NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 500,000 Max Cl/Cd: 75.81 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64209-il-500000.txt Download as CSV file: xf-naca64209-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5477 0.08636 0.08410 -0.0241 1.0000 0.0218
-9.250 -0.5516 0.07912 0.07688 -0.0305 1.0000 0.0218
-9.000 -0.5627 0.07300 0.07073 -0.0361 1.0000 0.0218
-8.750 -0.5758 0.06893 0.06661 -0.0383 1.0000 0.0218
-8.500 -0.5869 0.06471 0.06227 -0.0395 1.0000 0.0219
-8.250 -0.5917 0.06044 0.05786 -0.0402 1.0000 0.0219
-8.000 -0.5922 0.05632 0.05358 -0.0405 1.0000 0.0219
-7.750 -0.5903 0.05208 0.04913 -0.0404 1.0000 0.0219
-7.500 -0.6156 0.03747 0.03404 -0.0396 1.0000 0.0156
-7.250 -0.6083 0.03324 0.02951 -0.0384 1.0000 0.0152
-7.000 -0.5991 0.02898 0.02486 -0.0367 1.0000 0.0149
-6.750 -0.5881 0.02509 0.02050 -0.0345 1.0000 0.0153
-6.500 -0.5763 0.02170 0.01667 -0.0321 1.0000 0.0154
-6.250 -0.5583 0.01843 0.01296 -0.0307 0.9993 0.0156
-6.000 -0.5254 0.01586 0.01008 -0.0321 0.9964 0.0164
-5.750 -0.4891 0.01563 0.00984 -0.0344 0.9930 0.0172
-5.500 -0.4541 0.01509 0.00923 -0.0361 0.9889 0.0184
-5.250 -0.4179 0.01435 0.00836 -0.0380 0.9855 0.0206
-5.000 -0.3812 0.01356 0.00749 -0.0402 0.9828 0.0233
-4.750 -0.3477 0.01306 0.00700 -0.0416 0.9771 0.0272
-4.500 -0.3135 0.01224 0.00611 -0.0433 0.9720 0.0327
-4.250 -0.2800 0.01177 0.00564 -0.0449 0.9659 0.0366
-4.000 -0.2479 0.01141 0.00523 -0.0459 0.9581 0.0385
-3.750 -0.2177 0.01115 0.00492 -0.0465 0.9490 0.0396
-3.500 -0.1896 0.01066 0.00438 -0.0466 0.9395 0.0414
-3.250 -0.1639 0.01014 0.00381 -0.0463 0.9283 0.0432
-3.000 -0.1381 0.00983 0.00345 -0.0459 0.9171 0.0442
-2.750 -0.1121 0.00956 0.00315 -0.0455 0.9065 0.0458
-2.500 -0.0859 0.00933 0.00286 -0.0452 0.8964 0.0461
-2.250 -0.0594 0.00915 0.00262 -0.0448 0.8857 0.0455
-2.000 -0.0326 0.00900 0.00241 -0.0445 0.8750 0.0449
-1.750 -0.0057 0.00887 0.00223 -0.0443 0.8651 0.0444
-1.500 0.0213 0.00876 0.00206 -0.0440 0.8556 0.0440
-1.250 0.0486 0.00865 0.00191 -0.0439 0.8451 0.0437
-1.000 0.0760 0.00857 0.00179 -0.0438 0.8350 0.0435
-0.750 0.1033 0.00851 0.00167 -0.0436 0.8254 0.0434
-0.500 0.1309 0.00845 0.00158 -0.0435 0.8153 0.0436
-0.250 0.1585 0.00841 0.00151 -0.0434 0.8055 0.0440
0.000 0.1861 0.00839 0.00145 -0.0433 0.7962 0.0450
0.250 0.2138 0.00835 0.00141 -0.0432 0.7861 0.0478
0.500 0.2394 0.00697 0.00129 -0.0439 0.7764 0.4698
0.750 0.2656 0.00653 0.00137 -0.0438 0.7674 0.6209
1.000 0.2912 0.00631 0.00150 -0.0432 0.7575 0.7196
1.250 0.3174 0.00626 0.00161 -0.0427 0.7464 0.7646
1.500 0.3436 0.00626 0.00171 -0.0422 0.7350 0.7967
1.750 0.3694 0.00627 0.00178 -0.0416 0.7202 0.8215
2.000 0.3935 0.00629 0.00179 -0.0404 0.6907 0.8468
2.250 0.4146 0.00633 0.00186 -0.0385 0.6612 0.8832
2.500 0.4353 0.00638 0.00194 -0.0365 0.6394 0.9123
2.750 0.4591 0.00643 0.00202 -0.0355 0.6183 0.9275
3.000 0.4821 0.00652 0.00206 -0.0343 0.5881 0.9430
3.250 0.5064 0.00668 0.00210 -0.0334 0.5391 0.9605
3.500 0.5348 0.00735 0.00225 -0.0340 0.4036 0.9804
3.750 0.5561 0.00929 0.00296 -0.0343 0.1298 1.0000
4.000 0.5796 0.01025 0.00350 -0.0341 0.0491 1.0000
4.250 0.6060 0.01074 0.00397 -0.0340 0.0381 1.0000
4.500 0.6303 0.01158 0.00484 -0.0336 0.0308 1.0000
4.750 0.6566 0.01200 0.00532 -0.0334 0.0288 1.0000
5.000 0.6820 0.01257 0.00593 -0.0331 0.0264 1.0000
5.250 0.7070 0.01315 0.00651 -0.0329 0.0240 1.0000
5.500 0.7278 0.01453 0.00795 -0.0319 0.0220 1.0000
5.750 0.7507 0.01577 0.00927 -0.0311 0.0212 1.0000
6.000 0.7757 0.01659 0.01018 -0.0307 0.0206 1.0000
6.250 0.8005 0.01766 0.01134 -0.0302 0.0199 1.0000
6.500 0.8254 0.01887 0.01266 -0.0297 0.0190 1.0000
6.750 0.8502 0.01980 0.01368 -0.0293 0.0178 1.0000
7.000 0.8745 0.02115 0.01515 -0.0289 0.0172 1.0000
7.250 0.8981 0.02276 0.01693 -0.0283 0.0167 1.0000
7.500 0.9205 0.02471 0.01908 -0.0276 0.0163 1.0000
7.750 0.9411 0.02717 0.02180 -0.0267 0.0161 1.0000
11.250 0.7008 0.10920 0.10731 -0.0320 0.0215 1.0000
11.500 0.6926 0.11704 0.11515 -0.0361 0.0215 1.0000
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Polar data table (+)
Polar graphs
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