NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 500,000 Max Cl/Cd: 68.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca641112-il-500000.txt Download as CSV file: xf-naca641112-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6425 0.11112 0.10881 -0.0088 1.0000 0.0268
-12.250 -0.6421 0.10680 0.10449 -0.0108 1.0000 0.0271
-12.000 -0.6429 0.10217 0.09987 -0.0131 1.0000 0.0274
-11.750 -0.6467 0.09653 0.09425 -0.0162 1.0000 0.0278
-11.000 -0.8340 0.05156 0.04840 -0.0403 1.0000 0.0198
-10.750 -0.8549 0.04797 0.04464 -0.0385 1.0000 0.0196
-10.500 -0.8716 0.04462 0.04109 -0.0357 1.0000 0.0194
-10.250 -0.8819 0.04059 0.03677 -0.0335 1.0000 0.0191
-10.000 -0.8860 0.03656 0.03238 -0.0313 1.0000 0.0190
-9.750 -0.8831 0.03295 0.02841 -0.0294 1.0000 0.0190
-9.500 -0.8734 0.03003 0.02514 -0.0279 1.0000 0.0192
-9.250 -0.8591 0.02770 0.02253 -0.0266 1.0000 0.0195
-9.000 -0.8414 0.02609 0.02067 -0.0256 1.0000 0.0199
-8.750 -0.8232 0.02465 0.01897 -0.0246 1.0000 0.0205
-8.500 -0.8045 0.02210 0.01628 -0.0238 1.0000 0.0212
-8.250 -0.7839 0.02087 0.01499 -0.0231 1.0000 0.0217
-8.000 -0.7638 0.01991 0.01398 -0.0222 1.0000 0.0222
-7.750 -0.7458 0.01910 0.01312 -0.0209 0.9993 0.0228
-7.500 -0.7112 0.01802 0.01197 -0.0228 0.9911 0.0237
-7.000 -0.6406 0.01655 0.01032 -0.0267 0.9744 0.0258
-6.750 -0.6112 0.01501 0.00872 -0.0277 0.9631 0.0271
-6.500 -0.5840 0.01422 0.00789 -0.0281 0.9498 0.0284
-6.250 -0.5603 0.01371 0.00732 -0.0275 0.9357 0.0298
-6.000 -0.5380 0.01327 0.00681 -0.0265 0.9225 0.0315
-5.750 -0.5150 0.01293 0.00639 -0.0256 0.9107 0.0329
-5.500 -0.4944 0.01218 0.00557 -0.0244 0.8989 0.0362
-5.250 -0.4704 0.01180 0.00515 -0.0238 0.8879 0.0393
-5.000 -0.4457 0.01149 0.00475 -0.0232 0.8780 0.0425
-4.750 -0.4219 0.01100 0.00424 -0.0225 0.8682 0.0495
-4.500 -0.3967 0.01060 0.00384 -0.0222 0.8584 0.0610
-4.250 -0.3731 0.00997 0.00341 -0.0217 0.8496 0.1095
-4.000 -0.3524 0.00877 0.00287 -0.0212 0.8399 0.2633
-3.750 -0.3317 0.00762 0.00249 -0.0207 0.8307 0.4589
-3.500 -0.3058 0.00740 0.00238 -0.0204 0.8224 0.5163
-3.250 -0.2784 0.00729 0.00231 -0.0203 0.8134 0.5482
-3.000 -0.2510 0.00724 0.00223 -0.0201 0.8058 0.5685
-2.750 -0.2231 0.00718 0.00217 -0.0201 0.7970 0.5859
-2.500 -0.1953 0.00716 0.00212 -0.0200 0.7894 0.6009
-2.250 -0.1676 0.00714 0.00211 -0.0199 0.7808 0.6210
-2.000 -0.1402 0.00716 0.00214 -0.0197 0.7730 0.6446
-1.750 -0.1124 0.00717 0.00214 -0.0196 0.7646 0.6595
-1.500 -0.0842 0.00717 0.00210 -0.0196 0.7570 0.6679
-1.250 -0.0559 0.00714 0.00206 -0.0197 0.7491 0.6755
-1.000 -0.0275 0.00715 0.00203 -0.0197 0.7419 0.6836
-0.750 0.0009 0.00713 0.00200 -0.0198 0.7342 0.6903
-0.500 0.0293 0.00714 0.00199 -0.0199 0.7272 0.6973
-0.250 0.0578 0.00713 0.00197 -0.0200 0.7194 0.7043
0.000 0.0860 0.00714 0.00197 -0.0201 0.7126 0.7111
0.250 0.1147 0.00715 0.00198 -0.0203 0.7052 0.7186
0.500 0.1428 0.00717 0.00200 -0.0203 0.6991 0.7258
0.750 0.1715 0.00718 0.00203 -0.0205 0.6919 0.7338
1.000 0.1996 0.00720 0.00206 -0.0205 0.6855 0.7412
1.250 0.2282 0.00723 0.00211 -0.0206 0.6781 0.7492
1.500 0.2562 0.00725 0.00215 -0.0206 0.6707 0.7567
1.750 0.2846 0.00727 0.00221 -0.0207 0.6628 0.7650
2.000 0.3125 0.00731 0.00227 -0.0207 0.6557 0.7730
2.250 0.3404 0.00731 0.00231 -0.0206 0.6436 0.7815
2.500 0.3672 0.00733 0.00229 -0.0203 0.6240 0.7901
2.750 0.3945 0.00733 0.00232 -0.0201 0.6044 0.7984
3.000 0.4219 0.00738 0.00237 -0.0199 0.5867 0.8074
3.250 0.4492 0.00743 0.00246 -0.0198 0.5728 0.8155
3.500 0.4766 0.00750 0.00255 -0.0197 0.5557 0.8248
3.750 0.5029 0.00760 0.00265 -0.0193 0.5327 0.8334
4.000 0.5290 0.00774 0.00276 -0.0189 0.4989 0.8428
4.250 0.5529 0.00812 0.00291 -0.0183 0.4261 0.8528
4.500 0.5686 0.00945 0.00347 -0.0168 0.2465 0.8628
4.750 0.5860 0.01067 0.00408 -0.0156 0.1154 0.8735
5.000 0.6068 0.01143 0.00458 -0.0147 0.0619 0.8851
5.250 0.6289 0.01185 0.00501 -0.0136 0.0497 0.8965
5.500 0.6502 0.01231 0.00550 -0.0124 0.0428 0.9089
5.750 0.6719 0.01262 0.00587 -0.0113 0.0386 0.9226
6.000 0.6894 0.01329 0.00659 -0.0094 0.0345 0.9398
6.250 0.7125 0.01360 0.00699 -0.0086 0.0327 0.9590
6.500 0.7444 0.01415 0.00759 -0.0098 0.0302 0.9789
6.750 0.7727 0.01498 0.00842 -0.0107 0.0282 1.0000
7.000 0.7935 0.01596 0.00945 -0.0100 0.0266 1.0000
7.250 0.8176 0.01651 0.01004 -0.0098 0.0254 1.0000
7.500 0.8403 0.01724 0.01081 -0.0093 0.0244 1.0000
7.750 0.8627 0.01798 0.01159 -0.0087 0.0235 1.0000
8.000 0.8847 0.01877 0.01240 -0.0082 0.0227 1.0000
8.250 0.9059 0.01980 0.01343 -0.0075 0.0220 1.0000
8.500 0.9265 0.02176 0.01546 -0.0068 0.0213 1.0000
8.750 0.9487 0.02305 0.01688 -0.0063 0.0208 1.0000
9.000 0.9707 0.02386 0.01781 -0.0057 0.0203 1.0000
9.250 0.9919 0.02500 0.01909 -0.0050 0.0196 1.0000
9.500 1.0122 0.02654 0.02080 -0.0043 0.0192 1.0000
9.750 1.0311 0.02811 0.02253 -0.0034 0.0187 1.0000
10.000 1.0480 0.02995 0.02457 -0.0024 0.0185 1.0000
10.250 1.0627 0.03193 0.02676 -0.0012 0.0182 1.0000
10.500 1.0744 0.03411 0.02915 0.0002 0.0180 1.0000
10.750 1.0821 0.03655 0.03183 0.0020 0.0178 1.0000
11.000 1.0966 0.03720 0.03247 0.0029 0.0173 1.0000
11.250 1.1035 0.03890 0.03426 0.0045 0.0169 1.0000
11.500 1.0973 0.04195 0.03752 0.0073 0.0167 1.0000
11.750 1.0829 0.04549 0.04131 0.0102 0.0166 1.0000
12.000 1.0695 0.04867 0.04471 0.0124 0.0166 1.0000
12.250 1.0531 0.05229 0.04855 0.0139 0.0165 1.0000
12.500 1.0360 0.05617 0.05263 0.0144 0.0165 1.0000
12.750 1.0215 0.05995 0.05658 0.0142 0.0166 1.0000
13.000 1.0058 0.06412 0.06095 0.0132 0.0167 1.0000
13.250 0.9818 0.07013 0.06713 0.0108 0.0167 1.0000
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