NACA 16009 (naca16009-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 16009 (naca16009-il) Reynolds number: 50,000 Max Cl/Cd: 19.81 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16009-il-50000-n5.txt Download as CSV file: xf-naca16009-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6084 0.10051 0.09335 -0.0280 1.0000 0.0393
-9.750 -0.6138 0.09535 0.08823 -0.0308 1.0000 0.0388
-9.500 -0.6222 0.09040 0.08331 -0.0332 1.0000 0.0382
-9.250 -0.6338 0.08597 0.07890 -0.0343 1.0000 0.0376
-9.000 -0.6479 0.08213 0.07506 -0.0337 1.0000 0.0370
-8.750 -0.6636 0.07875 0.07167 -0.0317 1.0000 0.0366
-8.500 -0.6764 0.07525 0.06811 -0.0296 1.0000 0.0363
-8.250 -0.6872 0.07181 0.06457 -0.0271 1.0000 0.0362
-8.000 -0.6960 0.06843 0.06105 -0.0243 1.0000 0.0364
-7.750 -0.7025 0.06508 0.05751 -0.0213 1.0000 0.0367
-7.500 -0.7068 0.06176 0.05397 -0.0181 1.0000 0.0372
-7.250 -0.7089 0.05846 0.05039 -0.0148 1.0000 0.0377
-7.000 -0.7086 0.05518 0.04679 -0.0114 1.0000 0.0381
-6.750 -0.7058 0.05192 0.04316 -0.0080 1.0000 0.0382
-6.500 -0.7003 0.04866 0.03951 -0.0047 1.0000 0.0381
-6.250 -0.6919 0.04549 0.03591 -0.0015 1.0000 0.0380
-6.000 -0.6806 0.04242 0.03238 0.0014 1.0000 0.0381
-5.750 -0.6658 0.03949 0.02895 0.0041 1.0000 0.0384
-5.500 -0.6474 0.03673 0.02568 0.0063 1.0000 0.0391
-5.250 -0.6250 0.03417 0.02262 0.0080 1.0000 0.0402
-5.000 -0.5989 0.03190 0.01987 0.0091 1.0000 0.0417
-4.750 -0.5738 0.02990 0.01780 0.0096 1.0000 0.0467
-4.500 -0.5461 0.02848 0.01605 0.0102 1.0000 0.0552
-4.250 -0.5176 0.02680 0.01415 0.0105 1.0000 0.0634
-4.000 -0.4944 0.02551 0.01272 0.0116 1.0000 0.0814
-3.750 -0.4747 0.02396 0.01131 0.0131 1.0000 0.1125
-3.500 -0.2273 0.02342 0.01291 -0.0213 1.0000 0.9840
-3.250 -0.1690 0.02276 0.01176 -0.0286 1.0000 0.9997
-3.000 -0.1546 0.02244 0.01125 -0.0269 1.0000 1.0000
-2.750 -0.1412 0.02216 0.01080 -0.0249 1.0000 1.0000
-2.500 -0.1278 0.02191 0.01041 -0.0229 1.0000 1.0000
-2.250 -0.1145 0.02170 0.01000 -0.0209 1.0000 1.0000
-2.000 -0.1014 0.02151 0.00970 -0.0187 1.0000 1.0000
-1.750 -0.0884 0.02135 0.00945 -0.0165 1.0000 1.0000
-1.500 -0.0755 0.02122 0.00923 -0.0143 1.0000 1.0000
-1.250 -0.0627 0.02110 0.00905 -0.0120 1.0000 1.0000
-1.000 -0.0501 0.02102 0.00891 -0.0096 1.0000 1.0000
-0.750 -0.0375 0.02095 0.00878 -0.0072 1.0000 1.0000
-0.500 -0.0249 0.02090 0.00870 -0.0048 1.0000 1.0000
-0.250 -0.0125 0.02087 0.00865 -0.0024 1.0000 1.0000
0.000 0.0000 0.02086 0.00863 0.0000 1.0000 1.0000
0.250 0.0125 0.02087 0.00865 0.0024 1.0000 1.0000
0.500 0.0249 0.02090 0.00870 0.0048 1.0000 1.0000
0.750 0.0375 0.02094 0.00878 0.0072 1.0000 1.0000
1.000 0.0501 0.02101 0.00891 0.0096 1.0000 1.0000
1.250 0.0627 0.02110 0.00905 0.0120 1.0000 1.0000
1.500 0.0755 0.02121 0.00922 0.0143 1.0000 1.0000
1.750 0.0884 0.02135 0.00944 0.0165 1.0000 1.0000
2.000 0.1014 0.02150 0.00970 0.0187 1.0000 1.0000
2.250 0.1145 0.02169 0.00999 0.0209 1.0000 1.0000
2.500 0.1278 0.02190 0.01040 0.0229 1.0000 1.0000
2.750 0.1412 0.02215 0.01079 0.0249 1.0000 1.0000
3.000 0.1547 0.02243 0.01124 0.0269 1.0000 1.0000
3.250 0.1689 0.02275 0.01175 0.0286 0.9997 1.0000
3.500 0.2272 0.02341 0.01289 0.0213 0.9840 1.0000
3.750 0.4746 0.02396 0.01131 -0.0131 0.1125 1.0000
4.000 0.4943 0.02550 0.01272 -0.0115 0.0815 1.0000
4.250 0.5175 0.02679 0.01415 -0.0105 0.0634 1.0000
4.500 0.5460 0.02847 0.01605 -0.0102 0.0552 1.0000
4.750 0.5737 0.02989 0.01779 -0.0096 0.0467 1.0000
5.000 0.5988 0.03189 0.01987 -0.0091 0.0417 1.0000
5.250 0.6249 0.03416 0.02261 -0.0079 0.0402 1.0000
5.500 0.6473 0.03672 0.02567 -0.0063 0.0391 1.0000
5.750 0.6657 0.03948 0.02895 -0.0041 0.0384 1.0000
6.000 0.6805 0.04242 0.03237 -0.0014 0.0381 1.0000
6.250 0.6918 0.04548 0.03590 0.0015 0.0380 1.0000
6.500 0.7002 0.04865 0.03950 0.0047 0.0381 1.0000
6.750 0.7057 0.05191 0.04315 0.0080 0.0382 1.0000
7.000 0.7085 0.05518 0.04679 0.0114 0.0381 1.0000
7.250 0.7088 0.05845 0.05039 0.0148 0.0377 1.0000
7.500 0.7068 0.06175 0.05396 0.0181 0.0371 1.0000
7.750 0.7026 0.06507 0.05751 0.0213 0.0367 1.0000
8.000 0.6961 0.06842 0.06104 0.0243 0.0363 1.0000
8.250 0.6873 0.07181 0.06457 0.0271 0.0362 1.0000
8.500 0.6765 0.07525 0.06811 0.0296 0.0363 1.0000
8.750 0.6637 0.07875 0.07167 0.0317 0.0365 1.0000
9.000 0.6482 0.08214 0.07507 0.0337 0.0370 1.0000
9.250 0.6341 0.08599 0.07893 0.0342 0.0376 1.0000
9.500 0.6226 0.09042 0.08334 0.0331 0.0382 1.0000
9.750 0.6142 0.09539 0.08827 0.0307 0.0388 1.0000
10.000 0.6089 0.10057 0.09340 0.0278 0.0393 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 16009 (naca16009-il)