NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 50,000 Max Cl/Cd: 25.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66209-il-50000-n5.txt Download as CSV file: xf-naca66209-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4214 0.09415 0.08747 -0.0353 1.0000 0.0726
-9.500 -0.4257 0.08887 0.08221 -0.0374 1.0000 0.0617
-9.000 -0.5224 0.08915 0.08220 -0.0394 1.0000 0.0620
-8.750 -0.5317 0.08438 0.07751 -0.0421 1.0000 0.0587
-8.250 -0.5577 0.07632 0.06942 -0.0437 1.0000 0.0518
-8.000 -0.5625 0.07289 0.06599 -0.0428 1.0000 0.0506
-7.750 -0.5690 0.06950 0.06255 -0.0415 1.0000 0.0495
-7.500 -0.5751 0.06622 0.05918 -0.0398 1.0000 0.0485
-7.250 -0.5802 0.06296 0.05580 -0.0378 1.0000 0.0475
-7.000 -0.5839 0.05977 0.05243 -0.0356 1.0000 0.0472
-6.750 -0.5847 0.05679 0.04924 -0.0333 1.0000 0.0469
-6.500 -0.5836 0.05385 0.04604 -0.0309 1.0000 0.0479
-6.250 -0.5798 0.05101 0.04289 -0.0287 1.0000 0.0490
-6.000 -0.5734 0.04807 0.03958 -0.0265 1.0000 0.0496
-5.750 -0.5641 0.04514 0.03626 -0.0244 1.0000 0.0495
-5.500 -0.5521 0.04226 0.03295 -0.0224 1.0000 0.0492
-5.250 -0.5374 0.03958 0.02983 -0.0206 1.0000 0.0491
-5.000 -0.5205 0.03708 0.02688 -0.0190 1.0000 0.0494
-4.750 -0.5015 0.03478 0.02413 -0.0175 1.0000 0.0499
-4.500 -0.4812 0.03301 0.02177 -0.0159 1.0000 0.0527
-4.250 -0.4605 0.03109 0.01958 -0.0148 1.0000 0.0558
-4.000 -0.4385 0.02942 0.01772 -0.0137 1.0000 0.0579
-3.750 -0.4155 0.02801 0.01612 -0.0124 1.0000 0.0599
-3.500 -0.3925 0.02686 0.01478 -0.0110 1.0000 0.0625
-3.250 -0.3704 0.02599 0.01366 -0.0095 1.0000 0.0675
-3.000 -0.3504 0.02502 0.01268 -0.0083 1.0000 0.0753
-2.750 -0.3300 0.02425 0.01164 -0.0070 1.0000 0.0814
-2.500 -0.3107 0.02340 0.01072 -0.0058 1.0000 0.0897
-2.250 -0.1257 0.02118 0.01147 -0.0255 1.0000 1.0000
-2.000 -0.1215 0.02106 0.01117 -0.0223 1.0000 1.0000
-1.750 -0.1172 0.02094 0.01088 -0.0191 1.0000 1.0000
-1.500 -0.1127 0.02082 0.01061 -0.0160 1.0000 1.0000
-1.250 -0.1081 0.02071 0.01036 -0.0128 1.0000 1.0000
-1.000 -0.1032 0.02059 0.01012 -0.0097 1.0000 1.0000
-0.750 -0.0979 0.02048 0.00986 -0.0066 1.0000 1.0000
-0.500 -0.0804 0.02049 0.00972 -0.0059 0.9971 1.0000
-0.250 -0.0546 0.02063 0.00971 -0.0067 0.9919 1.0000
0.000 -0.0286 0.02081 0.00977 -0.0074 0.9868 1.0000
0.250 -0.0038 0.02098 0.00983 -0.0079 0.9812 1.0000
0.500 0.0240 0.02125 0.01001 -0.0090 0.9762 1.0000
0.750 0.0481 0.02144 0.01015 -0.0093 0.9699 1.0000
1.000 0.0781 0.02178 0.01045 -0.0107 0.9648 1.0000
1.500 0.1324 0.02239 0.01105 -0.0123 0.9528 1.0000
1.750 0.1567 0.02267 0.01135 -0.0125 0.9457 1.0000
2.000 0.1883 0.02308 0.01182 -0.0140 0.9397 1.0000
2.250 0.2142 0.02341 0.01226 -0.0145 0.9323 1.0000
2.500 0.2473 0.02385 0.01281 -0.0162 0.9257 1.0000
2.750 0.2731 0.02420 0.01329 -0.0166 0.9170 1.0000
3.000 0.3078 0.02464 0.01392 -0.0185 0.9096 1.0000
3.250 0.3363 0.02501 0.01453 -0.0192 0.8997 1.0000
3.500 0.3659 0.02536 0.01512 -0.0200 0.8890 1.0000
3.750 0.3989 0.02569 0.01576 -0.0212 0.8775 1.0000
4.000 0.4544 0.02532 0.01595 -0.0249 0.8534 1.0000
4.250 0.5342 0.02064 0.00943 -0.0190 0.2771 1.0000
4.500 0.5337 0.02302 0.01059 -0.0152 0.1221 1.0000
4.750 0.5474 0.02441 0.01178 -0.0131 0.0960 1.0000
5.000 0.5643 0.02559 0.01300 -0.0115 0.0800 1.0000
5.250 0.5831 0.02692 0.01435 -0.0101 0.0731 1.0000
5.500 0.6085 0.02816 0.01584 -0.0093 0.0679 1.0000
5.750 0.6399 0.02983 0.01748 -0.0098 0.0601 1.0000
6.000 0.6747 0.03145 0.01943 -0.0102 0.0553 1.0000
6.250 0.7086 0.03360 0.02183 -0.0107 0.0529 1.0000
6.500 0.7382 0.03603 0.02462 -0.0106 0.0512 1.0000
6.750 0.7636 0.03866 0.02756 -0.0101 0.0498 1.0000
7.000 0.7843 0.04186 0.03097 -0.0095 0.0474 1.0000
7.250 0.8008 0.04427 0.03405 -0.0076 0.0453 1.0000
7.500 0.8152 0.04741 0.03771 -0.0058 0.0444 1.0000
7.750 0.8268 0.05076 0.04153 -0.0040 0.0443 1.0000
8.000 0.8349 0.05433 0.04553 -0.0020 0.0443 1.0000
8.250 0.8395 0.05802 0.04963 -0.0001 0.0444 1.0000
8.500 0.8411 0.06180 0.05377 0.0019 0.0447 1.0000
8.750 0.8397 0.06565 0.05792 0.0037 0.0450 1.0000
9.000 0.8355 0.06955 0.06207 0.0053 0.0454 1.0000
9.250 0.8277 0.07346 0.06619 0.0067 0.0457 1.0000
9.500 0.8169 0.07719 0.07008 0.0081 0.0459 1.0000
9.750 0.8026 0.08102 0.07403 0.0091 0.0461 1.0000
10.000 0.7896 0.08521 0.07830 0.0090 0.0464 1.0000
10.250 0.7769 0.08979 0.08295 0.0079 0.0467 1.0000
10.500 0.7681 0.09467 0.08785 0.0063 0.0471 1.0000
10.750 0.7586 0.10001 0.09322 0.0038 0.0473 1.0000
11.000 0.7526 0.10548 0.09870 0.0012 0.0475 1.0000
11.500 0.7247 0.12318 0.11633 -0.0141 0.0566 1.0000
11.750 0.7252 0.12839 0.12151 -0.0163 0.0578 1.0000
12.000 0.7276 0.13333 0.12643 -0.0182 0.0587 1.0000
12.250 0.7311 0.13824 0.13134 -0.0198 0.0594 1.0000
12.750 0.6069 0.14604 0.13979 -0.0177 0.1280 1.0000
13.000 0.5921 0.14788 0.14162 -0.0204 0.1273 1.0000
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Polar data table (+)
Polar graphs
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