NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 100,000 Max Cl/Cd: 43.61 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65209-il-100000.txt Download as CSV file: xf-naca65209-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5320 0.10841 0.10334 -0.0173 1.0000 0.0853
-9.750 -0.5467 0.10471 0.09975 -0.0235 1.0000 0.0874
-9.500 -0.5634 0.10037 0.09554 -0.0304 1.0000 0.0879
-9.250 -0.5291 0.09642 0.09148 -0.0219 1.0000 0.0940
-9.000 -0.5320 0.09255 0.08767 -0.0245 1.0000 0.0983
-8.750 -0.5465 0.08806 0.08327 -0.0303 1.0000 0.1004
-8.500 -0.4485 0.07630 0.07181 -0.0279 1.0000 0.1232
-8.250 -0.5579 0.07922 0.07455 -0.0340 1.0000 0.1052
-8.000 -0.5557 0.07591 0.07126 -0.0342 1.0000 0.1104
-7.750 -0.5760 0.07220 0.06742 -0.0384 1.0000 0.1145
-7.500 -0.5656 0.06814 0.06346 -0.0368 1.0000 0.1214
-7.250 -0.5852 0.06614 0.06105 -0.0390 1.0000 0.1293
-7.000 -0.5683 0.06174 0.05693 -0.0369 1.0000 0.1406
-6.750 -0.5671 0.05878 0.05393 -0.0359 1.0000 0.1546
-6.500 -0.5637 0.05586 0.05100 -0.0344 1.0000 0.1680
-6.000 -0.5584 0.05037 0.04549 -0.0306 1.0000 0.2035
-5.000 -0.4920 0.03333 0.02562 -0.0266 1.0000 0.0895
-4.750 -0.4700 0.03030 0.02191 -0.0245 1.0000 0.0756
-4.500 -0.4501 0.02839 0.01965 -0.0230 1.0000 0.0752
-4.250 -0.4287 0.02624 0.01728 -0.0217 1.0000 0.0731
-4.000 -0.4068 0.02420 0.01501 -0.0205 1.0000 0.0717
-3.750 -0.3843 0.02260 0.01319 -0.0192 1.0000 0.0717
-3.500 -0.3622 0.02154 0.01191 -0.0180 1.0000 0.0737
-3.250 -0.3407 0.02007 0.01052 -0.0171 1.0000 0.0791
-3.000 -0.3194 0.01909 0.00952 -0.0159 1.0000 0.0829
-2.750 -0.2988 0.01835 0.00872 -0.0147 1.0000 0.0878
-2.500 -0.2788 0.01746 0.00794 -0.0138 1.0000 0.0986
-2.250 -0.2577 0.01668 0.00724 -0.0131 1.0000 0.1215
-2.000 -0.2519 0.01385 0.00737 -0.0085 1.0000 0.7336
-1.750 -0.2596 0.01421 0.00803 0.0012 1.0000 0.8500
-1.500 -0.1046 0.01588 0.00918 -0.0146 1.0000 0.9959
-1.250 -0.0924 0.01576 0.00895 -0.0141 1.0000 1.0000
-1.000 -0.1046 0.01551 0.00868 -0.0095 1.0000 1.0000
-0.750 -0.0746 0.01560 0.00861 -0.0119 0.9941 1.0000
-0.500 -0.0390 0.01573 0.00861 -0.0152 0.9859 1.0000
-0.250 -0.0054 0.01589 0.00868 -0.0179 0.9778 1.0000
0.000 0.0310 0.01613 0.00882 -0.0211 0.9705 1.0000
0.250 0.0580 0.01628 0.00890 -0.0224 0.9615 1.0000
0.500 0.0979 0.01660 0.00917 -0.0259 0.9555 1.0000
0.750 0.1221 0.01680 0.00933 -0.0264 0.9462 1.0000
1.000 0.1593 0.01713 0.00965 -0.0292 0.9399 1.0000
1.250 0.1882 0.01740 0.00992 -0.0304 0.9315 1.0000
1.500 0.2227 0.01774 0.01027 -0.0325 0.9246 1.0000
1.750 0.2551 0.01806 0.01063 -0.0342 0.9168 1.0000
2.000 0.2864 0.01840 0.01104 -0.0355 0.9088 1.0000
2.250 0.3248 0.01869 0.01143 -0.0381 0.9016 1.0000
2.500 0.3531 0.01903 0.01187 -0.0388 0.8920 1.0000
2.750 0.4023 0.01918 0.01224 -0.0429 0.8858 1.0000
3.000 0.4315 0.01943 0.01264 -0.0435 0.8744 1.0000
3.250 0.5291 0.01584 0.00946 -0.0480 0.8264 1.0000
3.500 0.5552 0.01395 0.00762 -0.0423 0.7703 1.0000
3.750 0.5709 0.01309 0.00671 -0.0368 0.6915 1.0000
4.000 0.5560 0.01567 0.00644 -0.0276 0.1670 1.0000
4.250 0.5690 0.01753 0.00773 -0.0253 0.1038 1.0000
4.500 0.5871 0.01878 0.00894 -0.0236 0.0897 1.0000
4.750 0.6063 0.02019 0.01021 -0.0222 0.0785 1.0000
5.000 0.6309 0.02149 0.01158 -0.0213 0.0739 1.0000
5.250 0.6582 0.02309 0.01321 -0.0208 0.0705 1.0000
5.500 0.6870 0.02500 0.01516 -0.0206 0.0682 1.0000
5.750 0.7151 0.02772 0.01791 -0.0206 0.0645 1.0000
6.000 0.7420 0.02988 0.02042 -0.0199 0.0637 1.0000
6.250 0.7682 0.03324 0.02409 -0.0193 0.0647 1.0000
6.500 0.7935 0.03538 0.02708 -0.0171 0.0710 1.0000
6.750 0.8180 0.03941 0.03155 -0.0157 0.0807 1.0000
8.500 0.8495 0.07493 0.07044 -0.0089 0.1560 1.0000
9.250 0.7142 0.08378 0.07967 -0.0079 0.1587 1.0000
9.500 0.6759 0.09173 0.08757 -0.0144 0.1580 1.0000
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Polar data table (+)
Polar graphs
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