NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 200,000 Max Cl/Cd: 53.84 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64209-il-200000-n5.txt Download as CSV file: xf-naca64209-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5732 0.08411 0.08057 -0.0207 1.0000 0.0141
-9.250 -0.5803 0.07775 0.07427 -0.0252 1.0000 0.0139
-9.000 -0.5952 0.06946 0.06601 -0.0329 1.0000 0.0135
-8.750 -0.6154 0.06342 0.05994 -0.0368 1.0000 0.0133
-8.500 -0.6301 0.05698 0.05331 -0.0391 1.0000 0.0131
-8.250 -0.6395 0.05042 0.04647 -0.0400 1.0000 0.0129
-8.000 -0.6392 0.04532 0.04106 -0.0400 1.0000 0.0129
-7.750 -0.6340 0.04074 0.03616 -0.0395 1.0000 0.0130
-7.500 -0.6245 0.03686 0.03192 -0.0387 1.0000 0.0133
-7.250 -0.6122 0.03333 0.02802 -0.0377 1.0000 0.0137
-7.000 -0.5980 0.03005 0.02431 -0.0365 1.0000 0.0141
-6.750 -0.5826 0.02653 0.02022 -0.0350 1.0000 0.0156
-6.500 -0.5634 0.02543 0.01896 -0.0340 1.0000 0.0165
-6.250 -0.5443 0.02413 0.01746 -0.0329 1.0000 0.0173
-6.000 -0.5254 0.02241 0.01545 -0.0315 1.0000 0.0184
-5.750 -0.5010 0.02040 0.01302 -0.0309 0.9980 0.0201
-5.500 -0.4675 0.01948 0.01199 -0.0326 0.9921 0.0219
-5.250 -0.4329 0.01871 0.01100 -0.0343 0.9865 0.0254
-5.000 -0.4003 0.01741 0.00952 -0.0356 0.9804 0.0282
-4.750 -0.3668 0.01640 0.00850 -0.0373 0.9749 0.0312
-4.500 -0.3350 0.01573 0.00774 -0.0384 0.9671 0.0334
-4.250 -0.3020 0.01515 0.00705 -0.0397 0.9600 0.0348
-4.000 -0.2694 0.01460 0.00644 -0.0410 0.9523 0.0353
-3.750 -0.2374 0.01428 0.00605 -0.0420 0.9439 0.0366
-3.500 -0.2059 0.01360 0.00534 -0.0431 0.9360 0.0379
-3.250 -0.1767 0.01309 0.00478 -0.0437 0.9259 0.0393
-3.000 -0.1474 0.01269 0.00434 -0.0442 0.9164 0.0412
-2.750 -0.1179 0.01239 0.00398 -0.0446 0.9072 0.0419
-2.500 -0.0901 0.01216 0.00369 -0.0446 0.8965 0.0419
-2.250 -0.0624 0.01196 0.00341 -0.0446 0.8863 0.0419
-2.000 -0.0347 0.01179 0.00317 -0.0445 0.8766 0.0420
-1.750 -0.0075 0.01164 0.00296 -0.0443 0.8663 0.0423
-1.500 0.0196 0.01151 0.00279 -0.0442 0.8561 0.0427
-1.250 0.0468 0.01140 0.00262 -0.0440 0.8465 0.0433
-1.000 0.0739 0.01131 0.00249 -0.0438 0.8367 0.0443
-0.750 0.1011 0.01122 0.00238 -0.0436 0.8265 0.0457
-0.500 0.1283 0.01115 0.00230 -0.0434 0.8172 0.0482
-0.250 0.1510 0.00946 0.00214 -0.0437 0.8079 0.4935
0.000 0.1773 0.00928 0.00218 -0.0433 0.7982 0.5599
0.250 0.2027 0.00910 0.00228 -0.0427 0.7891 0.6353
0.500 0.2281 0.00901 0.00239 -0.0420 0.7796 0.6905
0.750 0.2540 0.00898 0.00249 -0.0414 0.7705 0.7239
1.000 0.2795 0.00898 0.00259 -0.0406 0.7620 0.7562
1.250 0.3037 0.00897 0.00274 -0.0395 0.7523 0.7958
1.500 0.3297 0.00900 0.00285 -0.0390 0.7437 0.8128
1.750 0.3554 0.00905 0.00295 -0.0383 0.7350 0.8304
2.000 0.3792 0.00907 0.00307 -0.0371 0.7244 0.8558
2.250 0.3998 0.00906 0.00320 -0.0350 0.7130 0.8953
2.500 0.4229 0.00905 0.00326 -0.0335 0.6972 0.9245
2.750 0.4484 0.00907 0.00317 -0.0326 0.6573 0.9403
3.000 0.4752 0.00923 0.00306 -0.0320 0.5888 0.9574
3.250 0.5070 0.00944 0.00315 -0.0329 0.5354 0.9766
3.500 0.5341 0.00992 0.00327 -0.0331 0.4371 1.0000
3.750 0.5484 0.01154 0.00380 -0.0316 0.2147 1.0000
4.000 0.5681 0.01278 0.00441 -0.0310 0.0904 1.0000
4.250 0.5915 0.01355 0.00496 -0.0306 0.0529 1.0000
4.500 0.6164 0.01411 0.00555 -0.0304 0.0427 1.0000
4.750 0.6406 0.01478 0.00623 -0.0300 0.0357 1.0000
5.000 0.6654 0.01533 0.00685 -0.0296 0.0314 1.0000
5.250 0.6892 0.01604 0.00761 -0.0292 0.0285 1.0000
5.500 0.7104 0.01717 0.00879 -0.0284 0.0260 1.0000
5.750 0.7328 0.01818 0.00988 -0.0277 0.0249 1.0000
6.000 0.7561 0.01918 0.01096 -0.0270 0.0240 1.0000
6.250 0.7795 0.02033 0.01221 -0.0264 0.0231 1.0000
6.500 0.8036 0.02136 0.01337 -0.0259 0.0216 1.0000
6.750 0.8276 0.02235 0.01446 -0.0255 0.0201 1.0000
7.000 0.8512 0.02363 0.01586 -0.0250 0.0192 1.0000
7.250 0.8742 0.02507 0.01744 -0.0245 0.0184 1.0000
7.500 0.8963 0.02697 0.01953 -0.0239 0.0177 1.0000
7.750 0.9153 0.03022 0.02309 -0.0231 0.0168 1.0000
8.000 0.9362 0.03159 0.02482 -0.0222 0.0160 1.0000
8.250 0.9542 0.03388 0.02751 -0.0211 0.0150 1.0000
8.500 0.9679 0.03709 0.03117 -0.0196 0.0144 1.0000
8.750 0.9776 0.04070 0.03523 -0.0180 0.0139 1.0000
9.000 0.9824 0.04473 0.03969 -0.0161 0.0136 1.0000
9.250 0.9821 0.04904 0.04439 -0.0142 0.0134 1.0000
9.500 0.9770 0.05336 0.04905 -0.0123 0.0132 1.0000
9.750 0.9700 0.05695 0.05291 -0.0107 0.0129 1.0000
10.000 0.9525 0.06091 0.05708 -0.0085 0.0129 1.0000
10.250 0.9350 0.06484 0.06116 -0.0078 0.0127 1.0000
10.500 0.9065 0.07136 0.06788 -0.0095 0.0131 1.0000
10.750 0.8797 0.07895 0.07562 -0.0138 0.0133 1.0000
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Polar data table (+)
Polar graphs
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