NACA 66 (p51htip-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66 (p51htip-il) Reynolds number: 200,000 Max Cl/Cd: 52.55 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51htip-il-200000.txt Download as CSV file: xf-p51htip-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4689 0.09313 0.08972 -0.0499 1.0000 0.0522
-10.250 -0.4747 0.08826 0.08490 -0.0533 1.0000 0.0534
-10.000 -0.4919 0.08353 0.08026 -0.0561 1.0000 0.0542
-9.750 -0.5232 0.08143 0.07824 -0.0536 0.9991 0.0534
-9.500 -0.5306 0.07416 0.07086 -0.0625 0.9919 0.0540
-9.250 -0.5465 0.06836 0.06478 -0.0691 0.9830 0.0559
-9.000 -0.4645 0.04832 0.04482 -0.0792 0.9731 0.0610
-8.750 -0.4665 0.04503 0.04145 -0.0788 0.9660 0.0625
-8.500 -0.4657 0.04125 0.03749 -0.0791 0.9610 0.0651
-8.250 -0.4858 0.04073 0.03637 -0.0747 0.9502 0.0704
-8.000 -0.4856 0.03401 0.02954 -0.0746 0.9469 0.0724
-7.750 -0.4717 0.03103 0.02662 -0.0742 0.9431 0.0745
-7.500 -0.4634 0.02883 0.02431 -0.0726 0.9376 0.0782
-7.250 -0.4640 0.02593 0.02097 -0.0698 0.9327 0.0868
-7.000 -0.4496 0.02372 0.01880 -0.0690 0.9293 0.0903
-6.750 -0.4490 0.02212 0.01685 -0.0656 0.9234 0.1009
-6.500 -0.4303 0.02023 0.01501 -0.0652 0.9209 0.1082
-6.250 -0.4335 0.02823 0.02072 -0.0594 0.9226 0.0465
-6.000 -0.4076 0.02733 0.01957 -0.0588 0.9202 0.0456
-5.750 -0.3801 0.02569 0.01771 -0.0587 0.9184 0.0454
-5.500 -0.3497 0.02282 0.01473 -0.0596 0.9173 0.0481
-5.250 -0.3323 0.02202 0.01388 -0.0580 0.9130 0.0495
-5.000 -0.3084 0.02113 0.01292 -0.0574 0.9100 0.0508
-4.750 -0.2834 0.02033 0.01208 -0.0569 0.9078 0.0530
-4.500 -0.2583 0.01984 0.01152 -0.0566 0.9058 0.0565
-4.250 -0.2359 0.01895 0.01064 -0.0558 0.9040 0.0596
-4.000 -0.2203 0.01852 0.01024 -0.0539 0.9013 0.0630
-3.750 -0.2122 0.01845 0.01015 -0.0506 0.8965 0.0670
-3.500 -0.1966 0.01815 0.00983 -0.0486 0.8936 0.0738
-3.250 -0.1772 0.01783 0.00950 -0.0473 0.8914 0.0862
-3.000 -0.1709 0.01625 0.00901 -0.0442 0.8891 0.3072
-2.750 -0.1949 0.01525 0.00941 -0.0350 0.8833 0.6008
-2.500 -0.1905 0.01566 0.01033 -0.0292 0.8798 0.7698
-2.250 -0.1720 0.01618 0.01083 -0.0264 0.8774 0.8111
-2.000 -0.1516 0.01683 0.01147 -0.0236 0.8757 0.8407
-1.750 -0.1287 0.01785 0.01252 -0.0201 0.8744 0.8724
-1.500 -0.0777 0.01918 0.01381 -0.0216 0.8745 0.8978
-1.250 -0.0062 0.01980 0.01431 -0.0293 0.8752 0.9069
-1.000 -0.0060 0.01999 0.01447 -0.0245 0.8712 0.9167
-0.750 0.0302 0.02024 0.01467 -0.0268 0.8686 0.9197
-0.500 0.0633 0.02040 0.01478 -0.0285 0.8661 0.9234
-0.250 0.0708 0.02043 0.01478 -0.0249 0.8623 0.9312
0.000 0.1173 0.02045 0.01477 -0.0291 0.8612 0.9323
0.250 0.1619 0.02044 0.01473 -0.0329 0.8602 0.9335
0.500 0.2050 0.02040 0.01468 -0.0362 0.8591 0.9349
0.750 0.1805 0.02092 0.01522 -0.0273 0.8495 0.9457
1.000 0.2226 0.02089 0.01520 -0.0306 0.8476 0.9467
1.250 0.2653 0.02082 0.01515 -0.0338 0.8459 0.9476
1.500 0.3086 0.02071 0.01506 -0.0370 0.8445 0.9486
1.750 0.3107 0.02117 0.01556 -0.0333 0.8358 0.9553
2.000 0.3380 0.02105 0.01549 -0.0333 0.8322 0.9589
2.250 0.3837 0.02079 0.01528 -0.0367 0.8303 0.9594
2.500 0.4121 0.02097 0.01554 -0.0377 0.8235 0.9621
2.750 0.4503 0.02071 0.01538 -0.0397 0.8187 0.9635
3.000 0.5121 0.01886 0.01359 -0.0434 0.8141 0.9612
3.250 0.5522 0.01692 0.01171 -0.0431 0.7950 0.9618
3.500 0.5936 0.01451 0.00923 -0.0422 0.7707 0.9624
3.750 0.6234 0.01353 0.00831 -0.0414 0.7458 0.9655
4.000 0.6485 0.01280 0.00762 -0.0400 0.7139 0.9696
4.250 0.6605 0.01257 0.00650 -0.0356 0.5047 0.9742
4.500 0.6427 0.01570 0.00766 -0.0293 0.1507 0.9829
4.750 0.6595 0.01723 0.00865 -0.0285 0.0723 0.9876
5.000 0.6845 0.01807 0.00948 -0.0289 0.0612 0.9921
5.250 0.7110 0.01881 0.01030 -0.0295 0.0557 0.9960
5.500 0.7379 0.01971 0.01120 -0.0302 0.0517 0.9997
5.750 0.7422 0.02047 0.01195 -0.0264 0.0499 1.0000
6.000 0.7483 0.02149 0.01296 -0.0229 0.0480 1.0000
6.250 0.7547 0.02188 0.01341 -0.0193 0.0464 1.0000
6.500 0.7640 0.02248 0.01406 -0.0161 0.0447 1.0000
6.750 0.7805 0.02337 0.01502 -0.0142 0.0435 1.0000
7.000 0.8036 0.02455 0.01627 -0.0133 0.0425 1.0000
7.250 0.8292 0.02600 0.01781 -0.0129 0.0417 1.0000
7.500 0.8497 0.02737 0.01929 -0.0116 0.0408 1.0000
7.750 0.8684 0.02892 0.02088 -0.0104 0.0392 1.0000
8.000 0.8899 0.03107 0.02323 -0.0094 0.0389 1.0000
8.250 0.9074 0.03306 0.02554 -0.0072 0.0398 1.0000
8.500 0.9205 0.03807 0.03128 -0.0040 0.0457 1.0000
13.500 0.5963 0.12709 0.12384 0.0079 0.0603 1.0000
13.750 0.5776 0.13218 0.12892 0.0033 0.0600 1.0000
14.000 0.5527 0.13736 0.13407 -0.0030 0.0587 1.0000
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Polar data table (+)
Polar graphs
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