NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 200,000 Max Cl/Cd: 36.91 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a010-il-200000-n5.txt Download as CSV file: xf-naca64a010-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5692 0.08747 0.08401 -0.0172 1.0000 0.0159
-11.000 -0.6124 0.07026 0.06681 -0.0263 1.0000 0.0148
-10.750 -0.6871 0.05259 0.04882 -0.0354 1.0000 0.0139
-10.500 -0.7932 0.05622 0.05191 -0.0350 1.0000 0.0133
-10.250 -0.8117 0.05266 0.04815 -0.0334 1.0000 0.0133
-10.000 -0.8284 0.04954 0.04483 -0.0302 1.0000 0.0133
-9.750 -0.8416 0.04598 0.04100 -0.0272 1.0000 0.0134
-9.500 -0.8476 0.04265 0.03740 -0.0245 1.0000 0.0136
-9.250 -0.8458 0.04005 0.03457 -0.0223 1.0000 0.0138
-9.000 -0.8374 0.03839 0.03276 -0.0206 1.0000 0.0143
-8.750 -0.8278 0.03656 0.03073 -0.0188 1.0000 0.0147
-8.500 -0.8161 0.03486 0.02883 -0.0171 1.0000 0.0154
-8.250 -0.8049 0.03262 0.02628 -0.0150 1.0000 0.0161
-8.000 -0.7925 0.03008 0.02335 -0.0129 1.0000 0.0165
-7.750 -0.7774 0.02783 0.02074 -0.0110 1.0000 0.0169
-7.500 -0.7602 0.02591 0.01850 -0.0093 1.0000 0.0175
-7.250 -0.7414 0.02429 0.01662 -0.0078 1.0000 0.0181
-7.000 -0.7218 0.02298 0.01510 -0.0064 1.0000 0.0186
-6.750 -0.7038 0.02151 0.01356 -0.0050 1.0000 0.0199
-6.500 -0.6847 0.02067 0.01268 -0.0037 1.0000 0.0210
-6.250 -0.6656 0.01978 0.01170 -0.0022 1.0000 0.0222
-6.000 -0.6470 0.01883 0.01068 -0.0006 1.0000 0.0232
-5.750 -0.6291 0.01797 0.00974 0.0012 1.0000 0.0244
-5.500 -0.6116 0.01724 0.00893 0.0030 1.0000 0.0254
-5.250 -0.5962 0.01639 0.00806 0.0051 1.0000 0.0272
-5.000 -0.5795 0.01583 0.00750 0.0070 1.0000 0.0300
-4.750 -0.5536 0.01525 0.00684 0.0069 0.9969 0.0331
-4.500 -0.5209 0.01455 0.00607 0.0055 0.9903 0.0370
-4.250 -0.4878 0.01400 0.00548 0.0040 0.9837 0.0451
-4.000 -0.4549 0.01341 0.00492 0.0025 0.9769 0.0604
-3.750 -0.4247 0.01269 0.00442 0.0015 0.9686 0.1034
-3.500 -0.3980 0.01150 0.00388 0.0007 0.9599 0.2434
-3.250 -0.3749 0.01016 0.00351 0.0007 0.9505 0.4614
-3.000 -0.3480 0.00972 0.00340 0.0008 0.9402 0.5595
-2.750 -0.3185 0.00949 0.00333 0.0006 0.9307 0.6168
-2.500 -0.2880 0.00932 0.00333 0.0003 0.9223 0.6713
-2.250 -0.2601 0.00923 0.00335 0.0007 0.9115 0.7130
-2.000 -0.2301 0.00917 0.00326 0.0004 0.9011 0.7333
-1.750 -0.1990 0.00910 0.00315 -0.0001 0.8913 0.7459
-1.500 -0.1688 0.00904 0.00305 -0.0004 0.8806 0.7557
-1.250 -0.1399 0.00899 0.00296 -0.0005 0.8692 0.7654
-1.000 -0.1114 0.00895 0.00288 -0.0006 0.8582 0.7757
-0.750 -0.0828 0.00892 0.00282 -0.0006 0.8477 0.7850
-0.500 -0.0550 0.00890 0.00278 -0.0004 0.8368 0.7950
-0.250 -0.0278 0.00889 0.00275 -0.0002 0.8258 0.8058
0.000 0.0000 0.00888 0.00275 0.0000 0.8155 0.8155
0.250 0.0278 0.00889 0.00275 0.0002 0.8057 0.8257
0.500 0.0550 0.00890 0.00278 0.0004 0.7950 0.8368
0.750 0.0828 0.00892 0.00282 0.0006 0.7850 0.8477
1.000 0.1114 0.00895 0.00288 0.0006 0.7757 0.8582
1.250 0.1399 0.00899 0.00295 0.0005 0.7654 0.8692
1.500 0.1688 0.00904 0.00305 0.0004 0.7557 0.8806
1.750 0.1990 0.00910 0.00315 0.0001 0.7459 0.8913
2.000 0.2301 0.00917 0.00326 -0.0004 0.7333 0.9011
2.250 0.2602 0.00924 0.00336 -0.0007 0.7131 0.9115
2.500 0.2880 0.00932 0.00333 -0.0003 0.6716 0.9223
2.750 0.3185 0.00949 0.00333 -0.0006 0.6171 0.9307
3.000 0.3481 0.00972 0.00340 -0.0009 0.5599 0.9402
3.250 0.3750 0.01016 0.00351 -0.0007 0.4628 0.9505
3.500 0.3980 0.01150 0.00388 -0.0007 0.2438 0.9598
3.750 0.4246 0.01270 0.00442 -0.0015 0.1023 0.9686
4.000 0.4549 0.01341 0.00492 -0.0025 0.0606 0.9768
4.250 0.4877 0.01400 0.00548 -0.0040 0.0449 0.9837
4.500 0.5209 0.01455 0.00607 -0.0055 0.0371 0.9902
4.750 0.5535 0.01525 0.00684 -0.0069 0.0330 0.9969
5.000 0.5797 0.01582 0.00749 -0.0070 0.0297 1.0000
5.250 0.5961 0.01640 0.00807 -0.0051 0.0269 1.0000
5.500 0.6115 0.01725 0.00894 -0.0030 0.0254 1.0000
5.750 0.6291 0.01798 0.00975 -0.0012 0.0243 1.0000
6.000 0.6470 0.01884 0.01068 0.0006 0.0232 1.0000
6.250 0.6656 0.01978 0.01170 0.0022 0.0222 1.0000
6.500 0.6847 0.02068 0.01270 0.0037 0.0210 1.0000
6.750 0.7037 0.02146 0.01350 0.0050 0.0197 1.0000
7.000 0.7218 0.02300 0.01511 0.0064 0.0185 1.0000
7.250 0.7414 0.02428 0.01661 0.0078 0.0180 1.0000
7.500 0.7601 0.02592 0.01851 0.0093 0.0174 1.0000
7.750 0.7774 0.02782 0.02072 0.0110 0.0170 1.0000
8.000 0.7925 0.03009 0.02336 0.0129 0.0165 1.0000
8.250 0.8047 0.03267 0.02633 0.0151 0.0161 1.0000
8.500 0.8157 0.03500 0.02898 0.0171 0.0155 1.0000
8.750 0.8271 0.03674 0.03093 0.0189 0.0148 1.0000
9.000 0.8375 0.03838 0.03275 0.0206 0.0143 1.0000
9.250 0.8467 0.03987 0.03437 0.0222 0.0138 1.0000
9.500 0.8474 0.04267 0.03742 0.0245 0.0135 1.0000
9.750 0.8428 0.04590 0.04094 0.0271 0.0135 1.0000
10.000 0.8301 0.04943 0.04473 0.0301 0.0133 1.0000
10.250 0.8124 0.05262 0.04811 0.0333 0.0133 1.0000
10.500 0.7939 0.05619 0.05188 0.0349 0.0133 1.0000
10.750 0.7721 0.06071 0.05659 0.0346 0.0133 1.0000
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Polar data table (+)
Polar graphs
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