NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-65 (naca001065-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.31 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001065-il-1000000-n5.txt Download as CSV file: xf-naca001065-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-65
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
------ -------- --------- --------- -------- -------- --------
-17.250 -1.2134 0.06115 0.05851 -0.0552 1.0000 0.0047
-17.000 -1.2490 0.05223 0.04934 -0.0601 1.0000 0.0046
-16.750 -1.2699 0.04700 0.04393 -0.0612 1.0000 0.0047
-16.500 -1.2844 0.04312 0.03989 -0.0609 1.0000 0.0047
-16.250 -1.2943 0.04007 0.03669 -0.0597 1.0000 0.0047
-16.000 -1.3011 0.03754 0.03401 -0.0580 1.0000 0.0048
-15.750 -1.3050 0.03541 0.03175 -0.0559 1.0000 0.0049
-15.500 -1.3069 0.03355 0.02976 -0.0536 1.0000 0.0050
-15.250 -1.3068 0.03194 0.02801 -0.0511 1.0000 0.0050
-15.000 -1.3053 0.03050 0.02645 -0.0484 1.0000 0.0051
-14.750 -1.3027 0.02924 0.02506 -0.0455 1.0000 0.0052
-14.500 -1.2997 0.02810 0.02381 -0.0424 1.0000 0.0053
-14.250 -1.2967 0.02710 0.02270 -0.0390 1.0000 0.0054
-14.000 -1.2941 0.02621 0.02171 -0.0353 1.0000 0.0055
-13.750 -1.2922 0.02545 0.02085 -0.0312 1.0000 0.0056
-13.500 -1.2922 0.02481 0.02012 -0.0265 1.0000 0.0057
-13.250 -1.2936 0.02427 0.01949 -0.0213 1.0000 0.0058
-13.000 -1.2816 0.02323 0.01834 -0.0192 0.9993 0.0061
-12.750 -1.2614 0.02223 0.01725 -0.0187 0.9982 0.0064
-12.500 -1.2400 0.02137 0.01629 -0.0183 0.9971 0.0067
-12.250 -1.2179 0.02060 0.01544 -0.0181 0.9961 0.0071
-12.000 -1.1948 0.01988 0.01463 -0.0179 0.9953 0.0074
-11.750 -1.1706 0.01921 0.01386 -0.0179 0.9946 0.0077
-11.500 -1.1475 0.01861 0.01317 -0.0176 0.9935 0.0080
-11.250 -1.1254 0.01794 0.01243 -0.0171 0.9920 0.0085
-11.000 -1.1022 0.01732 0.01174 -0.0167 0.9907 0.0091
-10.750 -1.0778 0.01676 0.01114 -0.0166 0.9896 0.0098
-10.500 -1.0522 0.01625 0.01057 -0.0167 0.9885 0.0105
-10.250 -1.0259 0.01576 0.01002 -0.0169 0.9876 0.0112
-10.000 -0.9990 0.01530 0.00955 -0.0173 0.9869 0.0126
-9.750 -0.9716 0.01490 0.00914 -0.0177 0.9862 0.0139
-9.500 -0.9437 0.01452 0.00870 -0.0182 0.9857 0.0149
-9.250 -0.9150 0.01418 0.00837 -0.0188 0.9852 0.0164
-9.000 -0.8907 0.01393 0.00812 -0.0184 0.9832 0.0178
-8.750 -0.8649 0.01368 0.00786 -0.0183 0.9815 0.0190
-8.500 -0.8378 0.01346 0.00760 -0.0185 0.9802 0.0198
-8.250 -0.8100 0.01325 0.00735 -0.0188 0.9790 0.0203
-8.000 -0.7835 0.01279 0.00687 -0.0189 0.9778 0.0215
-7.750 -0.7555 0.01250 0.00657 -0.0193 0.9768 0.0226
-7.500 -0.7270 0.01225 0.00632 -0.0198 0.9759 0.0236
-7.250 -0.6987 0.01199 0.00603 -0.0202 0.9750 0.0245
-7.000 -0.6736 0.01176 0.00577 -0.0198 0.9730 0.0253
-6.750 -0.6496 0.01154 0.00553 -0.0192 0.9704 0.0260
-6.500 -0.6235 0.01133 0.00530 -0.0190 0.9684 0.0266
-6.250 -0.5965 0.01111 0.00506 -0.0191 0.9667 0.0270
-6.000 -0.5691 0.01090 0.00482 -0.0192 0.9652 0.0272
-5.750 -0.5429 0.01055 0.00443 -0.0191 0.9637 0.0281
-5.500 -0.5160 0.01023 0.00408 -0.0191 0.9624 0.0291
-5.250 -0.4935 0.01000 0.00384 -0.0180 0.9592 0.0301
-5.000 -0.4686 0.00979 0.00362 -0.0175 0.9566 0.0314
-4.750 -0.4426 0.00959 0.00342 -0.0173 0.9543 0.0324
-4.500 -0.4161 0.00939 0.00322 -0.0171 0.9523 0.0332
-4.250 -0.3889 0.00921 0.00302 -0.0171 0.9505 0.0341
-4.000 -0.3615 0.00905 0.00284 -0.0171 0.9488 0.0350
-3.750 -0.3372 0.00892 0.00271 -0.0165 0.9457 0.0358
-3.500 -0.3119 0.00876 0.00257 -0.0160 0.9428 0.0390
-3.250 -0.2860 0.00859 0.00243 -0.0157 0.9401 0.0441
-3.000 -0.2600 0.00837 0.00229 -0.0154 0.9377 0.0587
-2.750 -0.2331 0.00818 0.00216 -0.0153 0.9356 0.0738
-2.500 -0.2071 0.00803 0.00206 -0.0150 0.9331 0.0862
-2.250 -0.1825 0.00786 0.00198 -0.0145 0.9297 0.1034
-2.000 -0.1580 0.00763 0.00188 -0.0139 0.9265 0.1374
-1.750 -0.1328 0.00740 0.00179 -0.0134 0.9236 0.1735
-1.500 -0.1076 0.00712 0.00168 -0.0130 0.9210 0.2245
-1.250 -0.0846 0.00677 0.00159 -0.0122 0.9177 0.2960
-1.000 -0.0664 0.00624 0.00146 -0.0103 0.9108 0.4125
-0.750 -0.0593 0.00514 0.00119 -0.0060 0.9007 0.6464
-0.500 -0.0447 0.00465 0.00108 -0.0030 0.8877 0.7556
-0.250 -0.0237 0.00445 0.00103 -0.0012 0.8690 0.8095
0.000 0.0000 0.00440 0.00101 0.0000 0.8425 0.8429
0.250 0.0238 0.00445 0.00103 0.0012 0.8096 0.8691
0.500 0.0447 0.00465 0.00108 0.0030 0.7548 0.8874
0.750 0.0596 0.00514 0.00119 0.0060 0.6481 0.9006
1.000 0.0663 0.00624 0.00146 0.0103 0.4114 0.9108
1.250 0.0847 0.00677 0.00159 0.0122 0.2959 0.9178
1.500 0.1076 0.00711 0.00168 0.0130 0.2251 0.9210
1.750 0.1329 0.00740 0.00179 0.0134 0.1741 0.9236
2.000 0.1581 0.00763 0.00188 0.0139 0.1378 0.9264
2.250 0.1826 0.00786 0.00198 0.0144 0.1033 0.9297
2.500 0.2072 0.00803 0.00206 0.0150 0.0863 0.9331
2.750 0.2332 0.00818 0.00216 0.0153 0.0741 0.9356
3.000 0.2601 0.00837 0.00229 0.0154 0.0587 0.9377
3.250 0.2861 0.00859 0.00243 0.0157 0.0442 0.9401
3.500 0.3119 0.00876 0.00257 0.0160 0.0390 0.9428
3.750 0.3373 0.00892 0.00271 0.0164 0.0358 0.9457
4.000 0.3616 0.00905 0.00284 0.0171 0.0350 0.9488
4.250 0.3890 0.00921 0.00302 0.0171 0.0341 0.9505
4.500 0.4161 0.00939 0.00322 0.0171 0.0332 0.9523
4.750 0.4427 0.00959 0.00342 0.0173 0.0324 0.9543
5.000 0.4687 0.00979 0.00362 0.0175 0.0314 0.9566
5.250 0.4936 0.01000 0.00384 0.0180 0.0301 0.9592
5.500 0.5161 0.01023 0.00408 0.0190 0.0291 0.9624
5.750 0.5430 0.01054 0.00442 0.0191 0.0281 0.9637
6.000 0.5692 0.01090 0.00482 0.0192 0.0272 0.9652
6.250 0.5966 0.01111 0.00506 0.0191 0.0270 0.9667
6.500 0.6236 0.01133 0.00530 0.0190 0.0266 0.9684
6.750 0.6497 0.01155 0.00553 0.0192 0.0260 0.9704
7.000 0.6737 0.01176 0.00577 0.0198 0.0253 0.9730
7.250 0.6988 0.01199 0.00603 0.0202 0.0245 0.9750
7.500 0.7271 0.01225 0.00632 0.0197 0.0236 0.9759
7.750 0.7556 0.01249 0.00657 0.0193 0.0226 0.9768
8.000 0.7835 0.01279 0.00686 0.0189 0.0215 0.9778
8.250 0.8101 0.01325 0.00735 0.0188 0.0203 0.9790
8.500 0.8379 0.01345 0.00760 0.0185 0.0198 0.9802
8.750 0.8650 0.01368 0.00786 0.0183 0.0190 0.9816
9.000 0.8907 0.01392 0.00812 0.0184 0.0178 0.9833
9.250 0.9152 0.01418 0.00837 0.0188 0.0165 0.9852
9.500 0.9439 0.01452 0.00870 0.0181 0.0149 0.9857
9.750 0.9718 0.01490 0.00914 0.0176 0.0140 0.9863
10.000 0.9992 0.01530 0.00955 0.0172 0.0126 0.9869
10.250 1.0260 0.01576 0.01002 0.0169 0.0112 0.9876
10.500 1.0524 0.01625 0.01057 0.0167 0.0105 0.9885
10.750 1.0780 0.01676 0.01114 0.0166 0.0098 0.9896
11.000 1.1025 0.01732 0.01174 0.0167 0.0091 0.9908
11.250 1.1257 0.01794 0.01243 0.0170 0.0085 0.9921
11.500 1.1479 0.01860 0.01317 0.0175 0.0080 0.9935
11.750 1.1711 0.01921 0.01387 0.0178 0.0077 0.9946
12.000 1.1952 0.01988 0.01463 0.0178 0.0074 0.9953
12.250 1.2183 0.02060 0.01543 0.0180 0.0071 0.9962
12.500 1.2404 0.02137 0.01629 0.0183 0.0067 0.9971
12.750 1.2617 0.02223 0.01725 0.0186 0.0064 0.9982
13.000 1.2819 0.02323 0.01834 0.0191 0.0061 0.9993
13.250 1.2938 0.02426 0.01948 0.0212 0.0058 1.0000
13.500 1.2924 0.02481 0.02011 0.0264 0.0057 1.0000
13.750 1.2925 0.02544 0.02084 0.0311 0.0056 1.0000
14.000 1.2944 0.02621 0.02171 0.0352 0.0055 1.0000
14.250 1.2973 0.02709 0.02269 0.0389 0.0054 1.0000
14.500 1.3003 0.02810 0.02381 0.0423 0.0053 1.0000
14.750 1.3035 0.02924 0.02507 0.0454 0.0052 1.0000
15.000 1.3062 0.03051 0.02645 0.0482 0.0051 1.0000
15.250 1.3077 0.03195 0.02802 0.0509 0.0050 1.0000
15.500 1.3081 0.03356 0.02977 0.0534 0.0049 1.0000
15.750 1.3062 0.03542 0.03176 0.0557 0.0049 1.0000
16.000 1.3026 0.03754 0.03402 0.0577 0.0048 1.0000
16.250 1.2959 0.04007 0.03669 0.0594 0.0047 1.0000
16.500 1.2860 0.04313 0.03990 0.0606 0.0047 1.0000
16.750 1.2716 0.04700 0.04394 0.0609 0.0046 1.0000
17.000 1.2509 0.05223 0.04935 0.0598 0.0046 1.0000
17.250 1.2152 0.06121 0.05857 0.0548 0.0047 1.0000
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