NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.07 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64208-il-1000000-n5.txt Download as CSV file: xf-naca64208-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5869 0.10223 0.10059 -0.0053 1.0000 0.0031
-10.250 -0.5829 0.09888 0.09725 -0.0071 1.0000 0.0033
-9.250 -0.8249 0.02163 0.01811 -0.0380 1.0000 0.0030
-9.000 -0.8058 0.01968 0.01589 -0.0375 1.0000 0.0032
-8.750 -0.7839 0.01855 0.01461 -0.0370 1.0000 0.0033
-8.500 -0.7609 0.01770 0.01364 -0.0367 1.0000 0.0035
-8.250 -0.7384 0.01669 0.01246 -0.0362 1.0000 0.0037
-8.000 -0.7155 0.01581 0.01144 -0.0357 1.0000 0.0040
-7.750 -0.6929 0.01487 0.01035 -0.0351 1.0000 0.0042
-7.500 -0.6678 0.01399 0.00932 -0.0350 0.9988 0.0045
-7.250 -0.6369 0.01321 0.00842 -0.0361 0.9936 0.0047
-7.000 -0.6055 0.01255 0.00764 -0.0372 0.9881 0.0049
-6.750 -0.5746 0.01164 0.00662 -0.0384 0.9814 0.0055
-6.500 -0.5421 0.01127 0.00623 -0.0397 0.9742 0.0060
-6.250 -0.5099 0.01103 0.00595 -0.0409 0.9652 0.0067
-6.000 -0.4794 0.01075 0.00562 -0.0417 0.9539 0.0075
-5.750 -0.4512 0.01042 0.00521 -0.0419 0.9412 0.0079
-5.500 -0.4243 0.01016 0.00487 -0.0418 0.9279 0.0082
-5.250 -0.3992 0.00945 0.00402 -0.0414 0.9144 0.0094
-5.000 -0.3729 0.00920 0.00370 -0.0412 0.9019 0.0102
-4.750 -0.3463 0.00901 0.00346 -0.0410 0.8899 0.0110
-4.500 -0.3196 0.00881 0.00320 -0.0409 0.8783 0.0119
-4.250 -0.2929 0.00856 0.00287 -0.0407 0.8669 0.0124
-3.750 -0.2387 0.00818 0.00234 -0.0405 0.8449 0.0133
-3.500 -0.2115 0.00785 0.00191 -0.0404 0.8345 0.0160
-3.250 -0.1841 0.00769 0.00172 -0.0404 0.8242 0.0188
-2.750 -0.1289 0.00745 0.00139 -0.0404 0.8042 0.0256
-2.500 -0.1012 0.00733 0.00125 -0.0404 0.7944 0.0316
-2.250 -0.0736 0.00723 0.00113 -0.0404 0.7841 0.0396
-2.000 -0.0459 0.00705 0.00101 -0.0405 0.7739 0.0675
-1.750 -0.0187 0.00659 0.00087 -0.0407 0.7645 0.1697
-1.500 0.0085 0.00611 0.00072 -0.0409 0.7551 0.2900
-1.250 0.0355 0.00561 0.00061 -0.0412 0.7451 0.4227
-1.000 0.0629 0.00532 0.00057 -0.0413 0.7351 0.5147
-0.750 0.0901 0.00504 0.00057 -0.0414 0.7255 0.6087
-0.250 0.1456 0.00489 0.00059 -0.0414 0.7072 0.6842
0.000 0.1736 0.00489 0.00060 -0.0414 0.6982 0.6973
0.250 0.2016 0.00491 0.00061 -0.0415 0.6872 0.7080
0.500 0.2294 0.00496 0.00062 -0.0415 0.6694 0.7175
0.750 0.2567 0.00505 0.00064 -0.0414 0.6425 0.7277
1.000 0.2841 0.00514 0.00068 -0.0413 0.6161 0.7382
1.250 0.3110 0.00530 0.00073 -0.0412 0.5755 0.7487
1.500 0.3373 0.00557 0.00080 -0.0410 0.5138 0.7591
1.750 0.3638 0.00585 0.00089 -0.0408 0.4548 0.7695
2.000 0.3881 0.00649 0.00110 -0.0405 0.3292 0.7801
2.250 0.4118 0.00731 0.00140 -0.0402 0.1830 0.7912
2.500 0.4371 0.00785 0.00164 -0.0400 0.0946 0.8025
3.000 0.4902 0.00838 0.00200 -0.0397 0.0370 0.8246
3.250 0.5170 0.00855 0.00220 -0.0396 0.0287 0.8359
3.500 0.5439 0.00869 0.00238 -0.0395 0.0252 0.8477
3.750 0.5704 0.00888 0.00258 -0.0393 0.0201 0.8598
4.000 0.5967 0.00908 0.00283 -0.0390 0.0164 0.8727
4.250 0.6227 0.00926 0.00307 -0.0386 0.0152 0.8862
4.500 0.6482 0.00946 0.00335 -0.0382 0.0140 0.9010
4.750 0.6731 0.00968 0.00363 -0.0376 0.0129 0.9170
5.000 0.6972 0.00995 0.00395 -0.0369 0.0119 0.9351
5.250 0.7206 0.01039 0.00452 -0.0360 0.0105 0.9585
5.500 0.7500 0.01081 0.00501 -0.0365 0.0100 1.0000
5.750 0.7762 0.01118 0.00545 -0.0364 0.0098 1.0000
6.000 0.8024 0.01155 0.00585 -0.0363 0.0094 1.0000
6.250 0.8285 0.01190 0.00624 -0.0361 0.0088 1.0000
6.500 0.8544 0.01227 0.00664 -0.0360 0.0082 1.0000
6.750 0.8801 0.01268 0.00709 -0.0358 0.0077 1.0000
7.000 0.9058 0.01305 0.00749 -0.0356 0.0073 1.0000
7.250 0.9309 0.01352 0.00798 -0.0354 0.0067 1.0000
7.500 0.9536 0.01447 0.00906 -0.0348 0.0060 1.0000
7.750 0.9796 0.01472 0.00935 -0.0347 0.0058 1.0000
8.000 1.0048 0.01513 0.00981 -0.0345 0.0054 1.0000
8.250 1.0295 0.01559 0.01032 -0.0342 0.0049 1.0000
8.500 1.0539 0.01610 0.01089 -0.0339 0.0045 1.0000
8.750 1.0786 0.01653 0.01135 -0.0337 0.0042 1.0000
9.000 1.1028 0.01703 0.01189 -0.0334 0.0039 1.0000
9.250 1.1237 0.01817 0.01317 -0.0326 0.0035 1.0000
9.500 1.1460 0.01902 0.01416 -0.0320 0.0034 1.0000
9.750 1.1678 0.01989 0.01517 -0.0315 0.0032 1.0000
10.000 1.1887 0.02091 0.01633 -0.0308 0.0031 1.0000
10.250 1.2087 0.02204 0.01762 -0.0300 0.0030 1.0000
10.500 1.2279 0.02326 0.01900 -0.0292 0.0028 1.0000
10.750 1.2465 0.02447 0.02037 -0.0283 0.0027 1.0000
11.000 1.2640 0.02578 0.02184 -0.0274 0.0025 1.0000
11.250 1.2802 0.02719 0.02342 -0.0264 0.0024 1.0000
11.500 1.2946 0.02875 0.02516 -0.0252 0.0023 1.0000
11.750 1.3079 0.03033 0.02690 -0.0239 0.0022 1.0000
12.000 1.3157 0.03249 0.02929 -0.0222 0.0022 1.0000
12.250 1.3190 0.03496 0.03201 -0.0202 0.0021 1.0000
12.500 1.3122 0.03775 0.03504 -0.0171 0.0020 1.0000
12.750 1.2969 0.04091 0.03844 -0.0136 0.0020 1.0000
13.000 1.2714 0.04556 0.04336 -0.0112 0.0020 1.0000
13.250 1.2382 0.05187 0.04995 -0.0108 0.0020 1.0000
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Polar data table (+)
Polar graphs
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