NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 100,000 Max Cl/Cd: 51.88 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642415-il-100000.txt Download as CSV file: xf-naca642415-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4133 0.10081 0.09575 -0.0466 1.0000 0.1734
-10.250 -0.3921 0.09851 0.09343 -0.0446 1.0000 0.1782
-10.000 -0.4383 0.09364 0.08878 -0.0496 1.0000 0.1881
-9.750 -0.3961 0.09221 0.08726 -0.0450 1.0000 0.1937
-9.500 -0.5088 0.08698 0.08245 -0.0520 1.0000 0.2031
-9.250 -0.4074 0.08617 0.08139 -0.0445 1.0000 0.2091
-9.000 -0.4882 0.08345 0.07903 -0.0451 1.0000 0.2186
-8.500 -0.7529 0.05756 0.05195 -0.0425 0.9994 0.0972
-8.250 -0.7345 0.05047 0.04378 -0.0455 0.9919 0.0826
-8.000 -0.7077 0.04522 0.03833 -0.0481 0.9861 0.0809
-7.750 -0.6794 0.04152 0.03414 -0.0505 0.9796 0.0806
-7.500 -0.6478 0.03875 0.03081 -0.0528 0.9726 0.0818
-7.250 -0.6160 0.03635 0.02793 -0.0546 0.9660 0.0824
-7.000 -0.5830 0.03354 0.02481 -0.0564 0.9598 0.0836
-6.750 -0.5423 0.03144 0.02268 -0.0596 0.9555 0.0875
-6.500 -0.5150 0.03022 0.02133 -0.0600 0.9470 0.0911
-6.250 -0.4740 0.02883 0.01966 -0.0624 0.9419 0.0951
-6.000 -0.4430 0.02737 0.01832 -0.0633 0.9353 0.1006
-5.750 -0.4087 0.02644 0.01732 -0.0647 0.9284 0.1083
-5.500 -0.3674 0.02512 0.01618 -0.0673 0.9245 0.1192
-5.250 -0.3474 0.02434 0.01552 -0.0664 0.9150 0.1315
-5.000 -0.3116 0.02305 0.01447 -0.0685 0.9098 0.1613
-4.750 -0.2993 0.02035 0.01331 -0.0683 0.9012 0.3623
-4.500 -0.2705 0.02097 0.01448 -0.0671 0.8945 0.5726
-4.250 -0.2303 0.02196 0.01545 -0.0673 0.8908 0.6138
-4.000 -0.2169 0.02270 0.01616 -0.0638 0.8800 0.6356
-3.750 -0.1817 0.02357 0.01696 -0.0630 0.8757 0.6608
-3.500 -0.1685 0.02439 0.01777 -0.0591 0.8662 0.6781
-3.250 -0.1419 0.02530 0.01867 -0.0565 0.8609 0.6980
-3.000 -0.1096 0.02618 0.01949 -0.0544 0.8576 0.7195
-2.750 -0.1052 0.02680 0.02010 -0.0494 0.8467 0.7331
-2.500 -0.0717 0.02692 0.02011 -0.0493 0.8427 0.7464
-2.250 -0.0590 0.02701 0.02011 -0.0475 0.8335 0.7567
-2.000 -0.0317 0.02697 0.01999 -0.0471 0.8282 0.7631
-1.750 0.0048 0.02673 0.01964 -0.0487 0.8249 0.7705
-1.500 0.0103 0.02695 0.01982 -0.0462 0.8150 0.7778
-1.250 0.0410 0.02684 0.01964 -0.0466 0.8105 0.7840
-1.000 0.0801 0.02648 0.01916 -0.0491 0.8076 0.7919
-0.750 0.0790 0.02703 0.01973 -0.0450 0.7970 0.7978
-0.500 0.1110 0.02690 0.01952 -0.0462 0.7933 0.8049
-0.250 0.1473 0.02668 0.01924 -0.0478 0.7908 0.8107
0.000 0.1428 0.02744 0.02002 -0.0439 0.7802 0.8181
0.250 0.1772 0.02728 0.01981 -0.0455 0.7765 0.8253
0.500 0.2117 0.02712 0.01962 -0.0463 0.7742 0.8305
0.750 0.2036 0.02824 0.02076 -0.0431 0.7637 0.8404
1.000 0.2318 0.02819 0.02072 -0.0428 0.7601 0.8468
1.250 0.2693 0.02803 0.02053 -0.0444 0.7578 0.8546
1.500 0.2501 0.02942 0.02198 -0.0391 0.7469 0.8645
1.750 0.2846 0.02939 0.02194 -0.0404 0.7437 0.8732
2.000 0.3193 0.02919 0.02176 -0.0409 0.7414 0.8813
2.250 0.2930 0.03078 0.02340 -0.0348 0.7300 0.8960
2.500 0.3278 0.03068 0.02333 -0.0358 0.7268 0.9064
2.750 0.3705 0.03039 0.02307 -0.0377 0.7248 0.9163
3.000 0.3450 0.03222 0.02497 -0.0324 0.7133 0.9370
3.250 0.3885 0.03210 0.02489 -0.0348 0.7102 0.9498
3.500 0.4372 0.03215 0.02502 -0.0385 0.7069 0.9619
3.750 0.4629 0.03377 0.02675 -0.0420 0.6971 0.9808
4.000 0.5269 0.03346 0.02654 -0.0478 0.6941 0.9897
4.250 0.5960 0.03272 0.02589 -0.0538 0.6923 0.9962
4.500 0.5553 0.03499 0.02812 -0.0478 0.6785 1.0000
4.750 0.5927 0.03509 0.02828 -0.0498 0.6730 1.0000
5.000 0.6119 0.03598 0.02922 -0.0503 0.6630 1.0000
5.250 0.6771 0.03430 0.02766 -0.0536 0.6605 1.0000
5.500 0.6834 0.03581 0.02922 -0.0528 0.6472 1.0000
5.750 0.7559 0.03319 0.02676 -0.0559 0.6447 1.0000
6.000 0.7796 0.03331 0.02696 -0.0556 0.6322 1.0000
6.250 0.8788 0.02765 0.02143 -0.0593 0.6275 1.0000
6.500 0.9185 0.02609 0.01997 -0.0594 0.6130 1.0000
6.750 0.9685 0.02359 0.01748 -0.0599 0.5955 1.0000
7.000 0.9999 0.02246 0.01642 -0.0592 0.5755 1.0000
7.250 1.0262 0.02168 0.01572 -0.0581 0.5529 1.0000
7.500 1.0512 0.02093 0.01501 -0.0566 0.5259 1.0000
7.750 1.0667 0.02061 0.01475 -0.0541 0.4887 1.0000
8.000 1.0723 0.02067 0.01472 -0.0502 0.4229 1.0000
8.250 1.0576 0.02192 0.01508 -0.0437 0.3079 1.0000
8.500 1.0349 0.02444 0.01689 -0.0379 0.2287 1.0000
8.750 1.0172 0.02725 0.01916 -0.0337 0.1772 1.0000
9.000 1.0092 0.02978 0.02132 -0.0307 0.1462 1.0000
9.250 1.0105 0.03189 0.02321 -0.0285 0.1257 1.0000
9.500 1.0186 0.03367 0.02484 -0.0269 0.1115 1.0000
9.750 1.0333 0.03528 0.02627 -0.0257 0.1007 1.0000
10.000 1.0515 0.03669 0.02762 -0.0248 0.0918 1.0000
10.250 1.0793 0.03812 0.02905 -0.0244 0.0845 1.0000
10.500 1.1191 0.03985 0.03051 -0.0253 0.0770 1.0000
10.750 1.1416 0.04145 0.03238 -0.0247 0.0731 1.0000
11.000 1.1741 0.04339 0.03442 -0.0252 0.0695 1.0000
11.250 1.2218 0.04659 0.03759 -0.0277 0.0655 1.0000
11.500 1.2300 0.04866 0.04001 -0.0259 0.0639 1.0000
11.750 1.2412 0.05123 0.04292 -0.0246 0.0625 1.0000
12.000 1.2499 0.05417 0.04618 -0.0233 0.0617 1.0000
12.250 1.2529 0.05731 0.04966 -0.0217 0.0613 1.0000
12.500 1.2505 0.06067 0.05334 -0.0199 0.0611 1.0000
12.750 1.2429 0.06431 0.05731 -0.0182 0.0613 1.0000
13.000 1.2301 0.06822 0.06153 -0.0167 0.0614 1.0000
13.250 1.2135 0.07247 0.06608 -0.0155 0.0617 1.0000
13.500 1.1933 0.07713 0.07102 -0.0150 0.0620 1.0000
13.750 1.1707 0.08229 0.07645 -0.0151 0.0625 1.0000
14.000 1.1459 0.08802 0.08243 -0.0160 0.0630 1.0000
14.250 1.1204 0.09431 0.08894 -0.0178 0.0636 1.0000
14.500 1.0944 0.10121 0.09603 -0.0203 0.0643 1.0000
14.750 1.0708 0.10852 0.10349 -0.0234 0.0649 1.0000
15.000 1.0537 0.11589 0.11096 -0.0266 0.0656 1.0000
15.250 0.6934 0.17091 0.16688 -0.0553 0.1443 1.0000
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