NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 500,000 Max Cl/Cd: 89.19 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662415-il-500000-n5.txt Download as CSV file: xf-naca662415-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6151 0.08103 0.07843 -0.0857 0.9759 0.0137
-14.750 -0.6811 0.05981 0.05679 -0.1040 0.9671 0.0135
-14.500 -0.7119 0.04974 0.04629 -0.1129 0.9575 0.0135
-14.250 -0.7286 0.04301 0.03913 -0.1180 0.9466 0.0137
-14.000 -0.7214 0.04041 0.03638 -0.1204 0.9350 0.0140
-13.750 -0.7169 0.03839 0.03420 -0.1209 0.9227 0.0141
-13.500 -0.7120 0.03692 0.03261 -0.1205 0.9119 0.0142
-13.000 -0.7073 0.03397 0.02936 -0.1180 0.8931 0.0144
-12.750 -0.7049 0.03254 0.02776 -0.1164 0.8855 0.0146
-12.500 -0.7003 0.03138 0.02647 -0.1147 0.8783 0.0148
-12.250 -0.6958 0.03010 0.02502 -0.1128 0.8717 0.0150
-12.000 -0.6901 0.02888 0.02363 -0.1109 0.8660 0.0153
-11.750 -0.6839 0.02746 0.02201 -0.1090 0.8601 0.0155
-11.500 -0.6748 0.02631 0.02066 -0.1072 0.8550 0.0159
-11.250 -0.6639 0.02518 0.01934 -0.1055 0.8503 0.0163
-11.000 -0.6511 0.02405 0.01802 -0.1040 0.8455 0.0166
-10.750 -0.6369 0.02321 0.01698 -0.1025 0.8412 0.0170
-10.250 -0.6056 0.02153 0.01513 -0.1001 0.8341 0.0176
-10.000 -0.5889 0.02091 0.01444 -0.0988 0.8304 0.0178
-9.750 -0.5716 0.02032 0.01378 -0.0976 0.8269 0.0181
-9.500 -0.5538 0.01979 0.01316 -0.0964 0.8238 0.0184
-9.250 -0.5359 0.01937 0.01265 -0.0952 0.8210 0.0189
-9.000 -0.5162 0.01878 0.01199 -0.0943 0.8181 0.0194
-8.750 -0.4960 0.01826 0.01138 -0.0934 0.8152 0.0199
-8.500 -0.4750 0.01771 0.01074 -0.0926 0.8124 0.0204
-8.250 -0.4538 0.01720 0.01013 -0.0919 0.8098 0.0207
-8.000 -0.4332 0.01658 0.00944 -0.0911 0.8073 0.0211
-7.750 -0.4130 0.01604 0.00887 -0.0902 0.8049 0.0215
-7.500 -0.3923 0.01563 0.00845 -0.0894 0.8023 0.0220
-7.250 -0.3711 0.01525 0.00804 -0.0886 0.7996 0.0225
-7.000 -0.3494 0.01490 0.00767 -0.0878 0.7972 0.0232
-6.750 -0.3277 0.01456 0.00728 -0.0871 0.7950 0.0239
-6.500 -0.3055 0.01424 0.00691 -0.0864 0.7929 0.0247
-6.250 -0.2830 0.01393 0.00654 -0.0858 0.7910 0.0253
-6.000 -0.2617 0.01354 0.00611 -0.0850 0.7891 0.0259
-5.750 -0.2409 0.01313 0.00570 -0.0841 0.7871 0.0268
-5.500 -0.2181 0.01283 0.00540 -0.0835 0.7850 0.0277
-5.250 -0.1948 0.01257 0.00513 -0.0830 0.7830 0.0287
-5.000 -0.1710 0.01233 0.00487 -0.0826 0.7811 0.0300
-4.750 -0.1466 0.01212 0.00463 -0.0822 0.7793 0.0311
-4.500 -0.1229 0.01185 0.00432 -0.0818 0.7776 0.0325
-4.250 -0.0985 0.01160 0.00407 -0.0814 0.7760 0.0342
-4.000 -0.0733 0.01142 0.00385 -0.0812 0.7745 0.0361
-3.750 -0.0479 0.01125 0.00368 -0.0810 0.7727 0.0382
-3.500 -0.0229 0.01106 0.00350 -0.0808 0.7709 0.0418
-3.250 0.0025 0.01089 0.00335 -0.0806 0.7693 0.0470
-3.000 0.0271 0.01063 0.00320 -0.0804 0.7676 0.0693
-2.750 0.0478 0.01003 0.00298 -0.0797 0.7659 0.1695
-2.500 0.0663 0.00917 0.00270 -0.0788 0.7642 0.3299
-2.250 0.0817 0.00790 0.00234 -0.0776 0.7625 0.5659
-2.000 0.1063 0.00773 0.00254 -0.0770 0.7612 0.6843
-1.750 0.1342 0.00783 0.00267 -0.0770 0.7600 0.7109
-1.500 0.1627 0.00792 0.00276 -0.0772 0.7588 0.7252
-1.250 0.1912 0.00801 0.00281 -0.0775 0.7576 0.7349
-1.000 0.2189 0.00808 0.00292 -0.0775 0.7561 0.7418
-0.750 0.2471 0.00817 0.00299 -0.0778 0.7545 0.7503
-0.500 0.2751 0.00821 0.00305 -0.0779 0.7530 0.7538
-0.250 0.3037 0.00822 0.00307 -0.0783 0.7516 0.7552
0.000 0.3323 0.00824 0.00308 -0.0787 0.7502 0.7565
0.250 0.3611 0.00826 0.00310 -0.0791 0.7489 0.7578
0.500 0.3899 0.00829 0.00312 -0.0796 0.7477 0.7592
0.750 0.4188 0.00831 0.00314 -0.0800 0.7462 0.7606
1.000 0.4479 0.00832 0.00314 -0.0805 0.7444 0.7620
1.250 0.4767 0.00834 0.00315 -0.0809 0.7417 0.7636
1.500 0.5037 0.00834 0.00318 -0.0809 0.7378 0.7653
1.750 0.5317 0.00835 0.00320 -0.0812 0.7344 0.7668
2.000 0.5599 0.00834 0.00322 -0.0814 0.7314 0.7680
2.250 0.5887 0.00832 0.00319 -0.0817 0.7269 0.7692
2.500 0.6138 0.00829 0.00323 -0.0813 0.7193 0.7706
2.750 0.6414 0.00826 0.00317 -0.0814 0.7119 0.7720
3.000 0.6664 0.00825 0.00323 -0.0809 0.7029 0.7735
3.250 0.6919 0.00823 0.00322 -0.0805 0.6911 0.7752
3.500 0.7162 0.00824 0.00323 -0.0799 0.6752 0.7769
3.750 0.7385 0.00828 0.00322 -0.0789 0.6501 0.7788
4.000 0.7475 0.00864 0.00325 -0.0751 0.5719 0.7810
4.250 0.7403 0.00960 0.00372 -0.0684 0.4822 0.7837
4.500 0.7285 0.01049 0.00425 -0.0610 0.4022 0.7865
4.750 0.7232 0.01143 0.00487 -0.0551 0.3307 0.7894
5.000 0.7230 0.01238 0.00551 -0.0505 0.2644 0.7922
5.250 0.7251 0.01336 0.00618 -0.0465 0.1985 0.7951
5.500 0.7322 0.01422 0.00678 -0.0435 0.1447 0.7978
5.750 0.7396 0.01513 0.00744 -0.0406 0.0926 0.8004
6.000 0.7493 0.01595 0.00809 -0.0381 0.0533 0.8028
6.250 0.7644 0.01653 0.00861 -0.0365 0.0401 0.8053
6.500 0.7817 0.01703 0.00911 -0.0352 0.0354 0.8079
6.750 0.7997 0.01750 0.00959 -0.0340 0.0326 0.8107
7.000 0.8180 0.01797 0.01009 -0.0330 0.0304 0.8136
7.250 0.8351 0.01853 0.01065 -0.0318 0.0281 0.8164
7.500 0.8523 0.01905 0.01121 -0.0305 0.0267 0.8191
7.750 0.8700 0.01955 0.01177 -0.0294 0.0255 0.8222
8.000 0.8872 0.02009 0.01237 -0.0283 0.0243 0.8257
8.250 0.9038 0.02070 0.01300 -0.0271 0.0233 0.8293
8.500 0.9185 0.02146 0.01378 -0.0258 0.0220 0.8328
8.750 0.9352 0.02203 0.01442 -0.0246 0.0213 0.8360
9.000 0.9523 0.02261 0.01506 -0.0236 0.0202 0.8396
9.250 0.9688 0.02323 0.01573 -0.0225 0.0192 0.8436
9.500 0.9845 0.02394 0.01647 -0.0214 0.0184 0.8478
9.750 0.9980 0.02478 0.01735 -0.0200 0.0178 0.8517
10.000 1.0121 0.02558 0.01823 -0.0187 0.0173 0.8562
10.250 1.0271 0.02633 0.01906 -0.0176 0.0167 0.8611
10.500 1.0414 0.02715 0.01995 -0.0164 0.0161 0.8659
10.750 1.0548 0.02801 0.02088 -0.0151 0.0157 0.8712
11.000 1.0683 0.02888 0.02183 -0.0139 0.0153 0.8773
11.250 1.0817 0.02976 0.02276 -0.0127 0.0148 0.8835
11.500 1.0937 0.03072 0.02379 -0.0114 0.0145 0.8908
11.750 1.1043 0.03183 0.02496 -0.0100 0.0142 0.8985
12.000 1.1145 0.03296 0.02618 -0.0086 0.0139 0.9073
12.250 1.1250 0.03406 0.02739 -0.0072 0.0137 0.9168
12.500 1.1346 0.03526 0.02870 -0.0058 0.0135 0.9280
12.750 1.1462 0.03641 0.02998 -0.0048 0.0132 0.9418
13.000 1.1612 0.03778 0.03146 -0.0048 0.0129 0.9614
13.500 1.1826 0.04060 0.03445 -0.0034 0.0126 1.0000
13.750 1.1930 0.04209 0.03602 -0.0027 0.0123 1.0000
14.000 1.2027 0.04368 0.03770 -0.0020 0.0122 1.0000
14.250 1.2124 0.04527 0.03936 -0.0015 0.0120 1.0000
14.500 1.2219 0.04688 0.04103 -0.0010 0.0118 1.0000
14.750 1.2294 0.04873 0.04296 -0.0005 0.0117 1.0000
15.000 1.2368 0.05061 0.04491 -0.0001 0.0115 1.0000
15.250 1.2422 0.05277 0.04716 0.0004 0.0113 1.0000
15.500 1.2458 0.05518 0.04967 0.0008 0.0112 1.0000
15.750 1.2487 0.05775 0.05236 0.0012 0.0111 1.0000
16.000 1.2520 0.06031 0.05506 0.0014 0.0110 1.0000
16.250 1.2540 0.06310 0.05799 0.0014 0.0110 1.0000
16.500 1.2545 0.06616 0.06121 0.0013 0.0109 1.0000
16.750 1.2529 0.06957 0.06477 0.0010 0.0108 1.0000
17.000 1.2505 0.07317 0.06854 0.0005 0.0107 1.0000
17.250 1.2459 0.07722 0.07276 -0.0003 0.0106 1.0000
17.500 1.2398 0.08163 0.07735 -0.0014 0.0106 1.0000
17.750 1.2320 0.08648 0.08237 -0.0029 0.0105 1.0000
18.000 1.2222 0.09179 0.08786 -0.0049 0.0105 1.0000
18.250 1.2103 0.09765 0.09391 -0.0073 0.0104 1.0000
18.500 1.1972 0.10399 0.10044 -0.0103 0.0104 1.0000
18.750 1.1809 0.11120 0.10784 -0.0140 0.0103 1.0000
19.000 1.1621 0.11916 0.11600 -0.0184 0.0103 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(2)-415 (naca662415-il)