NASA RC(5)-10 AIRFOIL (rc510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA RC(5)-10 AIRFOIL (rc510-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.44 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc510-il-1000000-n5.txt Download as CSV file: xf-rc510-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA RC(5)-10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6107 0.14091 0.13932 0.0327 1.0000 0.0075
-12.000 -0.6124 0.13709 0.13524 0.0322 0.8724 0.0076
-11.000 -0.9903 0.03377 0.03060 -0.0184 0.8238 0.0089
-10.750 -0.9811 0.03037 0.02686 -0.0174 0.8135 0.0089
-10.500 -0.9662 0.02815 0.02439 -0.0165 0.8049 0.0090
-10.250 -0.9487 0.02638 0.02240 -0.0157 0.7970 0.0091
-10.000 -0.9297 0.02486 0.02067 -0.0149 0.7903 0.0092
-9.750 -0.9094 0.02350 0.01912 -0.0142 0.7843 0.0093
-9.500 -0.8882 0.02228 0.01771 -0.0135 0.7783 0.0094
-9.250 -0.8662 0.02115 0.01641 -0.0128 0.7731 0.0095
-9.000 -0.8436 0.02012 0.01522 -0.0122 0.7677 0.0096
-8.750 -0.8203 0.01917 0.01410 -0.0117 0.7628 0.0097
-8.500 -0.7965 0.01828 0.01307 -0.0111 0.7586 0.0099
-8.250 -0.7721 0.01747 0.01213 -0.0107 0.7540 0.0100
-8.000 -0.7472 0.01679 0.01132 -0.0102 0.7493 0.0102
-7.750 -0.7220 0.01616 0.01057 -0.0098 0.7450 0.0105
-7.500 -0.6965 0.01553 0.00983 -0.0094 0.7406 0.0107
-7.250 -0.6709 0.01492 0.00911 -0.0090 0.7361 0.0108
-7.000 -0.6450 0.01438 0.00847 -0.0087 0.7321 0.0110
-6.750 -0.6187 0.01389 0.00788 -0.0084 0.7284 0.0111
-6.500 -0.5923 0.01344 0.00736 -0.0081 0.7241 0.0112
-6.250 -0.5657 0.01304 0.00689 -0.0078 0.7197 0.0113
-5.750 -0.5138 0.01188 0.00556 -0.0070 0.7115 0.0119
-5.500 -0.4870 0.01150 0.00514 -0.0068 0.7073 0.0121
-5.250 -0.4600 0.01117 0.00477 -0.0066 0.7033 0.0124
-5.000 -0.4329 0.01088 0.00444 -0.0063 0.6995 0.0127
-4.750 -0.4056 0.01059 0.00411 -0.0062 0.6955 0.0130
-4.500 -0.3782 0.01032 0.00381 -0.0060 0.6910 0.0134
-4.250 -0.3508 0.01008 0.00353 -0.0058 0.6867 0.0137
-4.000 -0.3233 0.00985 0.00327 -0.0056 0.6827 0.0141
-3.750 -0.2956 0.00964 0.00303 -0.0055 0.6786 0.0145
-3.500 -0.2681 0.00940 0.00277 -0.0053 0.6744 0.0153
-3.250 -0.2405 0.00920 0.00255 -0.0052 0.6705 0.0163
-3.000 -0.2126 0.00902 0.00237 -0.0051 0.6665 0.0172
-2.750 -0.1847 0.00887 0.00219 -0.0050 0.6620 0.0183
-2.500 -0.1568 0.00870 0.00203 -0.0049 0.6576 0.0203
-2.250 -0.1289 0.00856 0.00188 -0.0048 0.6525 0.0234
-2.000 -0.1010 0.00842 0.00174 -0.0048 0.6435 0.0288
-1.750 -0.0731 0.00829 0.00162 -0.0047 0.6338 0.0355
-1.250 -0.0172 0.00807 0.00143 -0.0046 0.6163 0.0552
-1.000 0.0109 0.00798 0.00135 -0.0046 0.6079 0.0650
-0.750 0.0391 0.00790 0.00129 -0.0046 0.5998 0.0760
-0.500 0.0673 0.00783 0.00124 -0.0046 0.5910 0.0886
-0.250 0.0954 0.00777 0.00119 -0.0046 0.5809 0.1022
0.000 0.1236 0.00770 0.00116 -0.0046 0.5717 0.1202
0.250 0.1517 0.00765 0.00112 -0.0046 0.5595 0.1385
0.500 0.1795 0.00759 0.00109 -0.0046 0.5439 0.1657
0.750 0.2002 0.00643 0.00099 -0.0037 0.5295 0.5410
1.000 0.2256 0.00617 0.00098 -0.0033 0.5106 0.6401
1.250 0.2511 0.00607 0.00099 -0.0028 0.4784 0.7070
1.500 0.2737 0.00603 0.00105 -0.0018 0.4192 0.7986
1.750 0.2954 0.00615 0.00126 -0.0004 0.3528 0.9069
2.000 0.3244 0.00645 0.00142 -0.0007 0.3040 0.9392
2.500 0.3944 0.00697 0.00170 -0.0040 0.2463 0.9677
2.750 0.4285 0.00716 0.00181 -0.0054 0.2309 0.9753
3.000 0.4613 0.00736 0.00193 -0.0065 0.2170 0.9815
3.250 0.4961 0.00756 0.00205 -0.0081 0.2037 0.9866
3.500 0.5317 0.00772 0.00216 -0.0099 0.1945 0.9903
3.750 0.5631 0.00787 0.00227 -0.0108 0.1867 0.9926
4.000 0.5939 0.00804 0.00239 -0.0115 0.1779 0.9943
4.250 0.6265 0.00819 0.00250 -0.0127 0.1710 0.9955
4.500 0.6587 0.00834 0.00262 -0.0138 0.1647 0.9967
4.750 0.6906 0.00850 0.00275 -0.0148 0.1585 0.9980
5.000 0.7221 0.00866 0.00289 -0.0158 0.1521 0.9991
5.250 0.7535 0.00885 0.00304 -0.0167 0.1459 1.0000
5.500 0.7787 0.00899 0.00318 -0.0162 0.1415 1.0000
5.750 0.8036 0.00917 0.00334 -0.0158 0.1360 1.0000
6.000 0.8285 0.00936 0.00350 -0.0153 0.1315 1.0000
6.250 0.8535 0.00952 0.00367 -0.0148 0.1279 1.0000
6.500 0.8782 0.00972 0.00386 -0.0143 0.1225 1.0000
6.750 0.9029 0.00993 0.00405 -0.0138 0.1178 1.0000
7.000 0.9277 0.01012 0.00425 -0.0134 0.1143 1.0000
7.250 0.9521 0.01036 0.00447 -0.0129 0.1084 1.0000
7.500 0.9766 0.01059 0.00470 -0.0124 0.1035 1.0000
7.750 1.0010 0.01083 0.00493 -0.0119 0.0988 1.0000
8.000 1.0248 0.01112 0.00520 -0.0113 0.0928 1.0000
8.250 1.0492 0.01135 0.00545 -0.0109 0.0894 1.0000
8.500 1.0729 0.01166 0.00573 -0.0103 0.0836 1.0000
8.750 1.0965 0.01196 0.00603 -0.0097 0.0783 1.0000
9.000 1.1194 0.01234 0.00637 -0.0091 0.0710 1.0000
9.250 1.1425 0.01268 0.00671 -0.0085 0.0653 1.0000
9.500 1.1647 0.01312 0.00710 -0.0079 0.0583 1.0000
9.750 1.1870 0.01355 0.00751 -0.0072 0.0516 1.0000
10.000 1.2091 0.01400 0.00795 -0.0066 0.0458 1.0000
10.250 1.2306 0.01451 0.00843 -0.0059 0.0400 1.0000
10.500 1.2526 0.01496 0.00889 -0.0052 0.0358 1.0000
10.750 1.2736 0.01551 0.00942 -0.0045 0.0312 1.0000
11.000 1.2947 0.01604 0.00995 -0.0039 0.0276 1.0000
11.250 1.3151 0.01662 0.01054 -0.0031 0.0241 1.0000
11.500 1.3348 0.01724 0.01116 -0.0023 0.0208 1.0000
11.750 1.3543 0.01785 0.01179 -0.0015 0.0180 1.0000
12.000 1.3724 0.01857 0.01252 -0.0006 0.0153 1.0000
12.250 1.3908 0.01921 0.01320 0.0002 0.0135 1.0000
12.500 1.4074 0.01998 0.01400 0.0013 0.0117 1.0000
12.750 1.4234 0.02070 0.01476 0.0024 0.0105 1.0000
13.000 1.4354 0.02154 0.01564 0.0040 0.0093 1.0000
13.250 1.4475 0.02243 0.01659 0.0053 0.0085 1.0000
13.500 1.4591 0.02343 0.01765 0.0064 0.0078 1.0000
13.750 1.4695 0.02460 0.01888 0.0074 0.0071 1.0000
14.000 1.4795 0.02588 0.02022 0.0082 0.0065 1.0000
14.250 1.4899 0.02717 0.02160 0.0088 0.0062 1.0000
14.500 1.4990 0.02861 0.02311 0.0094 0.0059 1.0000
14.750 1.5068 0.03020 0.02478 0.0100 0.0056 1.0000
15.000 1.5132 0.03195 0.02660 0.0105 0.0053 1.0000
15.250 1.5179 0.03391 0.02865 0.0109 0.0051 1.0000
15.500 1.5207 0.03610 0.03092 0.0112 0.0048 1.0000
15.750 1.5220 0.03850 0.03342 0.0113 0.0046 1.0000
16.000 1.5239 0.04088 0.03590 0.0114 0.0045 1.0000
16.250 1.5238 0.04355 0.03867 0.0113 0.0045 1.0000
16.500 1.5220 0.04648 0.04171 0.0110 0.0044 1.0000
16.750 1.5178 0.04978 0.04513 0.0105 0.0043 1.0000
17.000 1.5116 0.05346 0.04892 0.0097 0.0042 1.0000
17.250 1.5030 0.05762 0.05320 0.0085 0.0042 1.0000
17.500 1.4921 0.06239 0.05811 0.0069 0.0041 1.0000
17.750 1.4779 0.06789 0.06374 0.0048 0.0041 1.0000
18.000 1.4591 0.07441 0.07041 0.0019 0.0041 1.0000
18.250 1.4344 0.08233 0.07849 -0.0018 0.0041 1.0000
18.500 1.4016 0.09205 0.08840 -0.0065 0.0041 1.0000
18.750 1.3603 0.10361 0.10016 -0.0120 0.0042 1.0000
19.000 1.3136 0.11615 0.11288 -0.0181 0.0043 1.0000
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Polar data table (+)
Polar graphs
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