NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 200,000 Max Cl/Cd: 53.3 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66209-il-200000.txt Download as CSV file: xf-naca66209-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4151 0.11308 0.10960 -0.0288 1.0000 0.0358
-11.000 -0.4186 0.10928 0.10583 -0.0315 1.0000 0.0363
-10.750 -0.4225 0.10532 0.10189 -0.0343 1.0000 0.0366
-10.500 -0.4241 0.10111 0.09770 -0.0364 1.0000 0.0366
-10.250 -0.4275 0.09665 0.09326 -0.0390 1.0000 0.0367
-10.000 -0.4304 0.08961 0.08626 -0.0383 1.0000 0.0380
-9.750 -0.4239 0.08621 0.08287 -0.0373 1.0000 0.0391
-9.500 -0.4231 0.08234 0.07901 -0.0378 1.0000 0.0399
-9.250 -0.4252 0.07816 0.07486 -0.0389 1.0000 0.0408
-9.000 -0.4299 0.07373 0.07046 -0.0405 1.0000 0.0415
-8.750 -0.4381 0.06889 0.06566 -0.0427 1.0000 0.0421
-8.500 -0.4531 0.06367 0.06048 -0.0461 1.0000 0.0418
-8.250 -0.4755 0.05964 0.05648 -0.0468 1.0000 0.0416
-8.000 -0.5059 0.05785 0.05473 -0.0426 1.0000 0.0409
-7.750 -0.5969 0.06517 0.06160 -0.0385 1.0000 0.0384
-7.500 -0.6043 0.06306 0.05949 -0.0351 1.0000 0.0390
-7.250 -0.6119 0.06092 0.05731 -0.0318 1.0000 0.0396
-7.000 -0.6172 0.05864 0.05499 -0.0288 1.0000 0.0405
-6.750 -0.6202 0.05622 0.05247 -0.0262 1.0000 0.0416
-6.500 -0.6183 0.05346 0.04957 -0.0243 0.9996 0.0432
-6.250 -0.5873 0.05177 0.04711 -0.0266 0.9949 0.0493
-6.000 -0.5741 0.04457 0.03972 -0.0282 0.9912 0.0514
-5.750 -0.5518 0.04126 0.03641 -0.0296 0.9879 0.0543
-5.500 -0.5242 0.03903 0.03344 -0.0307 0.9841 0.0641
-5.250 -0.5003 0.03534 0.02990 -0.0321 0.9820 0.0688
-5.000 -0.4797 0.03315 0.02737 -0.0321 0.9777 0.0803
-4.750 -0.4549 0.03115 0.02527 -0.0330 0.9744 0.0967
-4.250 -0.3810 0.02335 0.01594 -0.0316 0.9708 0.0452
-4.000 -0.3468 0.02129 0.01355 -0.0324 0.9694 0.0441
-3.750 -0.3243 0.02030 0.01238 -0.0312 0.9654 0.0463
-3.500 -0.2960 0.01901 0.01092 -0.0311 0.9627 0.0462
-3.250 -0.2660 0.01795 0.00977 -0.0315 0.9604 0.0476
-3.000 -0.2338 0.01725 0.00900 -0.0324 0.9582 0.0497
-2.750 -0.2027 0.01611 0.00796 -0.0336 0.9564 0.0573
-2.500 -0.1811 0.01568 0.00748 -0.0326 0.9523 0.0621
-2.250 -0.1568 0.01515 0.00691 -0.0323 0.9487 0.0751
-2.000 -0.1417 0.01244 0.00642 -0.0315 0.9458 0.5724
-1.750 -0.1283 0.01259 0.00738 -0.0262 0.9428 0.8332
-1.500 -0.1260 0.01312 0.00799 -0.0194 0.9373 0.8779
-1.250 -0.1175 0.01358 0.00845 -0.0136 0.9326 0.9132
-1.000 -0.0893 0.01395 0.00874 -0.0123 0.9305 0.9382
-0.750 -0.0071 0.01460 0.00927 -0.0221 0.9346 0.9605
-0.500 0.0399 0.01466 0.00925 -0.0265 0.9336 0.9642
-0.250 0.0805 0.01468 0.00920 -0.0297 0.9316 0.9679
0.000 0.1215 0.01468 0.00917 -0.0329 0.9298 0.9705
0.250 0.1679 0.01465 0.00912 -0.0372 0.9286 0.9715
0.500 0.1995 0.01468 0.00916 -0.0387 0.9238 0.9750
0.750 0.2359 0.01468 0.00918 -0.0411 0.9203 0.9777
1.000 0.2778 0.01464 0.00918 -0.0444 0.9179 0.9796
1.250 0.3224 0.01456 0.00917 -0.0482 0.9159 0.9808
1.500 0.3561 0.01456 0.00923 -0.0499 0.9112 0.9837
1.750 0.4004 0.01418 0.00895 -0.0530 0.9041 0.9843
2.000 0.4482 0.01313 0.00801 -0.0553 0.8894 0.9834
2.250 0.4844 0.01185 0.00677 -0.0545 0.8640 0.9844
2.500 0.5146 0.01079 0.00570 -0.0528 0.8316 0.9869
2.750 0.5405 0.01014 0.00503 -0.0511 0.7825 0.9908
3.000 0.5484 0.01083 0.00424 -0.0456 0.4496 0.9959
3.250 0.5501 0.01378 0.00528 -0.0424 0.0758 1.0000
3.500 0.5635 0.01433 0.00582 -0.0400 0.0610 1.0000
3.750 0.5734 0.01510 0.00659 -0.0369 0.0546 1.0000
4.000 0.5850 0.01565 0.00722 -0.0340 0.0512 1.0000
4.250 0.5952 0.01631 0.00790 -0.0309 0.0482 1.0000
4.500 0.6051 0.01704 0.00860 -0.0278 0.0448 1.0000
4.750 0.6175 0.01854 0.01007 -0.0252 0.0421 1.0000
5.000 0.6349 0.01944 0.01108 -0.0231 0.0410 1.0000
5.250 0.6563 0.02074 0.01248 -0.0218 0.0404 1.0000
5.500 0.6811 0.02248 0.01438 -0.0209 0.0403 1.0000
5.750 0.7068 0.02481 0.01692 -0.0202 0.0409 1.0000
6.000 0.7299 0.02640 0.01879 -0.0191 0.0396 1.0000
6.250 0.7553 0.03068 0.02324 -0.0187 0.0428 1.0000
7.500 0.8383 0.04685 0.04177 -0.0075 0.0588 1.0000
7.750 0.8555 0.05248 0.04714 -0.0084 0.0557 1.0000
8.000 0.8479 0.05377 0.04924 -0.0036 0.0508 1.0000
8.250 0.8521 0.05687 0.05258 -0.0018 0.0476 1.0000
8.500 0.8569 0.05997 0.05580 -0.0005 0.0456 1.0000
8.750 0.8642 0.06347 0.05931 0.0002 0.0441 1.0000
9.000 0.8644 0.07277 0.06851 -0.0007 0.0425 1.0000
9.250 0.7674 0.06244 0.05903 0.0096 0.0450 1.0000
9.500 0.7502 0.06643 0.06310 0.0108 0.0447 1.0000
9.750 0.7135 0.07211 0.06894 0.0100 0.0456 1.0000
10.000 0.6747 0.08069 0.07764 0.0050 0.0472 1.0000
10.250 0.6508 0.08996 0.08690 -0.0016 0.0481 1.0000
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Polar data table (+)
Polar graphs
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