NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 100,000 Max Cl/Cd: 43.43 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64209-il-100000-n5.txt Download as CSV file: xf-naca64209-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4515 0.11341 0.10860 -0.0102 1.0000 0.0421
-10.750 -0.4517 0.10921 0.10441 -0.0118 1.0000 0.0424
-10.500 -0.5618 0.10771 0.10257 -0.0126 1.0000 0.0266
-10.250 -0.5584 0.10377 0.09864 -0.0132 1.0000 0.0260
-10.000 -0.5563 0.09969 0.09459 -0.0147 1.0000 0.0254
-9.750 -0.5571 0.09487 0.08981 -0.0171 1.0000 0.0252
-9.500 -0.5601 0.08930 0.08429 -0.0207 1.0000 0.0255
-9.250 -0.5627 0.08395 0.07899 -0.0242 1.0000 0.0253
-9.000 -0.5668 0.07834 0.07342 -0.0283 1.0000 0.0245
-8.750 -0.5776 0.07227 0.06737 -0.0334 1.0000 0.0246
-8.500 -0.5895 0.06756 0.06262 -0.0359 1.0000 0.0243
-8.250 -0.5965 0.06284 0.05777 -0.0378 1.0000 0.0242
-8.000 -0.6001 0.05823 0.05296 -0.0389 1.0000 0.0248
-7.750 -0.6001 0.05370 0.04816 -0.0394 1.0000 0.0252
-7.500 -0.5965 0.04933 0.04343 -0.0393 1.0000 0.0256
-7.250 -0.5893 0.04522 0.03894 -0.0388 1.0000 0.0257
-7.000 -0.5788 0.04148 0.03478 -0.0380 1.0000 0.0259
-6.750 -0.5659 0.03806 0.03085 -0.0369 1.0000 0.0263
-6.500 -0.5505 0.03536 0.02756 -0.0356 1.0000 0.0269
-6.250 -0.5357 0.03198 0.02397 -0.0348 1.0000 0.0281
-6.000 -0.5181 0.03029 0.02222 -0.0341 1.0000 0.0306
-5.750 -0.4992 0.02836 0.01995 -0.0329 1.0000 0.0328
-5.500 -0.4792 0.02627 0.01742 -0.0316 1.0000 0.0344
-5.250 -0.4585 0.02462 0.01538 -0.0301 1.0000 0.0362
-5.000 -0.4390 0.02243 0.01307 -0.0289 1.0000 0.0386
-4.750 -0.4197 0.02120 0.01179 -0.0277 1.0000 0.0424
-4.500 -0.4001 0.02034 0.01079 -0.0264 1.0000 0.0464
-4.250 -0.3814 0.01942 0.00986 -0.0253 1.0000 0.0505
-4.000 -0.3506 0.01860 0.00897 -0.0264 0.9950 0.0529
-3.750 -0.3156 0.01797 0.00826 -0.0283 0.9879 0.0565
-3.500 -0.2807 0.01739 0.00758 -0.0301 0.9807 0.0583
-3.250 -0.2446 0.01686 0.00694 -0.0322 0.9740 0.0587
-3.000 -0.2097 0.01640 0.00636 -0.0340 0.9663 0.0593
-2.750 -0.1739 0.01599 0.00586 -0.0359 0.9592 0.0605
-2.500 -0.1380 0.01567 0.00546 -0.0377 0.9520 0.0622
-2.250 -0.1043 0.01540 0.00513 -0.0391 0.9436 0.0649
-2.000 -0.0687 0.01515 0.00482 -0.0408 0.9364 0.0707
-1.750 -0.0376 0.01470 0.00456 -0.0418 0.9270 0.1093
-1.500 -0.0152 0.01268 0.00462 -0.0417 0.9187 0.6019
-1.250 0.0132 0.01257 0.00467 -0.0414 0.9095 0.6657
-1.000 0.0410 0.01254 0.00470 -0.0410 0.8998 0.7067
-0.750 0.0696 0.01252 0.00475 -0.0406 0.8915 0.7447
-0.500 0.0975 0.01253 0.00474 -0.0404 0.8814 0.7615
-0.250 0.1250 0.01255 0.00474 -0.0401 0.8718 0.7796
0.000 0.1531 0.01255 0.00475 -0.0397 0.8635 0.7986
0.250 0.1777 0.01258 0.00483 -0.0387 0.8531 0.8220
0.500 0.1997 0.01260 0.00496 -0.0367 0.8435 0.8578
0.750 0.2262 0.01260 0.00499 -0.0360 0.8353 0.8790
1.000 0.2512 0.01261 0.00508 -0.0349 0.8253 0.9071
1.250 0.2868 0.01255 0.00512 -0.0357 0.8176 0.9478
1.500 0.3279 0.01253 0.00517 -0.0384 0.8091 0.9681
1.750 0.3662 0.01255 0.00525 -0.0407 0.8000 0.9822
2.000 0.4041 0.01255 0.00532 -0.0429 0.7919 0.9997
2.250 0.4256 0.01269 0.00552 -0.0420 0.7808 1.0000
2.500 0.4490 0.01281 0.00570 -0.0413 0.7695 1.0000
2.750 0.4735 0.01292 0.00586 -0.0406 0.7577 1.0000
3.000 0.4984 0.01301 0.00603 -0.0399 0.7437 1.0000
3.250 0.5203 0.01287 0.00587 -0.0378 0.7085 1.0000
3.500 0.5390 0.01272 0.00545 -0.0348 0.6357 1.0000
3.750 0.5600 0.01291 0.00539 -0.0329 0.5611 1.0000
4.000 0.5807 0.01337 0.00552 -0.0313 0.4590 1.0000
4.250 0.5888 0.01560 0.00617 -0.0288 0.1743 1.0000
4.500 0.6064 0.01716 0.00714 -0.0277 0.0819 1.0000
4.750 0.6278 0.01817 0.00807 -0.0269 0.0634 1.0000
5.000 0.6502 0.01902 0.00895 -0.0262 0.0528 1.0000
5.250 0.6710 0.02011 0.01009 -0.0252 0.0480 1.0000
5.500 0.6928 0.02112 0.01122 -0.0243 0.0438 1.0000
5.750 0.7146 0.02218 0.01231 -0.0236 0.0391 1.0000
6.000 0.7359 0.02378 0.01390 -0.0228 0.0363 1.0000
6.250 0.7603 0.02521 0.01548 -0.0222 0.0349 1.0000
6.500 0.7855 0.02690 0.01736 -0.0216 0.0335 1.0000
6.750 0.8108 0.02884 0.01953 -0.0211 0.0323 1.0000
7.000 0.8352 0.03097 0.02194 -0.0205 0.0311 1.0000
7.250 0.8572 0.03274 0.02395 -0.0199 0.0289 1.0000
7.500 0.8774 0.03472 0.02612 -0.0194 0.0270 1.0000
7.750 0.8957 0.03777 0.02951 -0.0186 0.0262 1.0000
8.000 0.9099 0.04172 0.03388 -0.0175 0.0257 1.0000
8.250 0.9210 0.04545 0.03805 -0.0161 0.0254 1.0000
8.500 0.9296 0.04900 0.04208 -0.0146 0.0252 1.0000
8.750 0.9346 0.05246 0.04601 -0.0130 0.0248 1.0000
9.000 0.9349 0.05611 0.05012 -0.0113 0.0241 1.0000
9.250 0.9301 0.06006 0.05446 -0.0097 0.0234 1.0000
9.500 0.9207 0.06412 0.05880 -0.0084 0.0231 1.0000
9.750 0.9049 0.06795 0.06283 -0.0070 0.0230 1.0000
10.000 0.8874 0.07218 0.06722 -0.0071 0.0231 1.0000
10.250 0.8681 0.07726 0.07244 -0.0089 0.0231 1.0000
10.500 0.8498 0.08323 0.07851 -0.0123 0.0235 1.0000
10.750 0.8317 0.09054 0.08590 -0.0174 0.0237 1.0000
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Polar data table (+)
Polar graphs
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