NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.26 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212-il-1000000-n5.txt Download as CSV file: xf-n64212-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
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
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0838 0.07549 0.07302 -0.0346 1.0000 0.0069
-16.750 -1.1188 0.06527 0.06258 -0.0411 1.0000 0.0069
-16.500 -1.1337 0.05934 0.05653 -0.0446 1.0000 0.0070
-16.250 -1.1437 0.05454 0.05160 -0.0472 1.0000 0.0070
-16.000 -1.1539 0.05002 0.04696 -0.0494 1.0000 0.0071
-15.750 -1.1648 0.04568 0.04246 -0.0513 1.0000 0.0071
-15.500 -1.1670 0.04261 0.03929 -0.0523 1.0000 0.0071
-15.250 -1.1652 0.04012 0.03671 -0.0530 1.0000 0.0073
-15.000 -1.1670 0.03737 0.03384 -0.0534 1.0000 0.0073
-14.750 -1.1634 0.03530 0.03167 -0.0536 1.0000 0.0075
-14.500 -1.1603 0.03327 0.02954 -0.0535 1.0000 0.0076
-14.250 -1.1584 0.03124 0.02739 -0.0531 1.0000 0.0077
-14.000 -1.1532 0.02961 0.02566 -0.0525 1.0000 0.0078
-13.750 -1.1452 0.02829 0.02425 -0.0518 1.0000 0.0080
-13.500 -1.1403 0.02679 0.02264 -0.0507 1.0000 0.0080
-13.250 -1.1327 0.02560 0.02135 -0.0494 1.0000 0.0082
-13.000 -1.1242 0.02459 0.02025 -0.0480 1.0000 0.0083
-12.750 -1.1156 0.02370 0.01927 -0.0461 1.0000 0.0084
-12.500 -1.1060 0.02289 0.01837 -0.0442 1.0000 0.0085
-12.250 -1.0922 0.02202 0.01741 -0.0429 1.0000 0.0086
-12.000 -1.0789 0.02102 0.01633 -0.0416 1.0000 0.0090
-11.750 -1.0620 0.02027 0.01552 -0.0406 1.0000 0.0092
-11.500 -1.0432 0.01964 0.01485 -0.0398 1.0000 0.0094
-11.250 -1.0242 0.01899 0.01414 -0.0389 1.0000 0.0096
-11.000 -1.0042 0.01841 0.01351 -0.0382 1.0000 0.0098
-10.750 -0.9841 0.01781 0.01285 -0.0374 1.0000 0.0100
-10.500 -0.9592 0.01724 0.01222 -0.0376 0.9909 0.0103
-10.000 -0.8925 0.01597 0.01079 -0.0414 0.9591 0.0109
-9.750 -0.8651 0.01551 0.01023 -0.0419 0.9410 0.0111
-9.500 -0.8415 0.01512 0.00975 -0.0414 0.9237 0.0113
-9.250 -0.8201 0.01456 0.00907 -0.0406 0.9083 0.0116
-9.000 -0.7981 0.01403 0.00845 -0.0399 0.8945 0.0120
-8.750 -0.7748 0.01360 0.00795 -0.0394 0.8826 0.0123
-8.500 -0.7509 0.01324 0.00752 -0.0389 0.8712 0.0127
-8.250 -0.7263 0.01290 0.00711 -0.0386 0.8604 0.0130
-8.000 -0.7013 0.01258 0.00673 -0.0383 0.8503 0.0134
-7.750 -0.6762 0.01228 0.00635 -0.0380 0.8406 0.0138
-7.500 -0.6508 0.01196 0.00596 -0.0378 0.8307 0.0142
-7.250 -0.6252 0.01165 0.00559 -0.0376 0.8217 0.0145
-7.000 -0.5992 0.01138 0.00523 -0.0374 0.8123 0.0148
-6.750 -0.5735 0.01101 0.00481 -0.0372 0.8036 0.0156
-6.500 -0.5474 0.01073 0.00449 -0.0371 0.7950 0.0163
-6.250 -0.5207 0.01049 0.00422 -0.0371 0.7864 0.0172
-6.000 -0.4938 0.01028 0.00397 -0.0370 0.7787 0.0183
-5.750 -0.4667 0.01008 0.00372 -0.0370 0.7705 0.0191
-5.500 -0.4398 0.00984 0.00345 -0.0370 0.7625 0.0206
-5.250 -0.4126 0.00964 0.00322 -0.0370 0.7540 0.0223
-5.000 -0.3851 0.00947 0.00302 -0.0371 0.7464 0.0239
-4.750 -0.3575 0.00931 0.00282 -0.0371 0.7386 0.0254
-4.500 -0.3300 0.00913 0.00261 -0.0372 0.7316 0.0283
-4.250 -0.3022 0.00897 0.00244 -0.0373 0.7241 0.0309
-4.000 -0.2744 0.00884 0.00228 -0.0374 0.7171 0.0342
-3.750 -0.2466 0.00867 0.00212 -0.0375 0.7095 0.0399
-3.500 -0.2189 0.00851 0.00197 -0.0376 0.7022 0.0508
-3.250 -0.1912 0.00827 0.00181 -0.0377 0.6945 0.0743
-3.000 -0.1638 0.00798 0.00164 -0.0379 0.6876 0.1143
-2.750 -0.1365 0.00761 0.00147 -0.0381 0.6808 0.1735
-2.500 -0.1093 0.00722 0.00129 -0.0383 0.6741 0.2447
-2.250 -0.0824 0.00666 0.00110 -0.0386 0.6679 0.3488
-2.000 -0.0551 0.00626 0.00098 -0.0388 0.6612 0.4391
-1.750 -0.0269 0.00611 0.00093 -0.0390 0.6552 0.4818
-1.500 0.0014 0.00597 0.00091 -0.0392 0.6487 0.5217
-1.250 0.0295 0.00586 0.00090 -0.0393 0.6423 0.5627
-1.000 0.0582 0.00582 0.00090 -0.0395 0.6359 0.5811
-0.750 0.0869 0.00582 0.00089 -0.0397 0.6296 0.5891
-0.500 0.1158 0.00582 0.00088 -0.0399 0.6242 0.5971
-0.250 0.1446 0.00582 0.00088 -0.0401 0.6185 0.6039
0.000 0.1733 0.00584 0.00089 -0.0403 0.6130 0.6102
0.250 0.2023 0.00585 0.00090 -0.0406 0.6079 0.6157
0.500 0.2310 0.00586 0.00092 -0.0408 0.6019 0.6214
0.750 0.2597 0.00589 0.00094 -0.0409 0.5954 0.6274
1.000 0.2885 0.00591 0.00097 -0.0411 0.5878 0.6331
1.250 0.3170 0.00594 0.00100 -0.0413 0.5808 0.6396
1.500 0.3458 0.00598 0.00104 -0.0415 0.5726 0.6463
1.750 0.3741 0.00603 0.00109 -0.0416 0.5595 0.6532
2.000 0.4018 0.00615 0.00114 -0.0416 0.5355 0.6601
2.250 0.4290 0.00632 0.00120 -0.0416 0.4986 0.6666
2.500 0.4564 0.00649 0.00129 -0.0416 0.4681 0.6737
2.750 0.4826 0.00682 0.00142 -0.0415 0.4108 0.6802
3.000 0.5072 0.00735 0.00165 -0.0412 0.3337 0.6876
3.250 0.5318 0.00791 0.00193 -0.0409 0.2592 0.6944
3.500 0.5557 0.00852 0.00224 -0.0406 0.1815 0.7022
3.750 0.5806 0.00902 0.00252 -0.0403 0.1252 0.7099
4.000 0.6056 0.00947 0.00279 -0.0400 0.0809 0.7183
4.250 0.6313 0.00983 0.00305 -0.0399 0.0535 0.7259
4.500 0.6577 0.01008 0.00327 -0.0397 0.0415 0.7339
4.750 0.6842 0.01032 0.00350 -0.0396 0.0344 0.7415
5.000 0.7108 0.01053 0.00373 -0.0395 0.0305 0.7497
5.250 0.7372 0.01076 0.00397 -0.0394 0.0271 0.7576
5.500 0.7637 0.01095 0.00420 -0.0393 0.0252 0.7666
5.750 0.7897 0.01120 0.00446 -0.0391 0.0227 0.7753
6.000 0.8156 0.01145 0.00475 -0.0389 0.0206 0.7845
6.250 0.8415 0.01168 0.00502 -0.0387 0.0189 0.7931
6.500 0.8669 0.01197 0.00532 -0.0384 0.0170 0.8022
6.750 0.8919 0.01226 0.00566 -0.0381 0.0157 0.8120
7.000 0.9170 0.01253 0.00598 -0.0378 0.0147 0.8217
7.500 0.9656 0.01318 0.00670 -0.0369 0.0130 0.8429
7.750 0.9886 0.01358 0.00717 -0.0362 0.0123 0.8540
8.000 1.0120 0.01392 0.00758 -0.0356 0.0121 0.8659
8.250 1.0347 0.01427 0.00801 -0.0349 0.0118 0.8794
8.500 1.0565 0.01465 0.00846 -0.0339 0.0116 0.8944
8.750 1.0770 0.01503 0.00893 -0.0328 0.0113 0.9122
9.000 1.0964 0.01540 0.00940 -0.0315 0.0111 0.9338
9.250 1.1180 0.01580 0.00989 -0.0306 0.0109 0.9717
9.500 1.1410 0.01630 0.01044 -0.0302 0.0107 1.0000
9.750 1.1623 0.01681 0.01098 -0.0295 0.0104 1.0000
10.000 1.1825 0.01737 0.01158 -0.0286 0.0102 1.0000
10.250 1.2019 0.01795 0.01220 -0.0277 0.0099 1.0000
10.500 1.2194 0.01864 0.01293 -0.0264 0.0097 1.0000
10.750 1.2326 0.01952 0.01388 -0.0246 0.0094 1.0000
11.000 1.2445 0.02029 0.01471 -0.0225 0.0093 1.0000
11.250 1.2574 0.02098 0.01546 -0.0206 0.0092 1.0000
11.500 1.2702 0.02171 0.01626 -0.0188 0.0091 1.0000
11.750 1.2818 0.02254 0.01716 -0.0171 0.0091 1.0000
12.000 1.2936 0.02340 0.01811 -0.0155 0.0089 1.0000
12.250 1.3044 0.02438 0.01916 -0.0139 0.0088 1.0000
12.500 1.3166 0.02528 0.02013 -0.0126 0.0087 1.0000
12.750 1.3254 0.02648 0.02142 -0.0111 0.0086 1.0000
13.000 1.3362 0.02757 0.02258 -0.0100 0.0084 1.0000
13.250 1.3453 0.02883 0.02391 -0.0088 0.0083 1.0000
13.500 1.3532 0.03023 0.02541 -0.0077 0.0082 1.0000
13.750 1.3609 0.03172 0.02698 -0.0067 0.0081 1.0000
14.000 1.3677 0.03331 0.02865 -0.0058 0.0080 1.0000
14.250 1.3740 0.03501 0.03045 -0.0051 0.0079 1.0000
14.500 1.3796 0.03683 0.03236 -0.0045 0.0077 1.0000
14.750 1.3843 0.03880 0.03442 -0.0040 0.0077 1.0000
15.000 1.3866 0.04111 0.03683 -0.0037 0.0076 1.0000
15.250 1.3899 0.04336 0.03917 -0.0035 0.0075 1.0000
15.500 1.3912 0.04592 0.04182 -0.0036 0.0074 1.0000
15.750 1.3925 0.04857 0.04456 -0.0038 0.0073 1.0000
16.000 1.3895 0.05183 0.04793 -0.0043 0.0072 1.0000
16.250 1.3857 0.05535 0.05157 -0.0050 0.0072 1.0000
16.500 1.3796 0.05936 0.05569 -0.0062 0.0071 1.0000
16.750 1.3693 0.06416 0.06062 -0.0078 0.0070 1.0000
17.000 1.3597 0.06914 0.06573 -0.0098 0.0069 1.0000
17.250 1.3451 0.07515 0.07189 -0.0125 0.0068 1.0000
17.500 1.3285 0.08185 0.07876 -0.0157 0.0068 1.0000
17.750 1.3151 0.08842 0.08547 -0.0192 0.0068 1.0000
18.000 1.3049 0.09469 0.09186 -0.0227 0.0068 1.0000
18.250 1.2828 0.10366 0.10101 -0.0280 0.0068 1.0000
18.500 1.2592 0.11345 0.11096 -0.0339 0.0068 1.0000
18.750 1.2312 0.12465 0.12233 -0.0407 0.0068 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(1)-212 (n64212-il)