NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.64 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca641112-il-1000000.txt Download as CSV file: xf-naca641112-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9869 0.06895 0.06664 -0.0296 1.0000 0.0098
-14.750 -1.0109 0.06150 0.05902 -0.0341 1.0000 0.0099
-14.500 -1.0311 0.05531 0.05265 -0.0374 1.0000 0.0099
-14.250 -1.0418 0.05095 0.04816 -0.0393 1.0000 0.0099
-14.000 -1.0334 0.04931 0.04652 -0.0401 1.0000 0.0101
-13.750 -1.0585 0.04361 0.04056 -0.0415 1.0000 0.0101
-13.500 -1.0612 0.04096 0.03781 -0.0418 1.0000 0.0102
-13.250 -1.0674 0.03805 0.03473 -0.0416 1.0000 0.0102
-13.000 -1.0670 0.03606 0.03263 -0.0411 1.0000 0.0104
-12.750 -1.0645 0.03441 0.03089 -0.0402 1.0000 0.0106
-12.500 -1.0618 0.03284 0.02922 -0.0391 1.0000 0.0108
-12.250 -1.0628 0.03092 0.02714 -0.0373 1.0000 0.0109
-12.000 -1.0600 0.02951 0.02561 -0.0353 1.0000 0.0111
-11.750 -1.0572 0.02815 0.02412 -0.0329 1.0000 0.0113
-11.500 -1.0488 0.02693 0.02277 -0.0309 1.0000 0.0115
-11.250 -1.0355 0.02589 0.02160 -0.0296 1.0000 0.0117
-11.000 -1.0197 0.02503 0.02063 -0.0285 1.0000 0.0119
-10.750 -1.0018 0.02437 0.01987 -0.0276 1.0000 0.0121
-10.500 -0.9910 0.02205 0.01731 -0.0261 1.0000 0.0124
-10.250 -0.9766 0.02035 0.01548 -0.0248 1.0000 0.0128
-10.000 -0.9572 0.01950 0.01459 -0.0240 1.0000 0.0131
-9.750 -0.9363 0.01886 0.01391 -0.0234 1.0000 0.0135
-9.500 -0.9150 0.01821 0.01320 -0.0228 1.0000 0.0138
-9.250 -0.8933 0.01756 0.01250 -0.0222 1.0000 0.0142
-9.000 -0.8716 0.01689 0.01177 -0.0215 1.0000 0.0146
-8.750 -0.8492 0.01636 0.01120 -0.0210 1.0000 0.0150
-8.500 -0.8197 0.01584 0.01063 -0.0219 0.9888 0.0155
-8.250 -0.7843 0.01531 0.01002 -0.0239 0.9752 0.0158
-8.000 -0.7575 0.01390 0.00849 -0.0247 0.9573 0.0165
-7.750 -0.7353 0.01330 0.00782 -0.0239 0.9390 0.0171
-7.500 -0.7128 0.01291 0.00737 -0.0231 0.9236 0.0177
-7.250 -0.6898 0.01255 0.00694 -0.0223 0.9101 0.0183
-6.750 -0.6412 0.01192 0.00617 -0.0213 0.8865 0.0198
-6.500 -0.6156 0.01170 0.00590 -0.0209 0.8762 0.0203
-6.250 -0.5933 0.01099 0.00507 -0.0202 0.8658 0.0218
-6.000 -0.5677 0.01067 0.00472 -0.0199 0.8558 0.0232
-5.750 -0.5416 0.01041 0.00442 -0.0197 0.8469 0.0245
-5.500 -0.5151 0.01022 0.00416 -0.0195 0.8379 0.0258
-5.250 -0.4894 0.00979 0.00369 -0.0193 0.8289 0.0287
-5.000 -0.4628 0.00958 0.00344 -0.0191 0.8203 0.0317
-4.750 -0.4359 0.00934 0.00316 -0.0191 0.8113 0.0350
-4.500 -0.4091 0.00909 0.00289 -0.0190 0.8031 0.0406
-4.250 -0.3821 0.00883 0.00265 -0.0189 0.7946 0.0501
-4.000 -0.3555 0.00849 0.00240 -0.0189 0.7867 0.0785
-3.750 -0.3301 0.00793 0.00212 -0.0188 0.7783 0.1476
-3.500 -0.3055 0.00716 0.00178 -0.0188 0.7703 0.2632
-3.250 -0.2817 0.00625 0.00145 -0.0187 0.7620 0.4197
-3.000 -0.2546 0.00595 0.00135 -0.0187 0.7539 0.4860
-2.750 -0.2267 0.00584 0.00127 -0.0188 0.7458 0.5172
-2.500 -0.1983 0.00576 0.00122 -0.0189 0.7379 0.5366
-2.000 -0.1414 0.00567 0.00113 -0.0192 0.7226 0.5687
-1.500 -0.0846 0.00559 0.00110 -0.0194 0.7078 0.6086
-1.250 -0.0562 0.00559 0.00109 -0.0195 0.7004 0.6240
-1.000 -0.0275 0.00556 0.00108 -0.0197 0.6930 0.6332
-0.500 0.0299 0.00555 0.00105 -0.0200 0.6786 0.6488
0.000 0.0874 0.00556 0.00105 -0.0204 0.6653 0.6631
0.250 0.1163 0.00558 0.00106 -0.0206 0.6585 0.6702
0.500 0.1449 0.00558 0.00107 -0.0208 0.6517 0.6769
0.750 0.1737 0.00560 0.00108 -0.0210 0.6439 0.6843
1.000 0.2023 0.00562 0.00111 -0.0211 0.6365 0.6914
1.250 0.2310 0.00563 0.00114 -0.0213 0.6289 0.6993
1.500 0.2596 0.00565 0.00117 -0.0214 0.6204 0.7068
1.750 0.2879 0.00570 0.00120 -0.0215 0.6073 0.7148
2.000 0.3161 0.00573 0.00122 -0.0216 0.5870 0.7222
2.250 0.3443 0.00580 0.00126 -0.0217 0.5696 0.7303
2.500 0.3724 0.00586 0.00131 -0.0217 0.5528 0.7379
2.750 0.4007 0.00593 0.00138 -0.0219 0.5390 0.7461
3.000 0.4287 0.00600 0.00146 -0.0219 0.5217 0.7540
3.250 0.4566 0.00613 0.00154 -0.0220 0.4986 0.7626
3.500 0.4836 0.00631 0.00166 -0.0219 0.4615 0.7709
3.750 0.5071 0.00701 0.00191 -0.0215 0.3467 0.7795
4.000 0.5285 0.00798 0.00235 -0.0209 0.2146 0.7880
4.250 0.5518 0.00870 0.00272 -0.0205 0.1285 0.7965
4.500 0.5761 0.00926 0.00306 -0.0201 0.0735 0.8053
4.750 0.6012 0.00968 0.00336 -0.0199 0.0468 0.8139
5.000 0.6274 0.00996 0.00363 -0.0197 0.0388 0.8233
5.250 0.6532 0.01024 0.00395 -0.0194 0.0337 0.8325
5.500 0.6792 0.01049 0.00422 -0.0192 0.0306 0.8420
5.750 0.7039 0.01089 0.00467 -0.0187 0.0269 0.8520
6.000 0.7296 0.01111 0.00494 -0.0184 0.0253 0.8618
6.250 0.7547 0.01138 0.00525 -0.0180 0.0234 0.8724
6.500 0.7771 0.01195 0.00588 -0.0172 0.0211 0.8844
6.750 0.8014 0.01219 0.00620 -0.0166 0.0204 0.8966
7.000 0.8247 0.01248 0.00655 -0.0158 0.0194 0.9099
7.250 0.8470 0.01279 0.00693 -0.0149 0.0186 0.9251
7.750 0.8901 0.01369 0.00797 -0.0129 0.0170 0.9711
8.000 0.9159 0.01465 0.00901 -0.0133 0.0163 1.0000
8.250 0.9398 0.01512 0.00953 -0.0129 0.0160 1.0000
8.500 0.9635 0.01559 0.01003 -0.0125 0.0155 1.0000
8.750 0.9864 0.01611 0.01059 -0.0120 0.0150 1.0000
9.000 1.0082 0.01671 0.01123 -0.0114 0.0146 1.0000
9.250 1.0304 0.01724 0.01179 -0.0108 0.0141 1.0000
9.500 1.0511 0.01788 0.01247 -0.0101 0.0138 1.0000
9.750 1.0709 0.01857 0.01319 -0.0092 0.0134 1.0000
10.000 1.0874 0.01964 0.01432 -0.0079 0.0131 1.0000
10.250 1.0973 0.02189 0.01672 -0.0060 0.0126 1.0000
10.500 1.1159 0.02260 0.01751 -0.0050 0.0125 1.0000
10.750 1.1329 0.02346 0.01847 -0.0038 0.0124 1.0000
11.000 1.1479 0.02411 0.01920 -0.0023 0.0121 1.0000
11.250 1.1605 0.02486 0.02003 -0.0005 0.0119 1.0000
11.500 1.1712 0.02588 0.02115 0.0014 0.0117 1.0000
11.750 1.1809 0.02697 0.02234 0.0033 0.0115 1.0000
12.000 1.1893 0.02822 0.02369 0.0050 0.0113 1.0000
12.250 1.1970 0.02950 0.02508 0.0066 0.0111 1.0000
12.500 1.2041 0.03080 0.02649 0.0081 0.0109 1.0000
12.750 1.2099 0.03228 0.02807 0.0094 0.0107 1.0000
13.000 1.2138 0.03402 0.02992 0.0107 0.0106 1.0000
13.250 1.2215 0.03520 0.03115 0.0115 0.0104 1.0000
13.500 1.2212 0.03754 0.03364 0.0125 0.0103 1.0000
13.750 1.2230 0.03961 0.03580 0.0131 0.0102 1.0000
14.000 1.2229 0.04194 0.03821 0.0134 0.0100 1.0000
14.250 1.2180 0.04505 0.04147 0.0136 0.0100 1.0000
14.500 1.2080 0.04887 0.04544 0.0133 0.0098 1.0000
14.750 1.1968 0.05308 0.04982 0.0125 0.0098 1.0000
15.000 1.1679 0.05995 0.05694 0.0105 0.0097 1.0000
15.250 1.1556 0.06492 0.06206 0.0084 0.0097 1.0000
15.500 1.1370 0.07132 0.06863 0.0053 0.0097 1.0000
15.750 1.1074 0.08024 0.07778 0.0003 0.0096 1.0000
16.000 1.0926 0.08729 0.08496 -0.0040 0.0097 1.0000
16.250 1.0633 0.09816 0.09602 -0.0111 0.0097 1.0000
16.500 1.0447 0.10765 0.10565 -0.0173 0.0097 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(1)-112 (naca641112-il)