NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 500,000 Max Cl/Cd: 42.87 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001066-il-500000.txt Download as CSV file: xf-naca001066-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6438 0.14346 0.14104 -0.0139 1.0000 0.0259
-13.250 -0.9148 0.06624 0.06364 -0.0512 1.0000 0.0162
-13.000 -0.9452 0.06056 0.05778 -0.0515 1.0000 0.0161
-12.750 -0.9734 0.05646 0.05351 -0.0489 1.0000 0.0160
-12.500 -1.0033 0.05289 0.04975 -0.0443 1.0000 0.0160
-12.250 -1.0333 0.04976 0.04643 -0.0383 1.0000 0.0160
-12.000 -1.0654 0.04685 0.04331 -0.0308 1.0000 0.0161
-11.750 -1.0959 0.04446 0.04070 -0.0224 1.0000 0.0161
-11.500 -1.1254 0.04250 0.03855 -0.0132 1.0000 0.0162
-11.250 -1.1426 0.04036 0.03623 -0.0062 1.0000 0.0164
-11.000 -1.1419 0.03948 0.03530 -0.0019 1.0000 0.0167
-10.750 -1.1335 0.03931 0.03512 0.0012 1.0000 0.0171
-10.500 -1.1263 0.03886 0.03462 0.0045 1.0000 0.0174
-10.250 -1.1188 0.03826 0.03396 0.0078 1.0000 0.0179
-10.000 -1.1167 0.03679 0.03231 0.0120 1.0000 0.0184
-9.750 -1.1162 0.03480 0.03004 0.0166 1.0000 0.0190
-9.500 -1.1140 0.03273 0.02764 0.0212 1.0000 0.0196
-9.250 -1.1067 0.03127 0.02588 0.0249 1.0000 0.0201
-9.000 -1.1006 0.02923 0.02349 0.0288 1.0000 0.0207
-8.750 -1.0811 0.02744 0.02156 0.0296 0.9989 0.0216
-8.500 -1.0598 0.02700 0.02108 0.0304 0.9980 0.0224
-8.250 -1.0386 0.02656 0.02056 0.0313 0.9971 0.0234
-8.000 -1.0176 0.02588 0.01974 0.0324 0.9964 0.0245
-7.750 -0.9943 0.02529 0.01895 0.0331 0.9955 0.0256
-7.500 -0.9711 0.02348 0.01686 0.0337 0.9948 0.0268
-7.250 -0.9452 0.02255 0.01590 0.0336 0.9934 0.0281
-7.000 -0.9231 0.02211 0.01541 0.0345 0.9921 0.0293
-6.750 -0.9009 0.02169 0.01493 0.0354 0.9912 0.0308
-6.500 -0.8780 0.02121 0.01433 0.0363 0.9904 0.0320
-6.250 -0.8546 0.02088 0.01391 0.0371 0.9896 0.0329
-6.000 -0.8314 0.01939 0.01231 0.0378 0.9892 0.0347
-5.750 -0.8080 0.01889 0.01180 0.0384 0.9885 0.0363
-5.500 -0.7822 0.01851 0.01138 0.0386 0.9875 0.0378
-5.250 -0.7552 0.01813 0.01094 0.0386 0.9866 0.0393
-5.000 -0.7288 0.01786 0.01063 0.0387 0.9859 0.0407
-4.750 -0.7026 0.01767 0.01038 0.0388 0.9853 0.0417
-4.500 -0.6787 0.01695 0.00961 0.0395 0.9848 0.0437
-4.250 -0.6526 0.01668 0.00933 0.0397 0.9843 0.0459
-4.000 -0.6326 0.01634 0.00899 0.0412 0.9826 0.0480
-3.750 -0.6121 0.01604 0.00866 0.0426 0.9812 0.0500
-3.500 -0.5884 0.01583 0.00841 0.0434 0.9796 0.0519
-3.250 -0.5657 0.01550 0.00810 0.0444 0.9786 0.0571
-3.000 -0.5419 0.01533 0.00794 0.0451 0.9777 0.0637
-2.750 -0.5186 0.01500 0.00779 0.0459 0.9769 0.0910
-2.500 -0.4950 0.01472 0.00770 0.0465 0.9761 0.1338
-2.250 -0.4695 0.01445 0.00767 0.0466 0.9751 0.1837
-2.000 -0.4436 0.01415 0.00769 0.0467 0.9742 0.2581
-1.750 -0.4202 0.01377 0.00772 0.0472 0.9735 0.3566
-1.500 -0.4044 0.01294 0.00773 0.0494 0.9727 0.5508
-1.250 -0.3734 0.01240 0.00870 0.0496 0.9735 0.9170
-1.000 -0.3385 0.01313 0.00940 0.0484 0.9733 0.9355
-0.750 -0.2957 0.01400 0.01024 0.0454 0.9736 0.9472
-0.500 -0.2020 0.01548 0.01169 0.0312 0.9751 0.9551
-0.250 -0.1393 0.01591 0.01208 0.0238 0.9700 0.9599
0.000 -0.0051 0.01630 0.01246 0.0011 0.9637 0.9634
0.250 0.1382 0.01592 0.01209 -0.0236 0.9600 0.9701
0.500 0.2021 0.01548 0.01169 -0.0313 0.9551 0.9751
0.750 0.2955 0.01400 0.01024 -0.0454 0.9473 0.9737
1.000 0.3384 0.01313 0.00940 -0.0484 0.9355 0.9733
1.250 0.3733 0.01240 0.00870 -0.0496 0.9170 0.9735
1.500 0.4044 0.01293 0.00772 -0.0494 0.5517 0.9727
1.750 0.4201 0.01376 0.00772 -0.0472 0.3569 0.9735
2.000 0.4435 0.01415 0.00769 -0.0466 0.2578 0.9742
2.250 0.4694 0.01445 0.00767 -0.0466 0.1837 0.9751
2.500 0.4949 0.01471 0.00770 -0.0465 0.1341 0.9761
2.750 0.5185 0.01500 0.00778 -0.0458 0.0910 0.9769
3.000 0.5418 0.01533 0.00794 -0.0450 0.0637 0.9777
3.250 0.5656 0.01549 0.00809 -0.0444 0.0571 0.9786
3.500 0.5883 0.01583 0.00841 -0.0434 0.0519 0.9796
3.750 0.6120 0.01604 0.00866 -0.0426 0.0500 0.9812
4.000 0.6324 0.01634 0.00899 -0.0412 0.0480 0.9826
4.250 0.6526 0.01667 0.00933 -0.0397 0.0459 0.9844
4.500 0.6786 0.01695 0.00961 -0.0395 0.0437 0.9848
4.750 0.7025 0.01766 0.01038 -0.0388 0.0417 0.9853
5.000 0.7288 0.01785 0.01061 -0.0387 0.0407 0.9859
5.250 0.7554 0.01812 0.01093 -0.0386 0.0393 0.9866
5.500 0.7823 0.01850 0.01137 -0.0386 0.0378 0.9876
5.750 0.8079 0.01889 0.01179 -0.0384 0.0363 0.9885
6.000 0.8313 0.01939 0.01230 -0.0378 0.0347 0.9892
6.250 0.8545 0.02088 0.01391 -0.0370 0.0329 0.9896
6.500 0.8779 0.02121 0.01433 -0.0363 0.0320 0.9904
6.750 0.9008 0.02168 0.01492 -0.0354 0.0308 0.9912
7.000 0.9230 0.02211 0.01541 -0.0345 0.0294 0.9921
7.250 0.9449 0.02253 0.01588 -0.0335 0.0281 0.9933
7.500 0.9707 0.02346 0.01684 -0.0336 0.0268 0.9948
7.750 0.9939 0.02528 0.01895 -0.0330 0.0256 0.9955
8.000 1.0175 0.02586 0.01972 -0.0324 0.0245 0.9964
8.250 1.0386 0.02656 0.02056 -0.0313 0.0234 0.9971
8.500 1.0597 0.02700 0.02108 -0.0304 0.0224 0.9980
8.750 1.0809 0.02745 0.02157 -0.0296 0.0216 0.9989
9.000 1.1010 0.02911 0.02336 -0.0289 0.0207 1.0000
9.250 1.1066 0.03127 0.02587 -0.0249 0.0201 1.0000
9.500 1.1140 0.03272 0.02762 -0.0212 0.0196 1.0000
9.750 1.1164 0.03476 0.02999 -0.0167 0.0190 1.0000
10.000 1.1172 0.03672 0.03222 -0.0121 0.0184 1.0000
10.250 1.1194 0.03818 0.03388 -0.0079 0.0179 1.0000
10.500 1.1270 0.03877 0.03452 -0.0046 0.0174 1.0000
10.750 1.1339 0.03927 0.03508 -0.0012 0.0171 1.0000
11.000 1.1421 0.03947 0.03529 0.0019 0.0167 1.0000
11.250 1.1427 0.04036 0.03623 0.0062 0.0164 1.0000
11.500 1.1260 0.04248 0.03853 0.0131 0.0162 1.0000
11.750 1.0959 0.04448 0.04073 0.0224 0.0161 1.0000
12.000 1.0654 0.04687 0.04332 0.0308 0.0161 1.0000
12.250 1.0335 0.04976 0.04643 0.0383 0.0160 1.0000
12.500 1.0028 0.05294 0.04981 0.0443 0.0160 1.0000
12.750 0.9729 0.05653 0.05358 0.0489 0.0160 1.0000
13.000 0.9454 0.06056 0.05778 0.0515 0.0161 1.0000
13.250 0.9146 0.06634 0.06375 0.0511 0.0162 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010-66 (naca001066-il)