NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.43 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64012-il-1000000-n5.txt Download as CSV file: xf-n64012-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1219 0.11239 0.11018 0.0097 1.0000 0.0071
-18.000 -1.1586 0.09946 0.09708 0.0018 1.0000 0.0071
-17.750 -1.1985 0.08676 0.08413 -0.0060 1.0000 0.0070
-17.500 -1.2221 0.07812 0.07532 -0.0112 1.0000 0.0070
-17.250 -1.2382 0.07141 0.06847 -0.0150 1.0000 0.0070
-17.000 -1.2551 0.06505 0.06196 -0.0183 1.0000 0.0070
-16.750 -1.2634 0.06035 0.05715 -0.0206 1.0000 0.0071
-16.500 -1.2693 0.05623 0.05293 -0.0223 1.0000 0.0072
-16.250 -1.2742 0.05249 0.04909 -0.0237 1.0000 0.0073
-16.000 -1.2776 0.04909 0.04558 -0.0248 1.0000 0.0074
-15.750 -1.2798 0.04599 0.04238 -0.0255 1.0000 0.0074
-15.500 -1.2791 0.04334 0.03963 -0.0260 1.0000 0.0075
-15.250 -1.2805 0.04056 0.03672 -0.0262 1.0000 0.0076
-15.000 -1.2770 0.03841 0.03449 -0.0263 1.0000 0.0076
-14.750 -1.2744 0.03625 0.03222 -0.0261 1.0000 0.0077
-14.500 -1.2689 0.03445 0.03035 -0.0257 1.0000 0.0079
-14.250 -1.2642 0.03264 0.02843 -0.0252 1.0000 0.0079
-14.000 -1.2577 0.03106 0.02676 -0.0245 1.0000 0.0081
-13.750 -1.2503 0.02962 0.02523 -0.0236 1.0000 0.0082
-13.500 -1.2432 0.02820 0.02372 -0.0226 1.0000 0.0084
-13.250 -1.2353 0.02691 0.02234 -0.0215 1.0000 0.0085
-13.000 -1.2263 0.02575 0.02109 -0.0202 1.0000 0.0086
-12.750 -1.2153 0.02480 0.02005 -0.0190 1.0000 0.0088
-12.500 -1.2038 0.02392 0.01910 -0.0176 1.0000 0.0089
-12.250 -1.1926 0.02308 0.01817 -0.0160 1.0000 0.0090
-12.000 -1.1811 0.02231 0.01733 -0.0143 1.0000 0.0091
-11.750 -1.1686 0.02163 0.01658 -0.0125 1.0000 0.0092
-11.500 -1.1585 0.02062 0.01548 -0.0104 1.0000 0.0094
-11.250 -1.1443 0.01967 0.01446 -0.0090 1.0000 0.0096
-11.000 -1.1268 0.01895 0.01368 -0.0079 1.0000 0.0098
-10.750 -1.1081 0.01827 0.01294 -0.0070 1.0000 0.0100
-10.500 -1.0880 0.01768 0.01230 -0.0062 1.0000 0.0102
-10.250 -1.0670 0.01712 0.01170 -0.0055 1.0000 0.0104
-10.000 -1.0451 0.01662 0.01117 -0.0049 1.0000 0.0107
-9.750 -1.0228 0.01613 0.01065 -0.0044 0.9911 0.0110
-9.500 -0.9909 0.01559 0.01002 -0.0059 0.9537 0.0113
-9.250 -0.9693 0.01515 0.00947 -0.0051 0.9298 0.0115
-9.000 -0.9484 0.01473 0.00897 -0.0041 0.9115 0.0117
-8.750 -0.9267 0.01434 0.00848 -0.0032 0.8959 0.0119
-8.500 -0.9040 0.01397 0.00803 -0.0025 0.8824 0.0122
-8.250 -0.8808 0.01362 0.00759 -0.0019 0.8700 0.0123
-8.000 -0.8583 0.01312 0.00701 -0.0011 0.8581 0.0130
-7.750 -0.8343 0.01275 0.00659 -0.0007 0.8469 0.0136
-7.500 -0.8096 0.01243 0.00622 -0.0003 0.8365 0.0141
-7.250 -0.7846 0.01213 0.00587 0.0000 0.8267 0.0146
-7.000 -0.7593 0.01184 0.00551 0.0003 0.8168 0.0152
-6.750 -0.7336 0.01157 0.00519 0.0005 0.8078 0.0157
-6.250 -0.6818 0.01102 0.00455 0.0009 0.7899 0.0176
-6.000 -0.6556 0.01078 0.00427 0.0010 0.7814 0.0191
-5.750 -0.6290 0.01056 0.00402 0.0011 0.7725 0.0205
-5.500 -0.6022 0.01037 0.00378 0.0012 0.7643 0.0218
-5.250 -0.5756 0.01013 0.00353 0.0013 0.7560 0.0242
-5.000 -0.5486 0.00994 0.00331 0.0013 0.7486 0.0265
-4.750 -0.5213 0.00977 0.00311 0.0013 0.7406 0.0288
-4.500 -0.4943 0.00956 0.00290 0.0013 0.7332 0.0329
-4.250 -0.4669 0.00940 0.00271 0.0013 0.7250 0.0366
-4.000 -0.4397 0.00919 0.00252 0.0013 0.7173 0.0449
-3.750 -0.4127 0.00895 0.00233 0.0013 0.7092 0.0621
-3.500 -0.3861 0.00862 0.00212 0.0013 0.7021 0.0964
-3.250 -0.3598 0.00822 0.00190 0.0013 0.6947 0.1450
-3.000 -0.3338 0.00777 0.00168 0.0013 0.6880 0.2111
-2.750 -0.3081 0.00724 0.00144 0.0014 0.6809 0.2924
-2.500 -0.2821 0.00676 0.00123 0.0014 0.6744 0.3690
-2.250 -0.2557 0.00635 0.00109 0.0014 0.6676 0.4501
-2.000 -0.2282 0.00617 0.00102 0.0013 0.6608 0.4926
-1.750 -0.2002 0.00603 0.00098 0.0012 0.6538 0.5261
-1.500 -0.1724 0.00590 0.00095 0.0012 0.6470 0.5607
-1.250 -0.1439 0.00585 0.00093 0.0010 0.6409 0.5766
-1.000 -0.1151 0.00584 0.00090 0.0008 0.6346 0.5848
-0.750 -0.0864 0.00582 0.00088 0.0006 0.6290 0.5921
-0.500 -0.0576 0.00581 0.00087 0.0004 0.6231 0.5993
-0.250 -0.0288 0.00580 0.00086 0.0002 0.6174 0.6056
0.000 0.0000 0.00579 0.00086 0.0000 0.6119 0.6118
0.250 0.0289 0.00580 0.00086 -0.0002 0.6056 0.6173
0.500 0.0576 0.00581 0.00087 -0.0004 0.5992 0.6231
0.750 0.0865 0.00582 0.00088 -0.0006 0.5921 0.6290
1.000 0.1152 0.00584 0.00090 -0.0008 0.5848 0.6346
1.250 0.1440 0.00585 0.00093 -0.0010 0.5766 0.6409
1.500 0.1725 0.00590 0.00095 -0.0012 0.5606 0.6470
1.750 0.2003 0.00603 0.00098 -0.0012 0.5262 0.6538
2.000 0.2282 0.00617 0.00102 -0.0013 0.4926 0.6608
2.250 0.2558 0.00636 0.00109 -0.0014 0.4498 0.6675
2.500 0.2821 0.00677 0.00123 -0.0014 0.3684 0.6744
2.750 0.3081 0.00724 0.00144 -0.0014 0.2917 0.6809
3.000 0.3338 0.00777 0.00168 -0.0014 0.2109 0.6880
3.250 0.3599 0.00822 0.00190 -0.0013 0.1450 0.6947
3.500 0.3862 0.00862 0.00212 -0.0013 0.0964 0.7021
3.750 0.4127 0.00895 0.00233 -0.0013 0.0616 0.7092
4.000 0.4397 0.00919 0.00252 -0.0013 0.0450 0.7173
4.250 0.4669 0.00940 0.00271 -0.0013 0.0365 0.7249
4.500 0.4943 0.00956 0.00290 -0.0013 0.0328 0.7332
4.750 0.5214 0.00977 0.00311 -0.0013 0.0288 0.7406
5.000 0.5486 0.00994 0.00331 -0.0013 0.0265 0.7486
5.250 0.5756 0.01013 0.00353 -0.0013 0.0242 0.7560
5.500 0.6023 0.01037 0.00378 -0.0012 0.0217 0.7644
5.750 0.6291 0.01056 0.00402 -0.0011 0.0204 0.7726
6.000 0.6557 0.01078 0.00427 -0.0011 0.0190 0.7815
6.250 0.6819 0.01102 0.00455 -0.0009 0.0177 0.7899
6.750 0.7336 0.01157 0.00519 -0.0005 0.0157 0.8080
7.000 0.7593 0.01185 0.00551 -0.0003 0.0152 0.8168
7.250 0.7847 0.01213 0.00587 0.0000 0.0146 0.8268
7.500 0.8097 0.01243 0.00622 0.0003 0.0140 0.8366
7.750 0.8343 0.01276 0.00659 0.0007 0.0135 0.8468
8.000 0.8584 0.01312 0.00701 0.0011 0.0129 0.8581
8.250 0.8808 0.01362 0.00759 0.0019 0.0123 0.8699
8.500 0.9042 0.01396 0.00802 0.0025 0.0121 0.8823
8.750 0.9268 0.01434 0.00848 0.0032 0.0120 0.8959
9.000 0.9484 0.01474 0.00898 0.0041 0.0117 0.9117
9.250 0.9693 0.01516 0.00949 0.0051 0.0115 0.9297
9.500 0.9909 0.01559 0.01003 0.0059 0.0113 0.9536
9.750 1.0228 0.01614 0.01065 0.0044 0.0110 0.9903
10.000 1.0451 0.01664 0.01119 0.0049 0.0107 1.0000
10.250 1.0669 0.01715 0.01174 0.0055 0.0104 1.0000
10.500 1.0882 0.01767 0.01230 0.0061 0.0102 1.0000
10.750 1.1082 0.01828 0.01295 0.0069 0.0100 1.0000
11.000 1.1270 0.01896 0.01369 0.0079 0.0098 1.0000
11.250 1.1444 0.01970 0.01449 0.0089 0.0096 1.0000
11.500 1.1585 0.02065 0.01551 0.0104 0.0094 1.0000
11.750 1.1684 0.02168 0.01663 0.0125 0.0092 1.0000
12.000 1.1810 0.02235 0.01737 0.0143 0.0091 1.0000
12.250 1.1927 0.02310 0.01820 0.0160 0.0090 1.0000
12.500 1.2039 0.02395 0.01913 0.0176 0.0089 1.0000
12.750 1.2153 0.02483 0.02009 0.0189 0.0088 1.0000
13.000 1.2264 0.02578 0.02112 0.0202 0.0086 1.0000
13.250 1.2348 0.02698 0.02242 0.0215 0.0085 1.0000
13.500 1.2437 0.02819 0.02372 0.0226 0.0083 1.0000
13.750 1.2498 0.02970 0.02532 0.0236 0.0083 1.0000
14.000 1.2577 0.03110 0.02681 0.0244 0.0081 1.0000
14.250 1.2630 0.03279 0.02860 0.0251 0.0080 1.0000
14.500 1.2707 0.03431 0.03020 0.0256 0.0078 1.0000
14.750 1.2736 0.03637 0.03236 0.0260 0.0078 1.0000
15.000 1.2775 0.03841 0.03449 0.0262 0.0077 1.0000
15.250 1.2825 0.04039 0.03655 0.0262 0.0075 1.0000
15.500 1.2813 0.04314 0.03942 0.0259 0.0075 1.0000
15.750 1.2822 0.04576 0.04214 0.0255 0.0074 1.0000
16.000 1.2777 0.04914 0.04564 0.0247 0.0073 1.0000
16.250 1.2775 0.05213 0.04871 0.0237 0.0072 1.0000
16.500 1.2705 0.05614 0.05283 0.0223 0.0072 1.0000
16.750 1.2649 0.06020 0.05699 0.0205 0.0071 1.0000
17.000 1.2488 0.06610 0.06306 0.0177 0.0071 1.0000
17.250 1.2429 0.07074 0.06778 0.0152 0.0070 1.0000
17.500 1.2204 0.07855 0.07576 0.0107 0.0070 1.0000
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Polar data table (+)
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