NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 200,000 Max Cl/Cd: 50.43 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65209-il-200000-n5.txt Download as CSV file: xf-naca65209-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5416 0.08764 0.08409 -0.0255 1.0000 0.0154
-9.250 -0.5448 0.08257 0.07906 -0.0287 1.0000 0.0151
-9.000 -0.5505 0.07682 0.07336 -0.0331 1.0000 0.0148
-8.750 -0.5614 0.07088 0.06742 -0.0383 1.0000 0.0147
-8.500 -0.5751 0.06643 0.06294 -0.0403 1.0000 0.0144
-8.250 -0.5833 0.06181 0.05823 -0.0415 1.0000 0.0142
-8.000 -0.5886 0.05715 0.05343 -0.0420 1.0000 0.0139
-7.750 -0.5910 0.05257 0.04867 -0.0416 1.0000 0.0138
-7.500 -0.5908 0.04819 0.04406 -0.0406 1.0000 0.0136
-7.250 -0.5889 0.04404 0.03966 -0.0389 1.0000 0.0135
-7.000 -0.5853 0.04020 0.03553 -0.0368 1.0000 0.0136
-6.750 -0.5804 0.03670 0.03172 -0.0343 1.0000 0.0138
-6.500 -0.5599 0.03236 0.02688 -0.0346 0.9955 0.0143
-6.250 -0.5311 0.02880 0.02275 -0.0357 0.9896 0.0157
-6.000 -0.4986 0.02686 0.02030 -0.0369 0.9848 0.0171
-5.750 -0.4712 0.02289 0.01582 -0.0379 0.9793 0.0179
-5.500 -0.4391 0.02099 0.01369 -0.0394 0.9755 0.0191
-5.250 -0.4087 0.01988 0.01241 -0.0404 0.9694 0.0208
-5.000 -0.3756 0.01879 0.01115 -0.0417 0.9651 0.0232
-4.750 -0.3457 0.01750 0.00965 -0.0421 0.9587 0.0243
-4.500 -0.3140 0.01643 0.00845 -0.0430 0.9535 0.0256
-4.250 -0.2839 0.01567 0.00759 -0.0436 0.9470 0.0266
-4.000 -0.2558 0.01446 0.00639 -0.0442 0.9404 0.0302
-3.750 -0.2272 0.01378 0.00565 -0.0446 0.9333 0.0323
-3.500 -0.1984 0.01320 0.00497 -0.0450 0.9263 0.0349
-3.250 -0.1705 0.01277 0.00442 -0.0452 0.9187 0.0381
-3.000 -0.1423 0.01229 0.00390 -0.0454 0.9116 0.0457
-2.750 -0.1155 0.01188 0.00351 -0.0454 0.9036 0.0628
-2.500 -0.0917 0.01062 0.00302 -0.0455 0.8965 0.2620
-2.250 -0.0750 0.00917 0.00302 -0.0439 0.8875 0.6241
-2.000 -0.0519 0.00906 0.00318 -0.0423 0.8807 0.7156
-1.750 -0.0275 0.00907 0.00323 -0.0412 0.8727 0.7526
-1.500 -0.0026 0.00910 0.00325 -0.0401 0.8662 0.7802
-1.250 0.0231 0.00911 0.00323 -0.0394 0.8584 0.7962
-1.000 0.0501 0.00909 0.00316 -0.0391 0.8519 0.8035
-0.750 0.0773 0.00908 0.00309 -0.0390 0.8444 0.8120
-0.500 0.1041 0.00907 0.00304 -0.0387 0.8382 0.8188
-0.250 0.1311 0.00907 0.00302 -0.0385 0.8306 0.8271
0.000 0.1578 0.00907 0.00300 -0.0381 0.8245 0.8343
0.250 0.1845 0.00908 0.00301 -0.0379 0.8170 0.8424
0.500 0.2112 0.00909 0.00302 -0.0375 0.8110 0.8502
0.750 0.2375 0.00910 0.00306 -0.0372 0.8034 0.8581
1.000 0.2643 0.00912 0.00308 -0.0369 0.7975 0.8666
1.250 0.2902 0.00915 0.00318 -0.0364 0.7897 0.8747
1.500 0.3168 0.00918 0.00322 -0.0361 0.7836 0.8836
1.750 0.3426 0.00921 0.00333 -0.0356 0.7756 0.8924
2.000 0.3690 0.00923 0.00340 -0.0351 0.7689 0.9015
2.250 0.3950 0.00925 0.00352 -0.0347 0.7587 0.9117
2.500 0.4199 0.00921 0.00347 -0.0336 0.7357 0.9218
2.750 0.4438 0.00916 0.00332 -0.0323 0.6931 0.9323
3.000 0.4670 0.00926 0.00317 -0.0308 0.6190 0.9439
3.250 0.4892 0.00980 0.00317 -0.0296 0.4785 0.9568
3.500 0.5042 0.01199 0.00384 -0.0288 0.1584 0.9747
3.750 0.5323 0.01314 0.00447 -0.0299 0.0536 0.9982
4.000 0.5557 0.01368 0.00498 -0.0294 0.0411 1.0000
4.250 0.5787 0.01428 0.00559 -0.0289 0.0340 1.0000
4.500 0.6021 0.01489 0.00631 -0.0283 0.0313 1.0000
4.750 0.6253 0.01554 0.00705 -0.0277 0.0293 1.0000
5.000 0.6479 0.01631 0.00788 -0.0270 0.0275 1.0000
5.250 0.6703 0.01718 0.00880 -0.0263 0.0262 1.0000
5.500 0.6931 0.01806 0.00971 -0.0257 0.0245 1.0000
5.750 0.7146 0.01943 0.01113 -0.0250 0.0224 1.0000
6.000 0.7382 0.02085 0.01264 -0.0244 0.0215 1.0000
6.250 0.7631 0.02205 0.01399 -0.0240 0.0208 1.0000
6.500 0.7880 0.02353 0.01565 -0.0235 0.0201 1.0000
6.750 0.8126 0.02524 0.01760 -0.0230 0.0193 1.0000
7.000 0.8361 0.02665 0.01924 -0.0224 0.0177 1.0000
7.250 0.8584 0.02815 0.02099 -0.0218 0.0165 1.0000
7.500 0.8792 0.03014 0.02327 -0.0210 0.0157 1.0000
7.750 0.8980 0.03228 0.02568 -0.0201 0.0151 1.0000
8.000 0.9141 0.03482 0.02852 -0.0190 0.0146 1.0000
8.500 0.9322 0.04197 0.03656 -0.0153 0.0131 1.0000
8.750 0.9374 0.04603 0.04109 -0.0131 0.0123 1.0000
9.000 0.9359 0.05075 0.04622 -0.0108 0.0119 1.0000
9.250 0.9301 0.05530 0.05109 -0.0086 0.0118 1.0000
9.500 0.9193 0.05971 0.05577 -0.0065 0.0118 1.0000
9.750 0.9025 0.06363 0.05987 -0.0042 0.0118 1.0000
10.000 0.8839 0.06783 0.06424 -0.0034 0.0118 1.0000
10.250 0.8644 0.07270 0.06924 -0.0043 0.0119 1.0000
10.500 0.8440 0.07869 0.07534 -0.0071 0.0120 1.0000
10.750 0.8251 0.08598 0.08272 -0.0120 0.0122 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65-209 (naca65209-il)