NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 500,000 Max Cl/Cd: 60.75 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64209-il-500000-n5.txt Download as CSV file: xf-naca64209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6242 0.08163 0.07940 -0.0201 1.0000 0.0066
-10.000 -0.6287 0.07632 0.07412 -0.0239 1.0000 0.0063
-9.750 -0.6463 0.06681 0.06464 -0.0330 1.0000 0.0061
-9.500 -0.6818 0.05853 0.05626 -0.0387 1.0000 0.0062
-9.250 -0.7052 0.05137 0.04890 -0.0403 1.0000 0.0062
-9.000 -0.7743 0.02898 0.02515 -0.0391 1.0000 0.0063
-8.750 -0.7650 0.02460 0.02019 -0.0379 1.0000 0.0066
-8.250 -0.7297 0.02073 0.01576 -0.0363 1.0000 0.0071
-8.000 -0.7087 0.01982 0.01476 -0.0357 1.0000 0.0076
-7.750 -0.6880 0.01868 0.01345 -0.0350 1.0000 0.0081
-7.500 -0.6676 0.01742 0.01199 -0.0340 1.0000 0.0085
-7.250 -0.6422 0.01620 0.01058 -0.0341 0.9972 0.0089
-7.000 -0.6111 0.01514 0.00933 -0.0353 0.9911 0.0092
-6.750 -0.5792 0.01420 0.00822 -0.0367 0.9852 0.0096
-6.500 -0.5477 0.01348 0.00739 -0.0379 0.9779 0.0102
-6.250 -0.5158 0.01290 0.00677 -0.0391 0.9701 0.0111
-6.000 -0.4834 0.01243 0.00625 -0.0404 0.9623 0.0120
-5.750 -0.4516 0.01228 0.00612 -0.0414 0.9529 0.0128
-5.500 -0.4202 0.01244 0.00630 -0.0422 0.9430 0.0139
-5.250 -0.3905 0.01247 0.00632 -0.0428 0.9321 0.0151
-5.000 -0.3643 0.01172 0.00536 -0.0425 0.9204 0.0195
-4.750 -0.3373 0.01158 0.00512 -0.0423 0.9087 0.0210
-4.500 -0.3106 0.01143 0.00494 -0.0421 0.8973 0.0220
-4.250 -0.2843 0.01118 0.00461 -0.0419 0.8863 0.0225
-4.000 -0.2580 0.01094 0.00430 -0.0417 0.8756 0.0230
-3.750 -0.2315 0.01074 0.00403 -0.0415 0.8650 0.0236
-3.500 -0.2048 0.01053 0.00377 -0.0413 0.8544 0.0242
-3.250 -0.1780 0.01036 0.00353 -0.0412 0.8444 0.0248
-3.000 -0.1511 0.01019 0.00331 -0.0410 0.8346 0.0253
-2.750 -0.1240 0.01004 0.00312 -0.0410 0.8246 0.0258
-2.500 -0.0967 0.00997 0.00302 -0.0409 0.8151 0.0265
-2.250 -0.0696 0.00984 0.00285 -0.0408 0.8055 0.0274
-2.000 -0.0427 0.00945 0.00242 -0.0408 0.7956 0.0287
-1.750 -0.0154 0.00923 0.00217 -0.0408 0.7866 0.0299
-1.500 0.0120 0.00909 0.00199 -0.0408 0.7776 0.0302
-1.250 0.0397 0.00896 0.00183 -0.0408 0.7680 0.0302
-1.000 0.0673 0.00885 0.00169 -0.0408 0.7587 0.0302
-0.750 0.0949 0.00876 0.00156 -0.0408 0.7493 0.0304
-0.500 0.1228 0.00868 0.00146 -0.0408 0.7404 0.0306
-0.250 0.1506 0.00862 0.00137 -0.0408 0.7319 0.0310
0.000 0.1784 0.00857 0.00130 -0.0409 0.7227 0.0316
0.250 0.2063 0.00852 0.00125 -0.0409 0.7138 0.0325
0.500 0.2341 0.00850 0.00121 -0.0409 0.7051 0.0336
0.750 0.2621 0.00847 0.00119 -0.0409 0.6967 0.0349
1.000 0.2900 0.00847 0.00119 -0.0410 0.6880 0.0363
1.250 0.3177 0.00848 0.00122 -0.0409 0.6770 0.0411
1.500 0.3433 0.00709 0.00117 -0.0416 0.6597 0.5353
1.750 0.3689 0.00686 0.00126 -0.0413 0.6321 0.6514
2.250 0.4198 0.00712 0.00144 -0.0403 0.5374 0.7234
2.500 0.4453 0.00733 0.00157 -0.0399 0.4891 0.7499
2.750 0.4689 0.00781 0.00177 -0.0393 0.3919 0.7727
3.000 0.4901 0.00879 0.00218 -0.0386 0.2412 0.7933
3.250 0.5109 0.00949 0.00260 -0.0376 0.1338 0.8352
3.500 0.5319 0.01006 0.00296 -0.0363 0.0628 0.8681
3.750 0.5562 0.01040 0.00323 -0.0357 0.0399 0.8821
4.000 0.5810 0.01062 0.00349 -0.0351 0.0330 0.8957
4.250 0.6051 0.01089 0.00380 -0.0344 0.0275 0.9107
4.500 0.6289 0.01112 0.00411 -0.0336 0.0244 0.9276
4.750 0.6534 0.01136 0.00441 -0.0329 0.0218 0.9472
5.000 0.6825 0.01170 0.00479 -0.0333 0.0193 0.9725
5.250 0.7098 0.01234 0.00550 -0.0335 0.0171 1.0000
5.500 0.7353 0.01284 0.00604 -0.0333 0.0164 1.0000
5.750 0.7608 0.01330 0.00656 -0.0331 0.0157 1.0000
6.000 0.7860 0.01379 0.00710 -0.0328 0.0148 1.0000
6.250 0.8105 0.01439 0.00777 -0.0324 0.0142 1.0000
6.500 0.8348 0.01502 0.00846 -0.0320 0.0136 1.0000
6.750 0.8587 0.01568 0.00918 -0.0316 0.0131 1.0000
7.000 0.8828 0.01630 0.00985 -0.0312 0.0125 1.0000
7.250 0.9059 0.01710 0.01071 -0.0307 0.0117 1.0000
7.500 0.9270 0.01837 0.01210 -0.0300 0.0110 1.0000
7.750 0.9505 0.01917 0.01301 -0.0295 0.0107 1.0000
8.000 0.9732 0.02015 0.01412 -0.0289 0.0103 1.0000
8.250 0.9955 0.02124 0.01536 -0.0283 0.0098 1.0000
8.500 1.0175 0.02232 0.01660 -0.0277 0.0093 1.0000
8.750 1.0396 0.02317 0.01757 -0.0271 0.0087 1.0000
9.000 1.0621 0.02365 0.01811 -0.0268 0.0082 1.0000
9.250 1.0838 0.02425 0.01875 -0.0263 0.0078 1.0000
9.500 1.1005 0.02599 0.02069 -0.0253 0.0074 1.0000
9.750 1.1160 0.02799 0.02298 -0.0241 0.0071 1.0000
10.000 1.1307 0.02995 0.02523 -0.0228 0.0069 1.0000
10.250 1.1413 0.03247 0.02808 -0.0212 0.0065 1.0000
10.500 1.1448 0.03582 0.03184 -0.0191 0.0062 1.0000
10.750 1.1394 0.03993 0.03636 -0.0164 0.0059 1.0000
11.000 1.1233 0.04406 0.04084 -0.0128 0.0058 1.0000
11.250 1.0938 0.04923 0.04635 -0.0094 0.0057 1.0000
11.500 1.0534 0.05647 0.05392 -0.0085 0.0057 1.0000
11.750 1.0080 0.06589 0.06361 -0.0113 0.0057 1.0000
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Polar data table (+)
Polar graphs
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