NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Reynolds number: 500,000 Max Cl/Cd: 51.48 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64012-il-500000-n5.txt Download as CSV file: xf-n64012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY 64-012 AIRFOIL
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 -1.0015 0.08651 0.08373 -0.0070 1.0000 0.0099
-15.250 -1.0621 0.07087 0.06767 -0.0166 1.0000 0.0097
-15.000 -1.0683 0.06631 0.06301 -0.0192 1.0000 0.0098
-14.750 -1.0815 0.06097 0.05751 -0.0219 1.0000 0.0098
-14.500 -1.0890 0.05682 0.05324 -0.0237 1.0000 0.0100
-14.250 -1.0942 0.05316 0.04945 -0.0251 1.0000 0.0101
-14.000 -1.0994 0.04971 0.04586 -0.0261 1.0000 0.0101
-13.750 -1.1032 0.04660 0.04262 -0.0267 1.0000 0.0103
-13.500 -1.1071 0.04360 0.03947 -0.0269 1.0000 0.0104
-13.250 -1.1084 0.04102 0.03673 -0.0268 1.0000 0.0105
-13.000 -1.1085 0.03867 0.03423 -0.0264 1.0000 0.0107
-12.750 -1.1074 0.03649 0.03190 -0.0256 1.0000 0.0109
-12.500 -1.1049 0.03451 0.02976 -0.0247 1.0000 0.0110
-12.250 -1.1010 0.03268 0.02776 -0.0235 1.0000 0.0112
-12.000 -1.0956 0.03100 0.02593 -0.0221 1.0000 0.0114
-11.750 -1.0885 0.02950 0.02428 -0.0207 1.0000 0.0116
-11.500 -1.0798 0.02820 0.02283 -0.0191 1.0000 0.0118
-11.250 -1.0700 0.02699 0.02146 -0.0175 1.0000 0.0120
-11.000 -1.0583 0.02604 0.02040 -0.0159 1.0000 0.0122
-10.750 -1.0466 0.02490 0.01913 -0.0142 1.0000 0.0124
-10.500 -1.0335 0.02366 0.01782 -0.0128 1.0000 0.0128
-10.250 -1.0171 0.02273 0.01682 -0.0117 1.0000 0.0131
-10.000 -0.9990 0.02194 0.01596 -0.0108 1.0000 0.0134
-9.750 -0.9801 0.02116 0.01512 -0.0099 1.0000 0.0136
-9.500 -0.9607 0.02039 0.01427 -0.0091 1.0000 0.0139
-9.250 -0.9408 0.01962 0.01344 -0.0084 1.0000 0.0143
-9.000 -0.9203 0.01889 0.01265 -0.0076 1.0000 0.0147
-8.750 -0.8992 0.01821 0.01190 -0.0070 1.0000 0.0151
-8.500 -0.8773 0.01761 0.01124 -0.0064 1.0000 0.0156
-8.250 -0.8484 0.01698 0.01052 -0.0073 0.9696 0.0161
-8.000 -0.8205 0.01617 0.00962 -0.0080 0.9473 0.0166
-7.750 -0.7988 0.01555 0.00893 -0.0073 0.9276 0.0173
-7.500 -0.7773 0.01510 0.00842 -0.0064 0.9111 0.0179
-7.250 -0.7554 0.01469 0.00794 -0.0055 0.8968 0.0186
-7.000 -0.7331 0.01428 0.00744 -0.0046 0.8837 0.0194
-6.750 -0.7101 0.01391 0.00698 -0.0039 0.8720 0.0203
-6.500 -0.6863 0.01356 0.00654 -0.0033 0.8605 0.0211
-6.250 -0.6629 0.01310 0.00602 -0.0027 0.8498 0.0226
-6.000 -0.6385 0.01276 0.00564 -0.0022 0.8399 0.0245
-5.750 -0.6134 0.01248 0.00529 -0.0019 0.8301 0.0266
-5.500 -0.5879 0.01219 0.00494 -0.0016 0.8207 0.0286
-5.250 -0.5628 0.01186 0.00456 -0.0012 0.8117 0.0318
-5.000 -0.5368 0.01159 0.00426 -0.0010 0.8026 0.0350
-4.750 -0.5107 0.01133 0.00396 -0.0008 0.7941 0.0398
-4.500 -0.4847 0.01106 0.00368 -0.0006 0.7853 0.0481
-4.250 -0.4589 0.01071 0.00339 -0.0004 0.7767 0.0671
-4.000 -0.4338 0.01028 0.00309 -0.0002 0.7685 0.1041
-3.750 -0.4089 0.00973 0.00278 -0.0001 0.7604 0.1631
-3.250 -0.3618 0.00822 0.00205 0.0005 0.7448 0.3678
-3.000 -0.3367 0.00778 0.00188 0.0007 0.7371 0.4518
-2.750 -0.3096 0.00758 0.00178 0.0007 0.7289 0.4911
-2.500 -0.2825 0.00743 0.00171 0.0008 0.7214 0.5283
-2.250 -0.2552 0.00730 0.00167 0.0009 0.7137 0.5629
-1.750 -0.1996 0.00718 0.00161 0.0009 0.6996 0.6058
-1.500 -0.1712 0.00716 0.00155 0.0008 0.6927 0.6139
-1.250 -0.1427 0.00713 0.00152 0.0007 0.6858 0.6215
-1.000 -0.1142 0.00712 0.00147 0.0006 0.6787 0.6284
-0.750 -0.0857 0.00711 0.00144 0.0004 0.6719 0.6342
-0.500 -0.0572 0.00710 0.00142 0.0003 0.6649 0.6405
-0.250 -0.0285 0.00710 0.00141 0.0001 0.6589 0.6467
0.000 0.0000 0.00709 0.00141 0.0000 0.6525 0.6525
0.250 0.0286 0.00710 0.00141 -0.0001 0.6467 0.6589
0.500 0.0572 0.00710 0.00142 -0.0003 0.6406 0.6649
0.750 0.0857 0.00711 0.00144 -0.0004 0.6342 0.6719
1.000 0.1143 0.00712 0.00147 -0.0006 0.6284 0.6787
1.250 0.1428 0.00713 0.00152 -0.0007 0.6215 0.6858
1.500 0.1712 0.00716 0.00155 -0.0008 0.6140 0.6927
1.750 0.1996 0.00718 0.00161 -0.0009 0.6058 0.6996
2.250 0.2553 0.00730 0.00167 -0.0009 0.5633 0.7137
2.500 0.2826 0.00743 0.00171 -0.0008 0.5282 0.7214
2.750 0.3096 0.00759 0.00178 -0.0007 0.4908 0.7289
3.000 0.3367 0.00778 0.00188 -0.0007 0.4517 0.7371
3.250 0.3619 0.00822 0.00205 -0.0005 0.3676 0.7448
3.750 0.4089 0.00974 0.00278 0.0000 0.1624 0.7604
4.000 0.4338 0.01028 0.00309 0.0002 0.1040 0.7685
4.250 0.4590 0.01071 0.00340 0.0004 0.0670 0.7768
4.500 0.4847 0.01106 0.00369 0.0006 0.0479 0.7853
4.750 0.5108 0.01133 0.00396 0.0008 0.0397 0.7942
5.000 0.5368 0.01160 0.00426 0.0010 0.0350 0.8026
5.250 0.5628 0.01186 0.00456 0.0012 0.0318 0.8117
5.500 0.5880 0.01219 0.00494 0.0016 0.0285 0.8207
5.750 0.6135 0.01248 0.00529 0.0018 0.0265 0.8301
6.000 0.6386 0.01276 0.00564 0.0022 0.0245 0.8399
6.250 0.6630 0.01310 0.00602 0.0027 0.0227 0.8497
6.500 0.6864 0.01357 0.00655 0.0033 0.0211 0.8605
6.750 0.7102 0.01391 0.00698 0.0039 0.0203 0.8720
7.000 0.7331 0.01429 0.00744 0.0046 0.0194 0.8837
7.250 0.7555 0.01469 0.00794 0.0055 0.0186 0.8968
7.500 0.7774 0.01510 0.00842 0.0064 0.0178 0.9111
7.750 0.7987 0.01555 0.00894 0.0073 0.0172 0.9276
8.000 0.8204 0.01618 0.00963 0.0081 0.0166 0.9473
8.250 0.8483 0.01698 0.01051 0.0073 0.0161 0.9696
8.500 0.8775 0.01758 0.01121 0.0064 0.0155 1.0000
8.750 0.8992 0.01820 0.01189 0.0070 0.0151 1.0000
9.000 0.9201 0.01890 0.01266 0.0076 0.0147 1.0000
9.250 0.9406 0.01964 0.01346 0.0084 0.0143 1.0000
9.500 0.9606 0.02040 0.01428 0.0091 0.0140 1.0000
9.750 0.9803 0.02113 0.01509 0.0099 0.0136 1.0000
10.000 0.9988 0.02198 0.01601 0.0108 0.0134 1.0000
10.250 1.0168 0.02277 0.01686 0.0117 0.0131 1.0000
10.500 1.0337 0.02363 0.01778 0.0128 0.0128 1.0000
10.750 1.0469 0.02487 0.01911 0.0142 0.0125 1.0000
11.000 1.0582 0.02606 0.02041 0.0159 0.0122 1.0000
11.250 1.0698 0.02705 0.02153 0.0175 0.0120 1.0000
11.500 1.0798 0.02823 0.02286 0.0191 0.0118 1.0000
11.750 1.0883 0.02959 0.02437 0.0207 0.0116 1.0000
12.000 1.0955 0.03107 0.02601 0.0221 0.0114 1.0000
12.250 1.1011 0.03271 0.02781 0.0234 0.0112 1.0000
12.500 1.1049 0.03457 0.02982 0.0246 0.0111 1.0000
12.750 1.1074 0.03657 0.03198 0.0256 0.0109 1.0000
13.000 1.1091 0.03866 0.03423 0.0263 0.0107 1.0000
13.250 1.1087 0.04107 0.03680 0.0267 0.0106 1.0000
13.500 1.1069 0.04372 0.03959 0.0268 0.0104 1.0000
13.750 1.1020 0.04686 0.04290 0.0266 0.0103 1.0000
14.000 1.1013 0.04957 0.04571 0.0260 0.0101 1.0000
14.250 1.0975 0.05284 0.04911 0.0251 0.0101 1.0000
14.500 1.0964 0.05590 0.05227 0.0239 0.0099 1.0000
14.750 1.0812 0.06119 0.05776 0.0216 0.0099 1.0000
15.000 1.0720 0.06592 0.06261 0.0192 0.0098 1.0000
15.250 1.0667 0.07030 0.06707 0.0167 0.0097 1.0000
15.500 1.0066 0.08571 0.08291 0.0073 0.0099 1.0000
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Polar data table (+)
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