NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 500,000 Max Cl/Cd: 66.37 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662215-il-500000-n5.txt Download as CSV file: xf-naca662215-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7694 0.07351 0.07061 -0.0743 1.0000 0.0130
-15.250 -0.8105 0.06354 0.06037 -0.0797 1.0000 0.0130
-15.000 -0.8376 0.05714 0.05376 -0.0820 1.0000 0.0130
-14.750 -0.8511 0.05315 0.04961 -0.0827 1.0000 0.0131
-14.500 -0.8647 0.04886 0.04511 -0.0835 0.9809 0.0132
-14.250 -0.8575 0.04548 0.04152 -0.0868 0.9643 0.0135
-14.000 -0.8561 0.04153 0.03726 -0.0894 0.9521 0.0138
-13.750 -0.8540 0.03839 0.03382 -0.0904 0.9387 0.0139
-13.500 -0.8518 0.03617 0.03135 -0.0898 0.9253 0.0142
-13.250 -0.8500 0.03419 0.02913 -0.0884 0.9141 0.0144
-12.750 -0.8401 0.03103 0.02552 -0.0852 0.8958 0.0148
-12.250 -0.8232 0.02828 0.02241 -0.0821 0.8818 0.0152
-12.000 -0.8120 0.02722 0.02123 -0.0807 0.8753 0.0154
-11.750 -0.7994 0.02635 0.02026 -0.0794 0.8697 0.0156
-11.500 -0.7857 0.02560 0.01942 -0.0782 0.8638 0.0158
-11.250 -0.7718 0.02496 0.01871 -0.0769 0.8585 0.0161
-11.000 -0.7564 0.02419 0.01783 -0.0757 0.8540 0.0164
-10.750 -0.7404 0.02353 0.01709 -0.0746 0.8494 0.0167
-10.500 -0.7235 0.02283 0.01629 -0.0736 0.8451 0.0171
-10.250 -0.7057 0.02206 0.01540 -0.0726 0.8414 0.0174
-10.000 -0.6871 0.02132 0.01456 -0.0717 0.8380 0.0177
-9.750 -0.6684 0.02061 0.01376 -0.0708 0.8344 0.0180
-9.500 -0.6496 0.01996 0.01301 -0.0699 0.8308 0.0184
-9.250 -0.6308 0.01939 0.01234 -0.0689 0.8275 0.0187
-9.000 -0.6135 0.01866 0.01156 -0.0677 0.8245 0.0191
-8.750 -0.5956 0.01807 0.01094 -0.0667 0.8215 0.0195
-8.500 -0.5770 0.01759 0.01044 -0.0656 0.8183 0.0199
-8.250 -0.5579 0.01718 0.00999 -0.0647 0.8151 0.0205
-8.000 -0.5393 0.01672 0.00948 -0.0635 0.8120 0.0210
-7.750 -0.5207 0.01630 0.00900 -0.0624 0.8093 0.0217
-7.500 -0.5020 0.01588 0.00853 -0.0612 0.8067 0.0223
-7.250 -0.4834 0.01548 0.00808 -0.0600 0.8040 0.0229
-7.000 -0.4654 0.01509 0.00764 -0.0586 0.8013 0.0233
-6.750 -0.4512 0.01457 0.00711 -0.0565 0.7986 0.0241
-6.500 -0.4344 0.01422 0.00673 -0.0549 0.7962 0.0248
-6.250 -0.4151 0.01392 0.00640 -0.0536 0.7941 0.0257
-5.750 -0.3732 0.01336 0.00578 -0.0518 0.7901 0.0278
-5.500 -0.3511 0.01312 0.00551 -0.0510 0.7880 0.0288
-5.250 -0.3304 0.01278 0.00516 -0.0501 0.7858 0.0303
-5.000 -0.3086 0.01249 0.00487 -0.0493 0.7838 0.0318
-4.750 -0.2858 0.01226 0.00462 -0.0486 0.7819 0.0335
-4.500 -0.2622 0.01206 0.00438 -0.0481 0.7800 0.0355
-4.250 -0.2387 0.01184 0.00415 -0.0476 0.7783 0.0379
-4.000 -0.2151 0.01163 0.00393 -0.0470 0.7766 0.0419
-3.750 -0.1915 0.01141 0.00374 -0.0465 0.7749 0.0497
-3.500 -0.1706 0.01101 0.00352 -0.0456 0.7731 0.0895
-3.250 -0.1540 0.01034 0.00325 -0.0441 0.7711 0.1847
-3.000 -0.1387 0.00957 0.00295 -0.0425 0.7692 0.3039
-2.750 -0.1272 0.00852 0.00255 -0.0402 0.7673 0.4683
-2.500 -0.1147 0.00767 0.00247 -0.0376 0.7655 0.6558
-2.250 -0.0880 0.00770 0.00257 -0.0374 0.7642 0.6912
-2.000 -0.0603 0.00777 0.00264 -0.0374 0.7629 0.7102
-1.750 -0.0322 0.00785 0.00271 -0.0375 0.7617 0.7228
-1.500 -0.0038 0.00792 0.00274 -0.0378 0.7605 0.7315
-1.250 0.0242 0.00798 0.00283 -0.0379 0.7590 0.7383
-1.000 0.0522 0.00806 0.00291 -0.0380 0.7574 0.7464
-0.750 0.0805 0.00810 0.00294 -0.0383 0.7559 0.7508
-0.500 0.1092 0.00810 0.00295 -0.0387 0.7545 0.7522
-0.250 0.1380 0.00811 0.00296 -0.0391 0.7531 0.7536
0.000 0.1667 0.00812 0.00297 -0.0395 0.7518 0.7549
0.250 0.1956 0.00813 0.00298 -0.0399 0.7505 0.7562
0.500 0.2244 0.00814 0.00299 -0.0403 0.7492 0.7576
0.750 0.2533 0.00816 0.00300 -0.0408 0.7478 0.7590
1.000 0.2824 0.00816 0.00299 -0.0412 0.7458 0.7604
1.250 0.3104 0.00816 0.00301 -0.0415 0.7425 0.7619
1.500 0.3383 0.00815 0.00302 -0.0417 0.7384 0.7635
1.750 0.3667 0.00814 0.00301 -0.0420 0.7346 0.7651
2.000 0.3950 0.00808 0.00294 -0.0421 0.7283 0.7663
2.250 0.4215 0.00802 0.00293 -0.0420 0.7194 0.7676
2.500 0.4493 0.00799 0.00291 -0.0420 0.7121 0.7689
2.750 0.4758 0.00795 0.00289 -0.0418 0.7009 0.7703
3.000 0.5017 0.00793 0.00287 -0.0415 0.6853 0.7718
3.250 0.5263 0.00793 0.00285 -0.0409 0.6593 0.7734
3.500 0.5407 0.00824 0.00280 -0.0383 0.5718 0.7754
3.750 0.5383 0.00931 0.00326 -0.0327 0.4507 0.7779
4.000 0.5397 0.01025 0.00374 -0.0282 0.3491 0.7803
4.250 0.5434 0.01105 0.00416 -0.0240 0.2654 0.7825
4.500 0.5458 0.01173 0.00455 -0.0196 0.1944 0.7849
4.750 0.5501 0.01250 0.00502 -0.0157 0.1265 0.7875
5.000 0.5600 0.01318 0.00548 -0.0130 0.0771 0.7901
5.250 0.5736 0.01375 0.00592 -0.0109 0.0477 0.7926
5.500 0.5916 0.01415 0.00628 -0.0095 0.0395 0.7950
5.750 0.6103 0.01453 0.00664 -0.0083 0.0354 0.7973
6.000 0.6289 0.01490 0.00703 -0.0071 0.0327 0.7994
6.250 0.6481 0.01524 0.00743 -0.0059 0.0310 0.8016
6.500 0.6666 0.01564 0.00784 -0.0048 0.0289 0.8041
6.750 0.6843 0.01609 0.00831 -0.0035 0.0275 0.8068
7.000 0.7020 0.01656 0.00881 -0.0022 0.0262 0.8096
7.250 0.7210 0.01698 0.00927 -0.0012 0.0253 0.8125
7.500 0.7393 0.01742 0.00975 -0.0001 0.0241 0.8151
7.750 0.7571 0.01788 0.01025 0.0011 0.0231 0.8178
8.000 0.7736 0.01842 0.01082 0.0024 0.0219 0.8211
8.250 0.7897 0.01903 0.01147 0.0037 0.0210 0.8248
8.500 0.8075 0.01954 0.01203 0.0047 0.0202 0.8283
8.750 0.8240 0.02012 0.01266 0.0060 0.0196 0.8317
9.000 0.8409 0.02066 0.01327 0.0071 0.0189 0.8351
9.250 0.8571 0.02128 0.01393 0.0083 0.0183 0.8389
9.500 0.8731 0.02192 0.01461 0.0094 0.0178 0.8430
9.750 0.8883 0.02263 0.01536 0.0106 0.0172 0.8469
10.000 0.9011 0.02348 0.01627 0.0122 0.0169 0.8511
10.250 0.9161 0.02422 0.01710 0.0134 0.0166 0.8558
10.500 0.9309 0.02501 0.01796 0.0146 0.0163 0.8606
10.750 0.9452 0.02580 0.01885 0.0158 0.0159 0.8654
11.000 0.9592 0.02663 0.01976 0.0171 0.0155 0.8708
11.250 0.9735 0.02746 0.02067 0.0182 0.0151 0.8769
11.500 0.9866 0.02834 0.02166 0.0195 0.0150 0.8831
11.750 1.0002 0.02919 0.02258 0.0207 0.0146 0.8905
12.000 1.0131 0.03007 0.02354 0.0219 0.0143 0.8980
12.250 1.0257 0.03096 0.02451 0.0230 0.0141 0.9069
12.500 1.0369 0.03201 0.02565 0.0243 0.0139 0.9163
12.750 1.0479 0.03308 0.02679 0.0255 0.0136 0.9274
13.000 1.0587 0.03443 0.02827 0.0265 0.0133 0.9403
13.250 1.0754 0.03578 0.02975 0.0262 0.0133 0.9555
13.500 1.0937 0.03727 0.03141 0.0252 0.0131 0.9919
14.000 1.1106 0.04035 0.03473 0.0273 0.0127 1.0000
14.250 1.1179 0.04216 0.03667 0.0281 0.0126 1.0000
14.500 1.1241 0.04408 0.03873 0.0289 0.0124 1.0000
14.750 1.1292 0.04610 0.04089 0.0295 0.0123 1.0000
15.000 1.1325 0.04834 0.04328 0.0302 0.0122 1.0000
15.250 1.1348 0.05071 0.04578 0.0307 0.0121 1.0000
15.500 1.1351 0.05335 0.04857 0.0311 0.0119 1.0000
15.750 1.1341 0.05620 0.05157 0.0313 0.0118 1.0000
16.000 1.1304 0.05947 0.05501 0.0313 0.0118 1.0000
16.250 1.1279 0.06265 0.05832 0.0310 0.0116 1.0000
16.500 1.1247 0.06608 0.06187 0.0304 0.0115 1.0000
16.750 1.1129 0.07093 0.06692 0.0293 0.0115 1.0000
17.000 1.1013 0.07596 0.07214 0.0278 0.0115 1.0000
17.250 1.1014 0.07940 0.07564 0.0262 0.0113 1.0000
17.500 1.0832 0.08606 0.08251 0.0234 0.0113 1.0000
17.750 1.0695 0.09233 0.08894 0.0202 0.0112 1.0000
18.000 1.0582 0.09849 0.09522 0.0168 0.0111 1.0000
18.250 1.0301 0.10833 0.10530 0.0112 0.0112 1.0000
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Polar data table (+)
Polar graphs
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