NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 200,000 Max Cl/Cd: 55.4 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662415-il-200000.txt Download as CSV file: xf-naca662415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3838 0.12148 0.11790 -0.0642 0.9891 0.0557
-12.250 -0.3782 0.11627 0.11269 -0.0691 0.9866 0.0585
-12.000 -0.4014 0.10507 0.10153 -0.0850 0.9836 0.0610
-11.500 -0.3747 0.09827 0.09472 -0.0845 0.9781 0.0637
-11.250 -0.3608 0.09498 0.09141 -0.0868 0.9757 0.0655
-11.000 -0.3539 0.08983 0.08624 -0.0918 0.9736 0.0680
-10.750 -0.3677 0.07903 0.07542 -0.1049 0.9711 0.0709
-10.500 -0.4034 0.07132 0.06753 -0.1129 0.9627 0.0720
-10.250 -0.4391 0.06759 0.06348 -0.1160 0.9544 0.0729
-10.000 -0.4659 0.06659 0.06213 -0.1135 0.9449 0.0734
-9.500 -0.4275 0.05616 0.05191 -0.1173 0.9413 0.0787
-9.250 -0.4353 0.05464 0.05028 -0.1141 0.9334 0.0810
-9.000 -0.4653 0.05660 0.05161 -0.1076 0.9246 0.0869
-8.750 -0.4706 0.05116 0.04617 -0.1055 0.9189 0.0891
-7.000 -0.4253 0.03152 0.02407 -0.0839 0.8904 0.0540
-6.750 -0.4102 0.02998 0.02210 -0.0813 0.8868 0.0521
-6.500 -0.3829 0.02853 0.02044 -0.0813 0.8849 0.0520
-6.250 -0.3530 0.02716 0.01895 -0.0819 0.8837 0.0524
-6.000 -0.3229 0.02612 0.01788 -0.0826 0.8826 0.0541
-5.750 -0.2924 0.02531 0.01702 -0.0834 0.8816 0.0564
-5.500 -0.3259 0.02627 0.01797 -0.0725 0.8739 0.0562
-5.250 -0.3141 0.02589 0.01753 -0.0698 0.8708 0.0571
-5.000 -0.2893 0.02526 0.01686 -0.0694 0.8689 0.0586
-4.750 -0.2636 0.02475 0.01630 -0.0692 0.8675 0.0602
-4.500 -0.2391 0.02406 0.01561 -0.0690 0.8663 0.0628
-4.250 -0.2139 0.02347 0.01509 -0.0690 0.8653 0.0669
-4.000 -0.2545 0.02453 0.01611 -0.0571 0.8582 0.0660
-3.750 -0.2447 0.02448 0.01606 -0.0543 0.8557 0.0685
-3.500 -0.2272 0.02432 0.01587 -0.0529 0.8538 0.0720
-3.250 -0.2036 0.02388 0.01543 -0.0526 0.8520 0.0789
-3.000 -0.1768 0.02351 0.01510 -0.0529 0.8507 0.0930
-2.750 -0.1655 0.02086 0.01437 -0.0520 0.8495 0.4853
-2.500 -0.1770 0.02131 0.01571 -0.0443 0.8452 0.7026
-2.250 -0.1717 0.02211 0.01652 -0.0399 0.8415 0.7460
-2.000 -0.1580 0.02294 0.01738 -0.0363 0.8387 0.7741
-1.750 -0.1415 0.02382 0.01828 -0.0326 0.8364 0.7996
-1.500 -0.1259 0.02482 0.01932 -0.0279 0.8344 0.8236
-1.250 -0.1051 0.02563 0.02010 -0.0247 0.8330 0.8445
-1.000 -0.1275 0.02621 0.02072 -0.0158 0.8258 0.8520
-0.750 -0.1130 0.02655 0.02102 -0.0128 0.8225 0.8638
-0.500 -0.0912 0.02685 0.02127 -0.0108 0.8200 0.8767
-0.250 -0.0649 0.02714 0.02152 -0.0092 0.8182 0.8866
0.000 -0.0690 0.02733 0.02170 -0.0044 0.8112 0.8937
0.250 -0.0474 0.02739 0.02171 -0.0035 0.8072 0.8978
0.500 -0.0144 0.02738 0.02164 -0.0049 0.8046 0.8999
0.750 0.0239 0.02735 0.02155 -0.0072 0.8028 0.9015
1.000 0.0623 0.02737 0.02152 -0.0095 0.8011 0.9026
1.250 0.0563 0.02760 0.02175 -0.0051 0.7911 0.9072
1.500 0.0922 0.02752 0.02164 -0.0068 0.7886 0.9085
1.750 0.1311 0.02746 0.02156 -0.0090 0.7869 0.9095
2.000 0.1332 0.02777 0.02188 -0.0056 0.7774 0.9131
2.250 0.1667 0.02773 0.02183 -0.0070 0.7743 0.9148
2.500 0.2053 0.02762 0.02172 -0.0091 0.7722 0.9165
2.750 0.2464 0.02748 0.02159 -0.0116 0.7708 0.9180
3.000 0.2492 0.02782 0.02195 -0.0085 0.7596 0.9220
3.250 0.2871 0.02760 0.02176 -0.0103 0.7573 0.9234
3.500 0.3285 0.02732 0.02151 -0.0125 0.7558 0.9246
3.750 0.3347 0.02761 0.02185 -0.0097 0.7445 0.9290
4.000 0.3750 0.02724 0.02153 -0.0118 0.7422 0.9307
4.250 0.4182 0.02676 0.02110 -0.0142 0.7406 0.9323
4.500 0.4265 0.02703 0.02143 -0.0116 0.7293 0.9372
4.750 0.4673 0.02644 0.02092 -0.0135 0.7270 0.9392
5.000 0.5156 0.02545 0.02003 -0.0161 0.7256 0.9406
5.250 0.5802 0.02316 0.01784 -0.0202 0.7234 0.9400
5.500 0.6124 0.02187 0.01665 -0.0199 0.7130 0.9432
5.750 0.7135 0.01730 0.01217 -0.0284 0.7055 0.9385
6.000 0.7392 0.01622 0.01116 -0.0271 0.6897 0.9423
6.250 0.7480 0.01589 0.01091 -0.0235 0.6716 0.9487
6.500 0.7599 0.01558 0.01069 -0.0205 0.6441 0.9550
6.750 0.7950 0.01435 0.00879 -0.0198 0.5150 0.9578
7.000 0.7812 0.01582 0.00952 -0.0137 0.3923 0.9682
7.250 0.7642 0.01852 0.01132 -0.0094 0.2375 0.9798
7.500 0.7570 0.02140 0.01321 -0.0071 0.0927 0.9918
7.750 0.7647 0.02264 0.01432 -0.0054 0.0733 1.0000
8.000 0.7768 0.02362 0.01529 -0.0043 0.0655 1.0000
8.250 0.7901 0.02472 0.01641 -0.0035 0.0603 1.0000
8.500 0.8058 0.02577 0.01748 -0.0029 0.0563 1.0000
8.750 0.8183 0.02716 0.01882 -0.0021 0.0530 1.0000
9.000 0.8374 0.02817 0.01989 -0.0018 0.0502 1.0000
9.250 0.8578 0.02916 0.02090 -0.0016 0.0474 1.0000
9.500 0.8801 0.03020 0.02192 -0.0016 0.0455 1.0000
9.750 0.9207 0.03164 0.02322 -0.0029 0.0432 1.0000
10.000 0.9482 0.03260 0.02432 -0.0033 0.0419 1.0000
10.250 0.9762 0.03368 0.02553 -0.0039 0.0399 1.0000
10.500 1.0120 0.03509 0.02704 -0.0051 0.0388 1.0000
10.750 1.0509 0.03691 0.02900 -0.0068 0.0380 1.0000
11.000 1.0876 0.03915 0.03144 -0.0083 0.0375 1.0000
11.250 1.1164 0.04196 0.03459 -0.0089 0.0377 1.0000
11.500 1.1339 0.04534 0.03841 -0.0081 0.0383 1.0000
11.750 1.1434 0.04827 0.04166 -0.0066 0.0383 1.0000
12.000 1.1436 0.05205 0.04584 -0.0041 0.0393 1.0000
12.250 1.1413 0.05636 0.05049 -0.0017 0.0409 1.0000
12.500 1.0426 0.06010 0.05521 0.0085 0.0519 1.0000
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Polar data table (+)
Polar graphs
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