NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415a05-il-1000000.txt Download as CSV file: xf-naca652415a05-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.4218 0.15382 0.15193 -0.0315 0.9125 0.0143
-15.250 -0.4192 0.14930 0.14735 -0.0333 0.8980 0.0144
-14.750 -0.8679 0.04371 0.04080 -0.0870 0.9150 0.0120
-14.500 -0.8257 0.04632 0.04356 -0.0859 0.8993 0.0123
-14.250 -0.8480 0.04181 0.03880 -0.0867 0.8818 0.0123
-14.000 -0.8505 0.03965 0.03650 -0.0865 0.8687 0.0125
-13.750 -0.8558 0.03733 0.03402 -0.0861 0.8570 0.0126
-13.500 -0.8627 0.03496 0.03147 -0.0851 0.8468 0.0126
-13.250 -0.8694 0.03280 0.02912 -0.0836 0.8372 0.0128
-13.000 -0.8715 0.03107 0.02723 -0.0818 0.8284 0.0130
-12.750 -0.8688 0.02984 0.02586 -0.0800 0.8207 0.0132
-12.500 -0.8681 0.02842 0.02429 -0.0777 0.8128 0.0134
-12.250 -0.8661 0.02718 0.02286 -0.0751 0.8056 0.0135
-12.000 -0.8624 0.02602 0.02155 -0.0724 0.7987 0.0138
-11.750 -0.8534 0.02509 0.02046 -0.0702 0.7924 0.0140
-11.500 -0.8382 0.02443 0.01966 -0.0689 0.7870 0.0142
-11.250 -0.8275 0.02292 0.01794 -0.0672 0.7814 0.0145
-11.000 -0.8149 0.02151 0.01638 -0.0657 0.7762 0.0149
-10.750 -0.7961 0.02081 0.01560 -0.0648 0.7714 0.0152
-10.500 -0.7750 0.02041 0.01517 -0.0642 0.7665 0.0155
-10.250 -0.7533 0.02007 0.01476 -0.0636 0.7617 0.0159
-10.000 -0.7320 0.01951 0.01410 -0.0629 0.7571 0.0163
-9.750 -0.7099 0.01891 0.01342 -0.0623 0.7526 0.0167
-9.500 -0.6868 0.01852 0.01293 -0.0619 0.7480 0.0173
-9.250 -0.6633 0.01816 0.01245 -0.0614 0.7435 0.0176
-9.000 -0.6429 0.01694 0.01110 -0.0607 0.7397 0.0182
-8.750 -0.6204 0.01623 0.01036 -0.0602 0.7357 0.0187
-8.500 -0.5961 0.01584 0.00993 -0.0599 0.7317 0.0191
-8.250 -0.5715 0.01551 0.00954 -0.0596 0.7277 0.0197
-8.000 -0.5468 0.01509 0.00906 -0.0593 0.7242 0.0202
-7.750 -0.5213 0.01475 0.00868 -0.0591 0.7206 0.0209
-7.500 -0.4954 0.01450 0.00836 -0.0590 0.7169 0.0215
-7.250 -0.4694 0.01427 0.00805 -0.0588 0.7133 0.0218
-7.000 -0.4487 0.01319 0.00691 -0.0580 0.7097 0.0228
-6.750 -0.4233 0.01281 0.00653 -0.0578 0.7065 0.0234
-6.500 -0.3973 0.01250 0.00620 -0.0577 0.7031 0.0241
-6.250 -0.3711 0.01224 0.00591 -0.0576 0.6999 0.0250
-6.000 -0.3449 0.01199 0.00560 -0.0575 0.6967 0.0258
-5.750 -0.3183 0.01176 0.00532 -0.0574 0.6938 0.0263
-5.500 -0.2941 0.01119 0.00472 -0.0570 0.6910 0.0273
-5.250 -0.2685 0.01081 0.00432 -0.0568 0.6882 0.0284
-5.000 -0.2417 0.01057 0.00407 -0.0568 0.6852 0.0295
-4.750 -0.2147 0.01038 0.00384 -0.0568 0.6823 0.0307
-4.500 -0.1876 0.01022 0.00363 -0.0568 0.6791 0.0317
-4.250 -0.1608 0.00993 0.00332 -0.0568 0.6769 0.0329
-4.000 -0.1339 0.00965 0.00303 -0.0567 0.6744 0.0351
-3.750 -0.1063 0.00947 0.00285 -0.0568 0.6719 0.0372
-3.500 -0.0784 0.00934 0.00269 -0.0570 0.6694 0.0390
-3.250 -0.0513 0.00912 0.00246 -0.0570 0.6670 0.0440
-3.000 -0.0238 0.00897 0.00231 -0.0571 0.6641 0.0518
-2.750 0.0026 0.00861 0.00214 -0.0571 0.6621 0.0969
-2.500 0.0264 0.00788 0.00191 -0.0569 0.6598 0.2335
-2.250 0.0480 0.00690 0.00167 -0.0564 0.6576 0.4401
-2.000 0.0738 0.00652 0.00160 -0.0563 0.6555 0.5389
-1.750 0.1015 0.00639 0.00157 -0.0564 0.6533 0.5805
-1.500 0.1296 0.00633 0.00156 -0.0566 0.6511 0.6088
-1.250 0.1579 0.00633 0.00157 -0.0568 0.6484 0.6325
-1.000 0.1862 0.00626 0.00158 -0.0570 0.6467 0.6582
-0.750 0.2143 0.00621 0.00162 -0.0571 0.6448 0.6879
-0.500 0.2426 0.00618 0.00166 -0.0572 0.6429 0.7106
-0.250 0.2712 0.00618 0.00168 -0.0575 0.6408 0.7249
0.000 0.3003 0.00620 0.00168 -0.0578 0.6387 0.7334
0.250 0.3290 0.00620 0.00170 -0.0581 0.6367 0.7406
0.500 0.3580 0.00625 0.00172 -0.0584 0.6346 0.7481
0.750 0.3868 0.00629 0.00177 -0.0588 0.6325 0.7550
1.000 0.4158 0.00629 0.00181 -0.0591 0.6308 0.7626
1.250 0.4447 0.00629 0.00184 -0.0595 0.6289 0.7700
1.500 0.4735 0.00630 0.00189 -0.0598 0.6270 0.7777
1.750 0.5024 0.00633 0.00193 -0.0601 0.6250 0.7851
2.000 0.5311 0.00634 0.00197 -0.0604 0.6230 0.7927
2.250 0.5599 0.00639 0.00202 -0.0607 0.6210 0.8007
2.500 0.5883 0.00645 0.00211 -0.0610 0.6187 0.8085
3.000 0.6453 0.00649 0.00225 -0.0615 0.6139 0.8241
3.250 0.6739 0.00650 0.00229 -0.0618 0.6104 0.8325
3.500 0.7017 0.00649 0.00233 -0.0619 0.6062 0.8405
4.000 0.7575 0.00654 0.00246 -0.0622 0.5975 0.8570
4.250 0.7855 0.00655 0.00251 -0.0623 0.5926 0.8656
4.500 0.8119 0.00654 0.00253 -0.0621 0.5821 0.8742
4.750 0.8383 0.00655 0.00254 -0.0620 0.5668 0.8831
5.000 0.8643 0.00661 0.00262 -0.0617 0.5548 0.8921
5.250 0.8904 0.00668 0.00271 -0.0615 0.5431 0.9010
5.500 0.9156 0.00679 0.00283 -0.0612 0.5277 0.9109
5.750 0.9382 0.00698 0.00298 -0.0603 0.4994 0.9209
6.000 0.9533 0.00755 0.00331 -0.0582 0.4404 0.9338
6.250 0.9596 0.00850 0.00391 -0.0547 0.3613 0.9524
6.500 0.9724 0.00970 0.00471 -0.0531 0.2738 0.9755
6.750 0.9903 0.01102 0.00560 -0.0530 0.1924 1.0000
7.000 0.9892 0.01187 0.00622 -0.0484 0.1483 1.0000
7.250 0.9856 0.01285 0.00699 -0.0437 0.1096 1.0000
7.500 0.9885 0.01381 0.00780 -0.0404 0.0803 1.0000
7.750 0.9920 0.01486 0.00871 -0.0374 0.0541 1.0000
8.000 1.0001 0.01579 0.00955 -0.0352 0.0395 1.0000
8.250 1.0109 0.01663 0.01035 -0.0334 0.0318 1.0000
8.500 1.0223 0.01749 0.01119 -0.0317 0.0273 1.0000
8.750 1.0359 0.01825 0.01196 -0.0304 0.0251 1.0000
9.000 1.0463 0.01923 0.01295 -0.0287 0.0228 1.0000
9.250 1.0610 0.01997 0.01372 -0.0276 0.0217 1.0000
9.500 1.0746 0.02079 0.01456 -0.0265 0.0208 1.0000
9.750 1.0873 0.02170 0.01548 -0.0252 0.0197 1.0000
10.000 1.0949 0.02295 0.01677 -0.0236 0.0186 1.0000
10.250 1.1079 0.02388 0.01774 -0.0225 0.0181 1.0000
10.500 1.1209 0.02483 0.01873 -0.0215 0.0175 1.0000
10.750 1.1333 0.02582 0.01975 -0.0204 0.0170 1.0000
11.000 1.1452 0.02686 0.02083 -0.0194 0.0164 1.0000
11.250 1.1564 0.02798 0.02198 -0.0184 0.0161 1.0000
11.500 1.1654 0.02927 0.02330 -0.0173 0.0155 1.0000
11.750 1.1731 0.03069 0.02476 -0.0161 0.0152 1.0000
12.000 1.1757 0.03258 0.02672 -0.0146 0.0147 1.0000
12.250 1.1859 0.03390 0.02809 -0.0137 0.0146 1.0000
12.500 1.1978 0.03510 0.02934 -0.0130 0.0143 1.0000
12.750 1.2064 0.03659 0.03089 -0.0122 0.0142 1.0000
13.000 1.2172 0.03795 0.03230 -0.0115 0.0139 1.0000
13.250 1.2248 0.03958 0.03399 -0.0107 0.0136 1.0000
13.500 1.2341 0.04110 0.03556 -0.0101 0.0135 1.0000
13.750 1.2432 0.04268 0.03718 -0.0095 0.0132 1.0000
14.000 1.2513 0.04437 0.03892 -0.0089 0.0129 1.0000
14.250 1.2605 0.04598 0.04059 -0.0085 0.0127 1.0000
14.500 1.2663 0.04794 0.04259 -0.0079 0.0126 1.0000
14.750 1.2730 0.04983 0.04453 -0.0075 0.0123 1.0000
15.000 1.2776 0.05197 0.04672 -0.0070 0.0121 1.0000
15.250 1.2779 0.05453 0.04936 -0.0063 0.0119 1.0000
15.500 1.2818 0.05678 0.05169 -0.0058 0.0117 1.0000
15.750 1.2890 0.05883 0.05382 -0.0057 0.0115 1.0000
16.000 1.2947 0.06102 0.05609 -0.0055 0.0115 1.0000
16.250 1.3002 0.06330 0.05845 -0.0054 0.0115 1.0000
16.500 1.3061 0.06561 0.06086 -0.0056 0.0113 1.0000
16.750 1.3102 0.06813 0.06346 -0.0057 0.0112 1.0000
17.000 1.3140 0.07072 0.06614 -0.0059 0.0111 1.0000
17.250 1.3167 0.07352 0.06904 -0.0062 0.0110 1.0000
17.500 1.3189 0.07646 0.07207 -0.0066 0.0108 1.0000
17.750 1.3207 0.07952 0.07522 -0.0073 0.0107 1.0000
18.000 1.3200 0.08292 0.07873 -0.0078 0.0106 1.0000
18.250 1.3196 0.08637 0.08229 -0.0086 0.0105 1.0000
18.500 1.3186 0.09000 0.08603 -0.0097 0.0104 1.0000
18.750 1.3163 0.09395 0.09008 -0.0110 0.0103 1.0000
19.000 1.3128 0.09811 0.09436 -0.0124 0.0102 1.0000
19.250 1.3094 0.10235 0.09871 -0.0141 0.0101 1.0000
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Polar data table (+)
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