NACA 0010 (naca0010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.15 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0010-il-1000000.txt Download as CSV file: xf-naca0010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
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
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0039 0.15161 0.14975 0.0348 1.0000 0.0085
-17.750 -1.0775 0.13031 0.12822 0.0233 1.0000 0.0082
-17.500 -1.1221 0.11680 0.11455 0.0161 1.0000 0.0080
-17.250 -1.1624 0.10480 0.10239 0.0099 1.0000 0.0079
-17.000 -1.1984 0.09402 0.09147 0.0042 1.0000 0.0077
-16.750 -1.2283 0.08447 0.08177 -0.0008 1.0000 0.0076
-16.500 -1.2553 0.07551 0.07267 -0.0058 1.0000 0.0076
-16.250 -1.2801 0.06692 0.06393 -0.0109 1.0000 0.0075
-16.000 -1.3026 0.05885 0.05569 -0.0160 1.0000 0.0075
-15.750 -1.3211 0.05178 0.04845 -0.0205 1.0000 0.0075
-15.500 -1.3399 0.04522 0.04170 -0.0245 1.0000 0.0076
-15.250 -1.3531 0.04023 0.03653 -0.0269 1.0000 0.0077
-15.000 -1.3634 0.03627 0.03241 -0.0278 1.0000 0.0078
-14.750 -1.3685 0.03339 0.02938 -0.0274 1.0000 0.0079
-14.500 -1.3699 0.03118 0.02706 -0.0263 1.0000 0.0081
-14.250 -1.3672 0.02949 0.02527 -0.0248 1.0000 0.0083
-14.000 -1.3617 0.02814 0.02382 -0.0229 1.0000 0.0085
-13.750 -1.3544 0.02700 0.02259 -0.0209 1.0000 0.0087
-13.500 -1.3446 0.02599 0.02149 -0.0189 1.0000 0.0090
-13.250 -1.3310 0.02500 0.02041 -0.0175 1.0000 0.0092
-13.000 -1.3156 0.02409 0.01940 -0.0163 1.0000 0.0095
-12.750 -1.2988 0.02324 0.01844 -0.0151 1.0000 0.0098
-12.500 -1.2804 0.02249 0.01760 -0.0141 1.0000 0.0100
-12.250 -1.2695 0.02091 0.01586 -0.0123 1.0000 0.0106
-12.000 -1.2517 0.01997 0.01486 -0.0112 1.0000 0.0112
-11.750 -1.2312 0.01929 0.01413 -0.0103 1.0000 0.0117
-11.500 -1.2099 0.01869 0.01347 -0.0096 1.0000 0.0123
-11.250 -1.1880 0.01811 0.01282 -0.0089 1.0000 0.0129
-11.000 -1.1652 0.01763 0.01226 -0.0083 1.0000 0.0133
-10.750 -1.1457 0.01670 0.01127 -0.0072 1.0000 0.0146
-10.500 -1.1220 0.01629 0.01087 -0.0068 1.0000 0.0157
-10.250 -1.0975 0.01596 0.01052 -0.0063 1.0000 0.0168
-10.000 -1.0727 0.01568 0.01020 -0.0059 1.0000 0.0176
-9.750 -1.0509 0.01498 0.00946 -0.0051 1.0000 0.0192
-9.500 -1.0259 0.01471 0.00920 -0.0047 1.0000 0.0206
-9.250 -1.0006 0.01448 0.00896 -0.0044 1.0000 0.0219
-9.000 -0.9748 0.01434 0.00879 -0.0041 1.0000 0.0229
-8.750 -0.9515 0.01384 0.00824 -0.0034 1.0000 0.0242
-8.500 -0.9284 0.01335 0.00775 -0.0027 1.0000 0.0260
-8.250 -0.9039 0.01307 0.00746 -0.0022 1.0000 0.0272
-8.000 -0.8794 0.01281 0.00717 -0.0016 1.0000 0.0285
-7.750 -0.8547 0.01261 0.00695 -0.0010 1.0000 0.0295
-7.500 -0.8300 0.01245 0.00678 -0.0004 1.0000 0.0301
-7.250 -0.8094 0.01176 0.00600 0.0009 1.0000 0.0318
-7.000 -0.7868 0.01134 0.00557 0.0018 1.0000 0.0335
-6.750 -0.7635 0.01105 0.00527 0.0027 1.0000 0.0349
-6.500 -0.7402 0.01079 0.00499 0.0036 1.0000 0.0362
-6.250 -0.7170 0.01054 0.00472 0.0045 1.0000 0.0373
-6.000 -0.6937 0.01033 0.00448 0.0054 1.0000 0.0381
-5.750 -0.6706 0.01010 0.00422 0.0063 1.0000 0.0388
-5.500 -0.6483 0.00974 0.00383 0.0074 1.0000 0.0411
-5.250 -0.6255 0.00947 0.00357 0.0084 1.0000 0.0438
-5.000 -0.5967 0.00923 0.00333 0.0081 0.9993 0.0465
-4.750 -0.5618 0.00893 0.00306 0.0065 0.9975 0.0536
-4.500 -0.5272 0.00853 0.00280 0.0049 0.9957 0.0772
-4.250 -0.4920 0.00814 0.00257 0.0031 0.9941 0.1094
-4.000 -0.4588 0.00779 0.00237 0.0018 0.9911 0.1424
-3.750 -0.4244 0.00744 0.00219 0.0002 0.9883 0.1787
-3.500 -0.3888 0.00711 0.00202 -0.0017 0.9861 0.2177
-3.250 -0.3541 0.00679 0.00187 -0.0033 0.9832 0.2589
-3.000 -0.3227 0.00650 0.00173 -0.0041 0.9774 0.2987
-2.750 -0.2908 0.00622 0.00161 -0.0050 0.9716 0.3397
-2.500 -0.2620 0.00596 0.00150 -0.0052 0.9626 0.3825
-2.250 -0.2347 0.00572 0.00141 -0.0050 0.9515 0.4241
-2.000 -0.2080 0.00552 0.00132 -0.0046 0.9390 0.4619
-1.750 -0.1818 0.00534 0.00124 -0.0041 0.9244 0.5007
-1.500 -0.1561 0.00515 0.00117 -0.0035 0.9075 0.5463
-1.250 -0.1303 0.00500 0.00111 -0.0029 0.8884 0.5859
-1.000 -0.1044 0.00489 0.00106 -0.0023 0.8671 0.6249
-0.750 -0.0786 0.00478 0.00102 -0.0016 0.8429 0.6658
-0.500 -0.0524 0.00472 0.00100 -0.0011 0.8166 0.6989
-0.250 -0.0262 0.00470 0.00098 -0.0005 0.7889 0.7294
0.000 0.0000 0.00469 0.00097 0.0000 0.7590 0.7592
0.250 0.0262 0.00470 0.00098 0.0005 0.7291 0.7887
0.500 0.0525 0.00472 0.00100 0.0011 0.6986 0.8166
0.750 0.0786 0.00478 0.00102 0.0016 0.6654 0.8428
1.000 0.1044 0.00489 0.00106 0.0023 0.6248 0.8669
1.250 0.1304 0.00500 0.00111 0.0029 0.5859 0.8882
1.500 0.1562 0.00514 0.00117 0.0035 0.5480 0.9074
1.750 0.1818 0.00534 0.00124 0.0041 0.5004 0.9245
2.000 0.2080 0.00552 0.00132 0.0046 0.4619 0.9390
2.250 0.2347 0.00573 0.00141 0.0050 0.4236 0.9515
2.500 0.2620 0.00596 0.00150 0.0052 0.3823 0.9626
2.750 0.2908 0.00622 0.00161 0.0050 0.3395 0.9716
3.000 0.3227 0.00650 0.00173 0.0041 0.2987 0.9774
3.250 0.3542 0.00679 0.00187 0.0033 0.2590 0.9832
3.500 0.3888 0.00711 0.00202 0.0017 0.2176 0.9861
3.750 0.4244 0.00744 0.00219 -0.0002 0.1787 0.9883
4.000 0.4588 0.00779 0.00237 -0.0018 0.1425 0.9911
4.250 0.4920 0.00814 0.00257 -0.0031 0.1094 0.9941
4.500 0.5272 0.00853 0.00280 -0.0049 0.0773 0.9957
4.750 0.5619 0.00893 0.00306 -0.0065 0.0536 0.9975
5.000 0.5967 0.00923 0.00333 -0.0081 0.0465 0.9993
5.250 0.6255 0.00947 0.00357 -0.0084 0.0438 1.0000
5.500 0.6483 0.00974 0.00383 -0.0074 0.0412 1.0000
5.750 0.6706 0.01010 0.00422 -0.0063 0.0388 1.0000
6.000 0.6936 0.01033 0.00448 -0.0054 0.0381 1.0000
6.250 0.7169 0.01054 0.00472 -0.0045 0.0373 1.0000
6.500 0.7402 0.01078 0.00499 -0.0036 0.0361 1.0000
6.750 0.7635 0.01105 0.00527 -0.0027 0.0349 1.0000
7.000 0.7868 0.01134 0.00557 -0.0018 0.0335 1.0000
7.250 0.8093 0.01176 0.00600 -0.0009 0.0318 1.0000
7.500 0.8300 0.01245 0.00677 0.0004 0.0301 1.0000
7.750 0.8548 0.01260 0.00694 0.0010 0.0295 1.0000
8.000 0.8794 0.01281 0.00717 0.0016 0.0285 1.0000
8.250 0.9039 0.01307 0.00746 0.0022 0.0272 1.0000
8.500 0.9285 0.01335 0.00774 0.0027 0.0260 1.0000
8.750 0.9516 0.01384 0.00824 0.0034 0.0242 1.0000
9.000 0.9747 0.01434 0.00880 0.0041 0.0229 1.0000
9.250 1.0007 0.01448 0.00896 0.0044 0.0219 1.0000
9.500 1.0260 0.01471 0.00920 0.0047 0.0206 1.0000
9.750 1.0509 0.01498 0.00946 0.0051 0.0192 1.0000
10.000 1.0727 0.01568 0.01020 0.0059 0.0176 1.0000
10.250 1.0975 0.01596 0.01052 0.0063 0.0168 1.0000
10.500 1.1220 0.01628 0.01087 0.0068 0.0157 1.0000
10.750 1.1457 0.01669 0.01127 0.0072 0.0146 1.0000
11.000 1.1652 0.01762 0.01226 0.0083 0.0133 1.0000
11.250 1.1880 0.01811 0.01282 0.0089 0.0129 1.0000
11.500 1.2099 0.01868 0.01347 0.0096 0.0123 1.0000
11.750 1.2313 0.01929 0.01413 0.0103 0.0117 1.0000
12.000 1.2518 0.01997 0.01487 0.0111 0.0112 1.0000
12.250 1.2696 0.02091 0.01587 0.0122 0.0106 1.0000
12.500 1.2807 0.02249 0.01760 0.0141 0.0100 1.0000
12.750 1.2991 0.02324 0.01844 0.0151 0.0098 1.0000
13.000 1.3159 0.02409 0.01940 0.0162 0.0095 1.0000
13.250 1.3311 0.02502 0.02043 0.0175 0.0092 1.0000
13.500 1.3448 0.02599 0.02150 0.0189 0.0090 1.0000
13.750 1.3547 0.02701 0.02260 0.0208 0.0087 1.0000
14.000 1.3622 0.02814 0.02383 0.0228 0.0085 1.0000
14.250 1.3679 0.02948 0.02525 0.0247 0.0083 1.0000
14.500 1.3705 0.03117 0.02705 0.0262 0.0081 1.0000
14.750 1.3695 0.03335 0.02935 0.0273 0.0080 1.0000
15.000 1.3640 0.03629 0.03242 0.0276 0.0078 1.0000
15.250 1.3544 0.04017 0.03647 0.0267 0.0077 1.0000
15.500 1.3403 0.04530 0.04178 0.0243 0.0076 1.0000
15.750 1.3221 0.05179 0.04846 0.0203 0.0075 1.0000
16.000 1.3030 0.05898 0.05583 0.0157 0.0075 1.0000
16.250 1.2811 0.06697 0.06399 0.0106 0.0075 1.0000
16.500 1.2569 0.07548 0.07265 0.0056 0.0076 1.0000
16.750 1.2294 0.08456 0.08186 0.0005 0.0076 1.0000
17.000 1.1991 0.09421 0.09165 -0.0046 0.0077 1.0000
17.250 1.1635 0.10491 0.10250 -0.0102 0.0079 1.0000
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