NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 100,000 Max Cl/Cd: 46.59 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415-il-100000-n5.txt Download as CSV file: xf-naca652415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4497 0.09622 0.09092 -0.0627 1.0000 0.0367
-11.750 -0.4717 0.08626 0.08101 -0.0684 1.0000 0.0359
-11.500 -0.5099 0.07613 0.07085 -0.0746 1.0000 0.0351
-11.250 -0.5457 0.06961 0.06425 -0.0772 1.0000 0.0347
-11.000 -0.5793 0.06522 0.05980 -0.0770 1.0000 0.0344
-10.750 -0.6134 0.06262 0.05716 -0.0739 1.0000 0.0342
-10.500 -0.6390 0.05946 0.05385 -0.0728 0.9939 0.0340
-10.250 -0.6457 0.05522 0.04928 -0.0752 0.9803 0.0341
-10.000 -0.6396 0.05164 0.04540 -0.0772 0.9701 0.0349
-9.750 -0.6301 0.04812 0.04149 -0.0790 0.9620 0.0358
-9.500 -0.6208 0.04492 0.03786 -0.0795 0.9526 0.0368
-9.250 -0.6039 0.04161 0.03404 -0.0807 0.9467 0.0376
-9.000 -0.5905 0.03902 0.03100 -0.0801 0.9373 0.0381
-8.750 -0.5671 0.03651 0.02799 -0.0810 0.9321 0.0388
-8.500 -0.5478 0.03460 0.02587 -0.0807 0.9240 0.0400
-8.250 -0.5218 0.03309 0.02425 -0.0815 0.9185 0.0415
-8.000 -0.4942 0.03153 0.02248 -0.0822 0.9136 0.0428
-7.750 -0.4710 0.03014 0.02091 -0.0818 0.9063 0.0438
-7.500 -0.4414 0.02871 0.01928 -0.0824 0.9016 0.0451
-7.250 -0.4143 0.02761 0.01798 -0.0825 0.8960 0.0468
-7.000 -0.3900 0.02653 0.01685 -0.0822 0.8893 0.0488
-6.750 -0.3625 0.02552 0.01585 -0.0826 0.8847 0.0508
-6.500 -0.3400 0.02472 0.01501 -0.0819 0.8783 0.0525
-6.250 -0.3175 0.02396 0.01418 -0.0812 0.8719 0.0546
-6.000 -0.2920 0.02324 0.01334 -0.0811 0.8673 0.0573
-5.750 -0.2761 0.02260 0.01275 -0.0795 0.8595 0.0608
-5.500 -0.2543 0.02201 0.01211 -0.0788 0.8541 0.0654
-5.250 -0.2320 0.02138 0.01140 -0.0782 0.8493 0.0704
-5.000 -0.2145 0.02090 0.01090 -0.0768 0.8419 0.0783
-4.750 -0.1925 0.02024 0.01028 -0.0762 0.8370 0.0950
-4.500 -0.1749 0.01932 0.00969 -0.0752 0.8315 0.1489
-4.250 -0.1667 0.01774 0.00909 -0.0734 0.8246 0.3376
-4.000 -0.1495 0.01721 0.00945 -0.0712 0.8203 0.5381
-3.750 -0.1255 0.01739 0.00963 -0.0701 0.8157 0.5928
-3.500 -0.1053 0.01792 0.01021 -0.0678 0.8096 0.6419
-3.250 -0.0838 0.01884 0.01117 -0.0647 0.8054 0.6856
-3.000 -0.0583 0.01939 0.01167 -0.0628 0.8024 0.7055
-2.750 -0.0368 0.01942 0.01157 -0.0620 0.7963 0.7151
-2.500 -0.0116 0.01947 0.01153 -0.0613 0.7916 0.7199
-2.250 0.0164 0.01940 0.01133 -0.0614 0.7881 0.7250
-2.000 0.0448 0.01924 0.01102 -0.0619 0.7847 0.7314
-1.750 0.0659 0.01935 0.01109 -0.0610 0.7788 0.7355
-1.500 0.0920 0.01934 0.01101 -0.0608 0.7747 0.7396
-1.250 0.1209 0.01924 0.01080 -0.0612 0.7715 0.7446
-1.000 0.1479 0.01918 0.01065 -0.0615 0.7676 0.7499
-0.750 0.1692 0.01933 0.01080 -0.0605 0.7622 0.7536
-0.500 0.1956 0.01934 0.01076 -0.0605 0.7584 0.7579
-0.250 0.2250 0.01927 0.01062 -0.0611 0.7554 0.7632
0.000 0.2515 0.01929 0.01061 -0.0611 0.7518 0.7676
0.250 0.2717 0.01949 0.01084 -0.0600 0.7462 0.7716
0.500 0.2979 0.01955 0.01088 -0.0600 0.7425 0.7764
0.750 0.3279 0.01951 0.01081 -0.0608 0.7397 0.7822
1.000 0.3549 0.01955 0.01085 -0.0606 0.7367 0.7858
1.250 0.3725 0.01987 0.01124 -0.0593 0.7305 0.7906
1.500 0.3987 0.01997 0.01135 -0.0594 0.7268 0.7964
1.750 0.4270 0.01999 0.01139 -0.0596 0.7239 0.8011
2.000 0.4566 0.01997 0.01140 -0.0599 0.7216 0.8055
2.250 0.4710 0.02046 0.01197 -0.0583 0.7147 0.8119
2.500 0.4958 0.02059 0.01216 -0.0580 0.7107 0.8172
2.750 0.5234 0.02062 0.01225 -0.0579 0.7078 0.8223
3.000 0.5542 0.02062 0.01228 -0.0585 0.7054 0.8284
3.250 0.5644 0.02122 0.01302 -0.0562 0.6977 0.8349
3.500 0.5901 0.02132 0.01320 -0.0559 0.6938 0.8409
3.750 0.6214 0.02128 0.01323 -0.0566 0.6909 0.8474
4.000 0.6347 0.02172 0.01380 -0.0544 0.6839 0.8544
4.250 0.6592 0.02184 0.01402 -0.0540 0.6786 0.8623
4.500 0.6898 0.02166 0.01394 -0.0541 0.6751 0.8682
4.750 0.7034 0.02209 0.01451 -0.0521 0.6671 0.8774
5.000 0.7290 0.02200 0.01455 -0.0515 0.6616 0.8849
5.250 0.7591 0.02177 0.01443 -0.0515 0.6561 0.8935
5.500 0.7751 0.02182 0.01464 -0.0494 0.6463 0.9040
5.750 0.7992 0.02156 0.01453 -0.0483 0.6369 0.9142
6.000 0.8275 0.02084 0.01391 -0.0475 0.6226 0.9251
6.250 0.8529 0.01974 0.01282 -0.0456 0.5954 0.9377
6.500 0.8673 0.01941 0.01257 -0.0431 0.5601 0.9567
6.750 0.8894 0.01929 0.01250 -0.0424 0.5199 0.9912
7.000 0.9039 0.01940 0.01245 -0.0404 0.4669 1.0000
7.250 0.9102 0.02006 0.01248 -0.0371 0.3715 1.0000
7.500 0.9036 0.02173 0.01356 -0.0332 0.2891 1.0000
7.750 0.8976 0.02369 0.01505 -0.0299 0.2158 1.0000
8.000 0.8946 0.02570 0.01660 -0.0273 0.1502 1.0000
8.250 0.8964 0.02756 0.01810 -0.0253 0.1035 1.0000
9.000 0.9214 0.03212 0.02238 -0.0212 0.0602 1.0000
9.250 0.9304 0.03364 0.02392 -0.0200 0.0554 1.0000
9.500 0.9408 0.03509 0.02543 -0.0190 0.0516 1.0000
9.750 0.9501 0.03664 0.02700 -0.0180 0.0488 1.0000
10.000 0.9604 0.03816 0.02858 -0.0170 0.0460 1.0000
10.250 0.9722 0.03961 0.03011 -0.0161 0.0434 1.0000
10.500 0.9838 0.04112 0.03167 -0.0152 0.0415 1.0000
10.750 0.9959 0.04269 0.03322 -0.0144 0.0400 1.0000
11.000 1.0120 0.04411 0.03468 -0.0137 0.0387 1.0000
11.250 1.0298 0.04545 0.03616 -0.0131 0.0371 1.0000
11.500 1.0466 0.04688 0.03769 -0.0125 0.0354 1.0000
11.750 1.0628 0.04839 0.03927 -0.0121 0.0340 1.0000
12.000 1.0816 0.04994 0.04084 -0.0117 0.0330 1.0000
12.250 1.1050 0.05166 0.04259 -0.0115 0.0322 1.0000
12.500 1.1222 0.05365 0.04485 -0.0110 0.0315 1.0000
12.750 1.1367 0.05593 0.04741 -0.0104 0.0310 1.0000
13.000 1.1469 0.05848 0.05023 -0.0098 0.0304 1.0000
13.250 1.1521 0.06126 0.05328 -0.0092 0.0298 1.0000
13.500 1.1539 0.06420 0.05648 -0.0086 0.0293 1.0000
13.750 1.1533 0.06732 0.05983 -0.0082 0.0287 1.0000
14.000 1.1511 0.07053 0.06326 -0.0079 0.0282 1.0000
14.250 1.1472 0.07396 0.06689 -0.0079 0.0278 1.0000
14.500 1.1403 0.07779 0.07094 -0.0081 0.0275 1.0000
14.750 1.1311 0.08196 0.07534 -0.0086 0.0273 1.0000
15.000 1.1181 0.08678 0.08040 -0.0095 0.0272 1.0000
15.250 1.1026 0.09212 0.08600 -0.0110 0.0272 1.0000
15.500 1.0833 0.09829 0.09242 -0.0133 0.0272 1.0000
15.750 1.0596 0.10561 0.10002 -0.0166 0.0273 1.0000
16.000 1.0263 0.11537 0.11009 -0.0220 0.0275 1.0000
16.250 0.9691 0.13228 0.12737 -0.0330 0.0282 1.0000
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