NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.45 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66209-il-1000000.txt Download as CSV file: xf-naca66209-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5195 0.08378 0.08217 -0.0360 1.0000 0.0090
-9.250 -0.5243 0.07875 0.07718 -0.0394 1.0000 0.0091
-9.000 -0.5378 0.07205 0.07050 -0.0458 1.0000 0.0087
-8.750 -0.5532 0.06818 0.06662 -0.0473 1.0000 0.0092
-8.500 -0.5709 0.06404 0.06244 -0.0470 0.9988 0.0088
-8.250 -0.5606 0.05848 0.05676 -0.0519 0.9882 0.0095
-8.000 -0.5456 0.05223 0.05033 -0.0568 0.9830 0.0099
-7.750 -0.5193 0.04715 0.04500 -0.0590 0.9760 0.0113
-6.750 -0.4838 0.01378 0.01050 -0.0506 0.9172 0.0101
-6.500 -0.4759 0.00892 0.00506 -0.0480 0.9114 0.0096
-6.250 -0.4575 0.00679 0.00256 -0.0468 0.9063 0.0103
-6.000 -0.4364 0.00534 0.00077 -0.0457 0.9019 0.0110
-5.750 -0.4132 0.01582 0.01087 -0.0488 0.9083 0.0115
-5.500 -0.3929 0.01268 0.00740 -0.0475 0.9034 0.0122
-5.250 -0.3682 0.01200 0.00665 -0.0471 0.8991 0.0129
-5.000 -0.3425 0.01156 0.00617 -0.0469 0.8945 0.0137
-4.750 -0.3163 0.01133 0.00590 -0.0468 0.8903 0.0151
-4.500 -0.2910 0.01078 0.00527 -0.0464 0.8864 0.0158
-4.250 -0.2651 0.01036 0.00481 -0.0461 0.8823 0.0165
-4.000 -0.2388 0.01008 0.00448 -0.0460 0.8781 0.0170
-3.750 -0.2168 0.00901 0.00328 -0.0450 0.8740 0.0184
-3.500 -0.1908 0.00867 0.00293 -0.0448 0.8702 0.0206
-3.250 -0.1641 0.00842 0.00266 -0.0448 0.8664 0.0227
-3.000 -0.1373 0.00822 0.00242 -0.0447 0.8629 0.0245
-2.750 -0.1106 0.00796 0.00209 -0.0446 0.8596 0.0269
-2.500 -0.0839 0.00770 0.00181 -0.0445 0.8564 0.0333
-2.250 -0.0565 0.00755 0.00165 -0.0445 0.8529 0.0384
-2.000 -0.0301 0.00721 0.00146 -0.0445 0.8494 0.0852
-1.750 -0.0092 0.00594 0.00119 -0.0441 0.8460 0.3967
-1.500 0.0114 0.00483 0.00106 -0.0433 0.8427 0.6918
-1.250 0.0382 0.00472 0.00110 -0.0431 0.8396 0.7436
-1.000 0.0655 0.00470 0.00114 -0.0430 0.8366 0.7729
-0.750 0.0930 0.00472 0.00117 -0.0429 0.8337 0.7916
-0.500 0.1206 0.00476 0.00122 -0.0428 0.8307 0.8057
-0.250 0.1483 0.00477 0.00126 -0.0428 0.8271 0.8148
0.000 0.1759 0.00477 0.00128 -0.0428 0.8223 0.8231
0.250 0.2033 0.00483 0.00131 -0.0426 0.8176 0.8331
0.500 0.2309 0.00481 0.00133 -0.0426 0.8122 0.8373
0.750 0.2583 0.00481 0.00128 -0.0425 0.8021 0.8406
1.000 0.2855 0.00479 0.00124 -0.0423 0.7891 0.8439
1.250 0.3133 0.00478 0.00124 -0.0424 0.7786 0.8470
1.500 0.3404 0.00478 0.00123 -0.0422 0.7643 0.8499
1.750 0.3672 0.00481 0.00123 -0.0420 0.7453 0.8531
2.000 0.3934 0.00489 0.00124 -0.0417 0.7132 0.8568
2.250 0.4143 0.00536 0.00129 -0.0403 0.5962 0.8608
2.500 0.4267 0.00670 0.00170 -0.0378 0.3602 0.8650
2.750 0.4426 0.00790 0.00211 -0.0362 0.1538 0.8696
3.000 0.4636 0.00869 0.00244 -0.0352 0.0417 0.8740
3.250 0.4886 0.00896 0.00270 -0.0348 0.0319 0.8778
3.500 0.5145 0.00914 0.00293 -0.0345 0.0282 0.8820
3.750 0.5399 0.00942 0.00322 -0.0342 0.0235 0.8866
4.000 0.5633 0.00990 0.00378 -0.0333 0.0202 0.8911
4.250 0.5882 0.01014 0.00407 -0.0329 0.0191 0.8956
4.500 0.6130 0.01047 0.00443 -0.0324 0.0179 0.9006
4.750 0.6370 0.01082 0.00484 -0.0318 0.0167 0.9053
5.000 0.6605 0.01118 0.00523 -0.0311 0.0153 0.9104
5.250 0.6799 0.01215 0.00629 -0.0296 0.0141 0.9166
5.500 0.6976 0.01341 0.00768 -0.0278 0.0136 0.9228
5.750 0.7214 0.01388 0.00821 -0.0271 0.0133 0.9290
6.000 0.7438 0.01445 0.00887 -0.0261 0.0130 0.9351
6.250 0.7665 0.01520 0.00970 -0.0253 0.0126 0.9421
6.500 0.7885 0.01569 0.01029 -0.0242 0.0117 0.9497
6.750 0.8105 0.01612 0.01079 -0.0232 0.0110 0.9590
7.500 0.8900 0.01915 0.01415 -0.0239 0.0095 1.0000
8.000 0.9255 0.02568 0.02145 -0.0212 0.0086 1.0000
8.250 0.9449 0.02764 0.02366 -0.0200 0.0080 1.0000
8.500 0.9533 0.03237 0.02884 -0.0172 0.0074 1.0000
8.750 0.9417 0.04101 0.03811 -0.0119 0.0076 1.0000
9.000 0.9332 0.04710 0.04456 -0.0080 0.0078 1.0000
9.250 0.9229 0.05230 0.05002 -0.0047 0.0081 1.0000
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Polar data table (+)
Polar graphs
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