NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.07 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a010-il-1000000-n5.txt Download as CSV file: xf-naca64a010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A-010 10.0%
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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0804 0.06300 0.06077 -0.0301 1.0000 0.0045
-15.000 -1.1183 0.05342 0.05092 -0.0357 1.0000 0.0044
-14.750 -1.1274 0.04907 0.04644 -0.0378 1.0000 0.0044
-14.500 -1.1424 0.04437 0.04158 -0.0393 1.0000 0.0045
-14.250 -1.1543 0.04050 0.03753 -0.0398 1.0000 0.0045
-14.000 -1.1571 0.03794 0.03485 -0.0396 1.0000 0.0046
-13.750 -1.1633 0.03523 0.03198 -0.0387 1.0000 0.0046
-13.500 -1.1685 0.03283 0.02941 -0.0371 1.0000 0.0046
-13.250 -1.1636 0.03148 0.02797 -0.0357 1.0000 0.0047
-13.000 -1.1644 0.02972 0.02605 -0.0334 1.0000 0.0047
-12.750 -1.1576 0.02867 0.02490 -0.0314 1.0000 0.0048
-12.500 -1.1529 0.02750 0.02361 -0.0288 1.0000 0.0049
-12.250 -1.1462 0.02655 0.02256 -0.0262 1.0000 0.0050
-12.000 -1.1373 0.02566 0.02158 -0.0237 1.0000 0.0051
-11.750 -1.1285 0.02434 0.02010 -0.0215 1.0000 0.0052
-11.500 -1.1141 0.02351 0.01918 -0.0199 1.0000 0.0054
-11.250 -1.1006 0.02250 0.01804 -0.0181 1.0000 0.0055
-11.000 -1.0847 0.02169 0.01712 -0.0166 1.0000 0.0057
-10.750 -1.0678 0.02094 0.01627 -0.0152 1.0000 0.0059
-10.500 -1.0510 0.02013 0.01535 -0.0137 1.0000 0.0060
-10.250 -1.0329 0.01947 0.01459 -0.0124 1.0000 0.0061
-10.000 -1.0154 0.01871 0.01372 -0.0109 1.0000 0.0062
-9.750 -0.9969 0.01805 0.01298 -0.0095 1.0000 0.0063
-9.500 -0.9807 0.01713 0.01194 -0.0078 1.0000 0.0065
-9.250 -0.9641 0.01627 0.01099 -0.0061 1.0000 0.0068
-9.000 -0.9453 0.01566 0.01032 -0.0047 1.0000 0.0070
-8.750 -0.9259 0.01512 0.00973 -0.0033 1.0000 0.0072
-8.500 -0.9059 0.01467 0.00923 -0.0021 1.0000 0.0075
-8.250 -0.8859 0.01423 0.00874 -0.0008 1.0000 0.0077
-8.000 -0.8661 0.01380 0.00826 0.0006 1.0000 0.0080
-7.750 -0.8432 0.01335 0.00776 0.0013 0.9995 0.0083
-7.500 -0.8124 0.01289 0.00725 0.0002 0.9969 0.0087
-7.250 -0.7828 0.01243 0.00674 -0.0005 0.9930 0.0090
-7.000 -0.7526 0.01212 0.00639 -0.0013 0.9889 0.0093
-6.750 -0.7237 0.01150 0.00571 -0.0020 0.9840 0.0101
-6.500 -0.6932 0.01108 0.00527 -0.0029 0.9788 0.0106
-6.250 -0.6605 0.01071 0.00488 -0.0042 0.9737 0.0113
-6.000 -0.6274 0.01037 0.00450 -0.0057 0.9666 0.0120
-5.750 -0.5936 0.01007 0.00416 -0.0072 0.9575 0.0128
-5.500 -0.5598 0.00980 0.00386 -0.0087 0.9457 0.0133
-5.250 -0.5294 0.00946 0.00347 -0.0095 0.9289 0.0153
-5.000 -0.5019 0.00925 0.00320 -0.0095 0.9101 0.0168
-4.750 -0.4760 0.00909 0.00297 -0.0092 0.8914 0.0181
-4.500 -0.4508 0.00893 0.00274 -0.0086 0.8742 0.0201
-4.250 -0.4258 0.00876 0.00253 -0.0081 0.8580 0.0236
-4.000 -0.4004 0.00863 0.00235 -0.0076 0.8433 0.0276
-3.750 -0.3752 0.00847 0.00218 -0.0072 0.8299 0.0348
-3.500 -0.3499 0.00831 0.00201 -0.0067 0.8175 0.0457
-3.250 -0.3247 0.00812 0.00184 -0.0063 0.8058 0.0634
-3.000 -0.2998 0.00787 0.00168 -0.0058 0.7946 0.0945
-2.750 -0.2760 0.00751 0.00150 -0.0052 0.7838 0.1532
-2.500 -0.2533 0.00703 0.00131 -0.0044 0.7736 0.2411
-2.250 -0.2304 0.00658 0.00112 -0.0036 0.7635 0.3262
-2.000 -0.2083 0.00604 0.00096 -0.0028 0.7542 0.4345
-1.750 -0.1846 0.00573 0.00088 -0.0021 0.7448 0.5104
-1.500 -0.1595 0.00555 0.00083 -0.0016 0.7351 0.5582
-1.250 -0.1342 0.00540 0.00080 -0.0011 0.7263 0.6016
-1.000 -0.1081 0.00532 0.00077 -0.0007 0.7178 0.6277
-0.750 -0.0813 0.00527 0.00076 -0.0005 0.7089 0.6471
-0.500 -0.0546 0.00523 0.00075 -0.0002 0.7003 0.6632
-0.250 -0.0273 0.00523 0.00074 -0.0001 0.6912 0.6744
0.000 0.0000 0.00522 0.00074 0.0000 0.6831 0.6831
0.250 0.0273 0.00523 0.00074 0.0001 0.6744 0.6912
0.500 0.0546 0.00523 0.00075 0.0002 0.6632 0.7001
0.750 0.0814 0.00527 0.00076 0.0005 0.6473 0.7089
1.000 0.1081 0.00532 0.00077 0.0007 0.6281 0.7177
1.250 0.1342 0.00540 0.00080 0.0011 0.6010 0.7262
1.500 0.1595 0.00555 0.00083 0.0015 0.5583 0.7352
1.750 0.1846 0.00573 0.00088 0.0020 0.5106 0.7449
2.000 0.2083 0.00605 0.00096 0.0028 0.4332 0.7542
2.250 0.2305 0.00657 0.00112 0.0036 0.3283 0.7635
2.500 0.2535 0.00701 0.00130 0.0044 0.2430 0.7735
2.750 0.2760 0.00751 0.00150 0.0052 0.1532 0.7837
3.000 0.2998 0.00788 0.00168 0.0058 0.0930 0.7946
3.250 0.3247 0.00812 0.00184 0.0062 0.0632 0.8058
3.500 0.3499 0.00831 0.00201 0.0067 0.0460 0.8173
3.750 0.3752 0.00847 0.00218 0.0072 0.0348 0.8299
4.000 0.4005 0.00863 0.00235 0.0076 0.0279 0.8433
4.250 0.4258 0.00876 0.00253 0.0081 0.0235 0.8580
4.500 0.4508 0.00893 0.00274 0.0086 0.0202 0.8742
4.750 0.4760 0.00909 0.00297 0.0092 0.0181 0.8918
5.000 0.5019 0.00924 0.00320 0.0095 0.0167 0.9106
5.250 0.5294 0.00946 0.00346 0.0095 0.0151 0.9291
5.500 0.5599 0.00979 0.00385 0.0087 0.0133 0.9459
5.750 0.5936 0.01006 0.00416 0.0072 0.0127 0.9574
6.000 0.6274 0.01038 0.00451 0.0057 0.0120 0.9666
6.250 0.6604 0.01071 0.00488 0.0043 0.0113 0.9736
6.500 0.6931 0.01108 0.00526 0.0029 0.0106 0.9787
6.750 0.7235 0.01150 0.00571 0.0020 0.0100 0.9841
7.000 0.7522 0.01216 0.00643 0.0014 0.0093 0.9889
7.250 0.7825 0.01246 0.00677 0.0006 0.0090 0.9930
7.500 0.8123 0.01288 0.00724 -0.0002 0.0087 0.9968
7.750 0.8429 0.01337 0.00779 -0.0012 0.0084 0.9995
8.000 0.8658 0.01383 0.00830 -0.0005 0.0080 1.0000
8.250 0.8858 0.01425 0.00876 0.0008 0.0077 1.0000
8.500 0.9059 0.01468 0.00923 0.0021 0.0074 1.0000
8.750 0.9258 0.01513 0.00974 0.0034 0.0072 1.0000
9.000 0.9453 0.01565 0.01031 0.0047 0.0070 1.0000
9.250 0.9643 0.01624 0.01096 0.0060 0.0068 1.0000
9.500 0.9803 0.01718 0.01199 0.0079 0.0065 1.0000
9.750 0.9961 0.01815 0.01308 0.0097 0.0063 1.0000
10.000 1.0143 0.01882 0.01385 0.0111 0.0063 1.0000
10.250 1.0328 0.01946 0.01458 0.0124 0.0062 1.0000
10.500 1.0510 0.02011 0.01532 0.0137 0.0060 1.0000
10.750 1.0684 0.02084 0.01617 0.0151 0.0058 1.0000
11.000 1.0845 0.02168 0.01712 0.0166 0.0057 1.0000
11.250 1.0995 0.02259 0.01814 0.0182 0.0056 1.0000
11.500 1.1144 0.02345 0.01911 0.0198 0.0054 1.0000
11.750 1.1271 0.02447 0.02025 0.0217 0.0052 1.0000
12.000 1.1390 0.02546 0.02135 0.0236 0.0051 1.0000
12.250 1.1486 0.02632 0.02231 0.0259 0.0050 1.0000
12.500 1.1531 0.02747 0.02358 0.0288 0.0049 1.0000
12.750 1.1558 0.02881 0.02506 0.0315 0.0049 1.0000
13.000 1.1565 0.03041 0.02682 0.0341 0.0048 1.0000
13.250 1.1661 0.03126 0.02773 0.0355 0.0047 1.0000
13.500 1.1656 0.03310 0.02971 0.0373 0.0047 1.0000
13.750 1.1659 0.03499 0.03171 0.0386 0.0046 1.0000
14.000 1.1589 0.03776 0.03466 0.0395 0.0046 1.0000
14.250 1.1558 0.04037 0.03740 0.0398 0.0045 1.0000
14.500 1.1482 0.04372 0.04090 0.0394 0.0045 1.0000
14.750 1.1353 0.04808 0.04542 0.0381 0.0044 1.0000
15.000 1.1131 0.05428 0.05182 0.0352 0.0044 1.0000
15.250 1.0924 0.06107 0.05877 0.0312 0.0044 1.0000
15.500 1.0488 0.07360 0.07156 0.0227 0.0045 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64A-010 10.0% (naca64a010-il)