0.6490 1.0000
1.750 0.3992 0.00694 0.00224 -0.0317 0.6320 1.0000
2.000 0.4221 0.00698 0.00224 -0.0308 0.6139 1.0000
2.250 0.4449 0.00703 0.00227 -0.0299 0.5956 1.0000
2.500 0.4678 0.00710 0.00230 -0.0289 0.5765 1.0000
2.750 0.4906 0.00718 0.00233 -0.0279 0.5523 1.0000
3.000 0.5126 0.00732 0.00235 -0.0268 0.5132 1.0000
3.250 0.5344 0.00752 0.00239 -0.0257 0.4693 1.0000
3.500 0.5568 0.00772 0.00250 -0.0247 0.4313 1.0000
3.750 0.5784 0.00801 0.00262 -0.0236 0.3807 1.0000
4.000 0.5988 0.00851 0.00279 -0.0224 0.2980 1.0000
4.250 0.6145 0.00973 0.00324 -0.0208 0.1306 1.0000
4.500 0.6313 0.01095 0.00397 -0.0191 0.0320 1.0000
4.750 0.6515 0.01163 0.00473 -0.0176 0.0241 1.0000
5.000 0.6731 0.01204 0.00521 -0.0164 0.0217 1.0000
5.250 0.6935 0.01259 0.00584 -0.0150 0.0199 1.0000
5.500 0.7129 0.01328 0.00659 -0.0134 0.0183 1.0000
5.750 0.7271 0.01467 0.00808 -0.0110 0.0162 1.0000
6.000 0.7454 0.01554 0.00904 -0.0092 0.0153 1.0000
6.250 0.7646 0.01634 0.00994 -0.0076 0.0146 1.0000
6.500 0.7828 0.01747 0.01117 -0.0057 0.0141 1.0000
6.750 0.8012 0.01877 0.01259 -0.0039 0.0133 1.0000
7.000 0.8193 0.02053 0.01452 -0.0020 0.0132 1.0000
7.250 0.8366 0.02297 0.01721 0.0001 0.0137 1.0000
|
Polar data table (+)
Polar graphs
<< Back to TSAGI 8% AIRFOIL (tsagi8-il)