NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-65 (naca001065-il) Reynolds number: 500,000 Max Cl/Cd: 50.72 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001065-il-500000-n5.txt Download as CSV file: xf-naca001065-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0849 0.05823 0.05517 -0.0563 1.0000 0.0077
-15.250 -1.1135 0.05116 0.04787 -0.0593 1.0000 0.0076
-15.000 -1.1331 0.04647 0.04297 -0.0594 1.0000 0.0077
-14.750 -1.1477 0.04290 0.03920 -0.0582 1.0000 0.0077
-14.500 -1.1585 0.04001 0.03611 -0.0562 1.0000 0.0078
-14.250 -1.1660 0.03762 0.03352 -0.0536 1.0000 0.0079
-14.000 -1.1711 0.03558 0.03129 -0.0507 1.0000 0.0080
-13.750 -1.1768 0.03370 0.02925 -0.0472 1.0000 0.0081
-13.500 -1.1813 0.03208 0.02749 -0.0433 1.0000 0.0084
-13.250 -1.1833 0.03078 0.02604 -0.0394 1.0000 0.0086
-13.000 -1.1840 0.02969 0.02484 -0.0352 1.0000 0.0088
-12.750 -1.1848 0.02877 0.02380 -0.0308 1.0000 0.0090
-12.500 -1.1859 0.02798 0.02290 -0.0259 1.0000 0.0092
-12.250 -1.1848 0.02718 0.02199 -0.0215 1.0000 0.0095
-12.000 -1.1799 0.02634 0.02102 -0.0177 1.0000 0.0098
-11.750 -1.1736 0.02552 0.02008 -0.0141 1.0000 0.0101
-11.500 -1.1659 0.02474 0.01916 -0.0108 1.0000 0.0105
-11.250 -1.1556 0.02397 0.01825 -0.0079 0.9999 0.0109
-11.000 -1.1336 0.02300 0.01719 -0.0076 0.9987 0.0117
-10.750 -1.1092 0.02237 0.01648 -0.0077 0.9975 0.0125
-10.500 -1.0847 0.02177 0.01580 -0.0077 0.9963 0.0133
-10.250 -1.0601 0.02110 0.01501 -0.0077 0.9953 0.0142
-10.000 -1.0349 0.02042 0.01420 -0.0077 0.9944 0.0150
-9.750 -1.0107 0.01994 0.01371 -0.0076 0.9929 0.0161
-9.500 -0.9846 0.01966 0.01340 -0.0077 0.9913 0.0172
-9.250 -0.9585 0.01931 0.01297 -0.0078 0.9899 0.0185
-9.000 -0.9321 0.01892 0.01247 -0.0080 0.9886 0.0197
-8.750 -0.9052 0.01845 0.01191 -0.0082 0.9874 0.0205
-8.500 -0.8785 0.01789 0.01133 -0.0086 0.9864 0.0218
-8.250 -0.8495 0.01762 0.01102 -0.0093 0.9855 0.0230
-8.000 -0.8232 0.01728 0.01062 -0.0094 0.9841 0.0242
-7.750 -0.7997 0.01691 0.01019 -0.0088 0.9819 0.0254
-7.500 -0.7733 0.01658 0.00978 -0.0088 0.9801 0.0264
-7.250 -0.7453 0.01630 0.00943 -0.0092 0.9787 0.0271
-7.000 -0.7192 0.01562 0.00868 -0.0093 0.9774 0.0282
-6.750 -0.6921 0.01505 0.00808 -0.0095 0.9763 0.0296
-6.500 -0.6634 0.01463 0.00763 -0.0101 0.9755 0.0307
-6.250 -0.6338 0.01426 0.00723 -0.0108 0.9747 0.0319
-6.000 -0.6129 0.01394 0.00687 -0.0095 0.9714 0.0328
-5.750 -0.5880 0.01359 0.00647 -0.0091 0.9692 0.0336
-5.500 -0.5605 0.01325 0.00609 -0.0093 0.9675 0.0345
-5.250 -0.5317 0.01295 0.00575 -0.0098 0.9661 0.0353
-5.000 -0.5022 0.01266 0.00543 -0.0104 0.9651 0.0362
-4.750 -0.4728 0.01228 0.00502 -0.0110 0.9641 0.0380
-4.500 -0.4426 0.01198 0.00472 -0.0118 0.9633 0.0399
-4.250 -0.4145 0.01173 0.00447 -0.0120 0.9618 0.0420
-4.000 -0.3948 0.01156 0.00429 -0.0103 0.9575 0.0442
-3.750 -0.3679 0.01134 0.00408 -0.0103 0.9553 0.0486
-3.500 -0.3399 0.01108 0.00389 -0.0105 0.9535 0.0595
-3.250 -0.3113 0.01081 0.00370 -0.0109 0.9521 0.0760
-3.000 -0.2821 0.01056 0.00352 -0.0114 0.9508 0.0933
-2.750 -0.2532 0.01027 0.00336 -0.0119 0.9496 0.1208
-2.500 -0.2330 0.01004 0.00326 -0.0104 0.9455 0.1529
-2.250 -0.2100 0.00976 0.00314 -0.0095 0.9421 0.1941
-2.000 -0.1850 0.00940 0.00300 -0.0092 0.9397 0.2497
-1.750 -0.1623 0.00879 0.00281 -0.0084 0.9374 0.3592
-1.500 -0.1582 0.00731 0.00247 -0.0038 0.9338 0.6453
-1.250 -0.1487 0.00683 0.00253 0.0005 0.9279 0.7730
-1.000 -0.1215 0.00672 0.00262 0.0009 0.9256 0.8250
-0.750 -0.0910 0.00672 0.00270 0.0005 0.9238 0.8545
-0.500 -0.0596 0.00678 0.00283 0.0000 0.9222 0.8798
-0.250 -0.0255 0.00683 0.00291 -0.0011 0.9200 0.8965
0.000 0.0000 0.00687 0.00296 0.0000 0.9094 0.9094
0.250 0.0255 0.00684 0.00291 0.0011 0.8967 0.9200
0.500 0.0596 0.00678 0.00283 0.0000 0.8798 0.9222
0.750 0.0910 0.00672 0.00270 -0.0005 0.8548 0.9238
1.000 0.1215 0.00672 0.00262 -0.0009 0.8248 0.9256
1.250 0.1488 0.00683 0.00253 -0.0005 0.7732 0.9279
1.500 0.1581 0.00732 0.00247 0.0038 0.6450 0.9338
1.750 0.1623 0.00879 0.00281 0.0084 0.3595 0.9374
2.000 0.1850 0.00940 0.00300 0.0092 0.2497 0.9397
2.250 0.2099 0.00976 0.00314 0.0095 0.1936 0.9421
2.500 0.2329 0.01004 0.00326 0.0104 0.1530 0.9455
2.750 0.2532 0.01027 0.00335 0.0119 0.1209 0.9496
3.000 0.2821 0.01056 0.00352 0.0114 0.0934 0.9508
3.250 0.3113 0.01081 0.00370 0.0109 0.0761 0.9521
3.500 0.3399 0.01108 0.00389 0.0105 0.0595 0.9535
3.750 0.3678 0.01133 0.00408 0.0103 0.0486 0.9553
4.000 0.3948 0.01156 0.00429 0.0103 0.0442 0.9575
4.250 0.4123 0.01171 0.00445 0.0125 0.0420 0.9625
4.500 0.4426 0.01198 0.00471 0.0118 0.0399 0.9633
4.750 0.4728 0.01228 0.00502 0.0110 0.0380 0.9641
5.000 0.5022 0.01266 0.00543 0.0104 0.0362 0.9651
5.250 0.5317 0.01295 0.00575 0.0098 0.0353 0.9662
5.500 0.5605 0.01325 0.00609 0.0093 0.0345 0.9675
5.750 0.5879 0.01359 0.00647 0.0092 0.0337 0.9692
6.000 0.6128 0.01394 0.00687 0.0096 0.0328 0.9715
6.250 0.6338 0.01425 0.00722 0.0108 0.0319 0.9747
6.500 0.6634 0.01463 0.00763 0.0101 0.0307 0.9755
6.750 0.6922 0.01505 0.00808 0.0095 0.0296 0.9764
7.000 0.7192 0.01561 0.00868 0.0092 0.0282 0.9774
7.250 0.7453 0.01630 0.00943 0.0092 0.0271 0.9787
7.500 0.7733 0.01658 0.00978 0.0088 0.0264 0.9802
7.750 0.7997 0.01691 0.01018 0.0088 0.0254 0.9819
8.000 0.8232 0.01728 0.01062 0.0094 0.0243 0.9842
8.250 0.8496 0.01761 0.01101 0.0093 0.0230 0.9856
8.500 0.8786 0.01789 0.01132 0.0085 0.0218 0.9864
8.750 0.9053 0.01845 0.01191 0.0082 0.0205 0.9875
9.000 0.9322 0.01891 0.01247 0.0079 0.0197 0.9886
9.250 0.9586 0.01932 0.01297 0.0078 0.0185 0.9899
9.500 0.9847 0.01966 0.01340 0.0077 0.0172 0.9913
9.750 1.0109 0.01994 0.01370 0.0075 0.0161 0.9929
10.000 1.0351 0.02041 0.01420 0.0077 0.0150 0.9944
10.250 1.0604 0.02109 0.01501 0.0076 0.0142 0.9953
10.500 1.0850 0.02176 0.01579 0.0076 0.0133 0.9964
10.750 1.1095 0.02237 0.01648 0.0076 0.0125 0.9975
11.000 1.1338 0.02300 0.01719 0.0076 0.0117 0.9987
11.250 1.1559 0.02396 0.01825 0.0078 0.0109 0.9999
11.500 1.1659 0.02473 0.01916 0.0108 0.0105 1.0000
11.750 1.1736 0.02552 0.02008 0.0142 0.0102 1.0000
12.000 1.1799 0.02633 0.02102 0.0177 0.0098 1.0000
12.250 1.1849 0.02717 0.02198 0.0215 0.0095 1.0000
12.500 1.1863 0.02797 0.02289 0.0259 0.0092 1.0000
12.750 1.1850 0.02877 0.02380 0.0307 0.0090 1.0000
13.000 1.1844 0.02969 0.02483 0.0352 0.0088 1.0000
13.250 1.1837 0.03078 0.02604 0.0393 0.0086 1.0000
13.500 1.1818 0.03208 0.02749 0.0432 0.0083 1.0000
13.750 1.1773 0.03371 0.02926 0.0471 0.0081 1.0000
14.000 1.1719 0.03559 0.03130 0.0506 0.0080 1.0000
14.250 1.1670 0.03762 0.03353 0.0535 0.0079 1.0000
14.500 1.1594 0.04003 0.03613 0.0560 0.0078 1.0000
14.750 1.1488 0.04292 0.03922 0.0580 0.0077 1.0000
15.000 1.1344 0.04650 0.04300 0.0592 0.0077 1.0000
15.250 1.1145 0.05123 0.04794 0.0590 0.0076 1.0000
15.500 1.0862 0.05830 0.05524 0.0560 0.0077 1.0000
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