NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.14 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a010-il-1000000.txt Download as CSV file: xf-naca64a010-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7715 0.06552 0.06374 -0.0317 1.0000 0.0087
-11.250 -0.7985 0.05836 0.05646 -0.0362 1.0000 0.0086
-11.000 -0.8317 0.05190 0.04982 -0.0378 1.0000 0.0085
-10.750 -0.8652 0.04647 0.04417 -0.0360 1.0000 0.0084
-10.500 -0.9074 0.04092 0.03830 -0.0300 1.0000 0.0082
-10.250 -0.9366 0.03485 0.03178 -0.0246 1.0000 0.0082
-10.000 -0.9470 0.03047 0.02698 -0.0205 1.0000 0.0083
-9.750 -0.9461 0.02726 0.02341 -0.0172 1.0000 0.0085
-9.500 -0.9345 0.02560 0.02153 -0.0151 1.0000 0.0088
-9.250 -0.9196 0.02440 0.02016 -0.0133 1.0000 0.0091
-9.000 -0.8998 0.02418 0.01984 -0.0121 1.0000 0.0093
-8.750 -0.8953 0.02042 0.01565 -0.0088 1.0000 0.0096
-8.500 -0.8820 0.01848 0.01353 -0.0066 1.0000 0.0100
-8.250 -0.8639 0.01762 0.01260 -0.0051 1.0000 0.0103
-8.000 -0.8447 0.01700 0.01192 -0.0037 1.0000 0.0107
-7.750 -0.8260 0.01627 0.01112 -0.0022 1.0000 0.0110
-7.500 -0.8070 0.01565 0.01043 -0.0007 1.0000 0.0114
-7.250 -0.7891 0.01489 0.00959 0.0011 1.0000 0.0117
-7.000 -0.7707 0.01430 0.00895 0.0028 1.0000 0.0122
-6.750 -0.7523 0.01381 0.00841 0.0045 1.0000 0.0127
-6.500 -0.7322 0.01354 0.00810 0.0059 0.9999 0.0131
-6.250 -0.7017 0.01229 0.00673 0.0048 0.9977 0.0140
-6.000 -0.6693 0.01149 0.00587 0.0033 0.9951 0.0149
-5.750 -0.6367 0.01106 0.00543 0.0020 0.9920 0.0159
-5.500 -0.6036 0.01062 0.00496 0.0006 0.9888 0.0169
-5.250 -0.5688 0.01025 0.00455 -0.0011 0.9863 0.0181
-5.000 -0.5379 0.00981 0.00406 -0.0020 0.9812 0.0194
-4.750 -0.5046 0.00929 0.00352 -0.0034 0.9773 0.0223
-4.500 -0.4719 0.00900 0.00321 -0.0046 0.9715 0.0248
-4.250 -0.4378 0.00862 0.00283 -0.0061 0.9654 0.0305
-4.000 -0.4059 0.00831 0.00253 -0.0072 0.9557 0.0402
-3.750 -0.3752 0.00793 0.00227 -0.0080 0.9439 0.0681
-3.500 -0.3484 0.00742 0.00199 -0.0080 0.9286 0.1316
-3.250 -0.3261 0.00675 0.00169 -0.0072 0.9114 0.2419
-3.000 -0.3074 0.00591 0.00139 -0.0058 0.8942 0.3953
-2.750 -0.2861 0.00544 0.00124 -0.0046 0.8784 0.5017
-2.500 -0.2618 0.00526 0.00116 -0.0039 0.8641 0.5500
-2.250 -0.2363 0.00516 0.00109 -0.0034 0.8508 0.5795
-2.000 -0.2104 0.00509 0.00104 -0.0029 0.8383 0.6042
-1.750 -0.1848 0.00501 0.00100 -0.0024 0.8262 0.6325
-1.500 -0.1590 0.00495 0.00098 -0.0019 0.8148 0.6587
-1.250 -0.1335 0.00490 0.00096 -0.0014 0.8039 0.6850
-1.000 -0.1071 0.00488 0.00094 -0.0011 0.7933 0.7033
-0.750 -0.0805 0.00486 0.00093 -0.0008 0.7829 0.7184
-0.500 -0.0538 0.00485 0.00093 -0.0005 0.7728 0.7322
-0.250 -0.0271 0.00484 0.00092 -0.0002 0.7628 0.7432
0.000 0.0000 0.00483 0.00092 0.0000 0.7529 0.7529
0.250 0.0272 0.00484 0.00092 0.0002 0.7432 0.7628
0.500 0.0539 0.00485 0.00093 0.0004 0.7322 0.7728
0.750 0.0805 0.00486 0.00093 0.0007 0.7185 0.7829
1.000 0.1071 0.00488 0.00094 0.0010 0.7035 0.7933
1.250 0.1335 0.00490 0.00096 0.0014 0.6846 0.8039
1.500 0.1591 0.00495 0.00098 0.0019 0.6588 0.8148
1.750 0.1848 0.00501 0.00100 0.0024 0.6327 0.8263
2.000 0.2104 0.00509 0.00104 0.0029 0.6040 0.8383
2.250 0.2363 0.00516 0.00110 0.0034 0.5799 0.8508
2.500 0.2618 0.00525 0.00116 0.0039 0.5508 0.8640
2.750 0.2860 0.00545 0.00124 0.0046 0.5010 0.8784
3.000 0.3073 0.00593 0.00139 0.0058 0.3917 0.8942
3.250 0.3261 0.00675 0.00169 0.0072 0.2413 0.9114
3.500 0.3484 0.00741 0.00199 0.0080 0.1329 0.9285
3.750 0.3751 0.00793 0.00227 0.0080 0.0683 0.9439
4.000 0.4058 0.00831 0.00253 0.0072 0.0405 0.9557
4.250 0.4378 0.00862 0.00283 0.0061 0.0303 0.9654
4.500 0.4719 0.00900 0.00321 0.0046 0.0249 0.9714
4.750 0.5046 0.00929 0.00352 0.0034 0.0222 0.9774
5.000 0.5376 0.00986 0.00412 0.0020 0.0191 0.9813
5.250 0.5689 0.01022 0.00452 0.0011 0.0180 0.9863
5.500 0.6036 0.01061 0.00494 -0.0006 0.0169 0.9888
5.750 0.6368 0.01104 0.00540 -0.0020 0.0158 0.9920
6.000 0.6692 0.01151 0.00590 -0.0033 0.0149 0.9951
6.250 0.7015 0.01232 0.00676 -0.0047 0.0140 0.9977
6.500 0.7323 0.01350 0.00806 -0.0059 0.0131 0.9999
6.750 0.7527 0.01378 0.00837 -0.0046 0.0126 1.0000
7.000 0.7704 0.01436 0.00901 -0.0027 0.0122 1.0000
7.250 0.7889 0.01493 0.00964 -0.0010 0.0117 1.0000
7.500 0.8070 0.01566 0.01045 0.0007 0.0113 1.0000
7.750 0.8257 0.01635 0.01121 0.0023 0.0110 1.0000
8.000 0.8443 0.01712 0.01206 0.0038 0.0107 1.0000
8.250 0.8632 0.01781 0.01281 0.0052 0.0104 1.0000
8.500 0.8818 0.01854 0.01359 0.0066 0.0100 1.0000
8.750 0.8964 0.02018 0.01538 0.0086 0.0097 1.0000
9.000 0.8999 0.02415 0.01981 0.0120 0.0093 1.0000
9.250 0.9186 0.02458 0.02037 0.0134 0.0091 1.0000
9.500 0.9344 0.02560 0.02154 0.0151 0.0088 1.0000
9.750 0.9449 0.02746 0.02363 0.0173 0.0086 1.0000
10.000 0.9479 0.03032 0.02681 0.0204 0.0083 1.0000
10.250 0.9377 0.03470 0.03161 0.0245 0.0082 1.0000
10.500 0.9096 0.04068 0.03805 0.0298 0.0082 1.0000
10.750 0.8614 0.04699 0.04471 0.0362 0.0084 1.0000
11.000 0.8303 0.05214 0.05007 0.0377 0.0085 1.0000
11.250 0.8031 0.05765 0.05572 0.0363 0.0086 1.0000
11.500 0.7691 0.06616 0.06439 0.0312 0.0087 1.0000
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Polar data table (+)
Polar graphs
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