NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 100,000 Max Cl/Cd: 32.85 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215b-il-100000.txt Download as CSV file: xf-n63215b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6313 0.08733 0.08191 -0.0404 1.0000 0.0804
-12.000 -0.6441 0.08080 0.07536 -0.0432 1.0000 0.0787
-11.750 -0.6834 0.07249 0.06692 -0.0481 1.0000 0.0765
-11.500 -0.7315 0.06517 0.05936 -0.0514 1.0000 0.0741
-11.250 -0.8231 0.05955 0.05310 -0.0493 1.0000 0.0707
-11.000 -0.8392 0.05716 0.05036 -0.0469 1.0000 0.0700
-10.750 -0.8419 0.05390 0.04683 -0.0453 1.0000 0.0698
-10.500 -0.8426 0.05057 0.04324 -0.0436 1.0000 0.0697
-10.250 -0.8416 0.04732 0.03970 -0.0418 1.0000 0.0700
-10.000 -0.8328 0.04374 0.03601 -0.0407 1.0000 0.0711
-9.750 -0.8166 0.04182 0.03417 -0.0398 1.0000 0.0735
-9.500 -0.8067 0.04004 0.03228 -0.0379 1.0000 0.0753
-9.250 -0.8009 0.03832 0.03038 -0.0353 1.0000 0.0771
-9.000 -0.7979 0.03689 0.02870 -0.0321 1.0000 0.0789
-8.750 -0.7972 0.03575 0.02730 -0.0284 1.0000 0.0806
-8.500 -0.7933 0.03428 0.02562 -0.0252 1.0000 0.0822
-8.250 -0.7821 0.03257 0.02397 -0.0231 1.0000 0.0843
-8.000 -0.7723 0.03149 0.02287 -0.0207 1.0000 0.0868
-7.750 -0.7618 0.03053 0.02184 -0.0184 1.0000 0.0898
-7.500 -0.7498 0.02959 0.02074 -0.0162 1.0000 0.0927
-7.250 -0.7356 0.02846 0.01949 -0.0142 1.0000 0.0952
-7.000 -0.7203 0.02729 0.01847 -0.0126 1.0000 0.0987
-6.750 -0.7064 0.02655 0.01775 -0.0108 1.0000 0.1033
-6.500 -0.6787 0.02559 0.01674 -0.0112 0.9968 0.1098
-6.250 -0.6427 0.02452 0.01585 -0.0133 0.9911 0.1194
-6.000 -0.6109 0.02344 0.01493 -0.0148 0.9844 0.1339
-5.750 -0.5791 0.02208 0.01390 -0.0167 0.9786 0.1649
-5.500 -0.5632 0.01950 0.01250 -0.0171 0.9710 0.2958
-5.250 -0.5346 0.01906 0.01289 -0.0177 0.9645 0.4750
-5.000 -0.5050 0.01952 0.01335 -0.0178 0.9569 0.5248
-4.750 -0.4676 0.02020 0.01400 -0.0190 0.9515 0.5596
-4.500 -0.4441 0.02087 0.01470 -0.0174 0.9440 0.5821
-4.250 -0.4095 0.02168 0.01547 -0.0178 0.9386 0.6087
-4.000 -0.3853 0.02255 0.01639 -0.0160 0.9317 0.6273
-3.750 -0.3558 0.02336 0.01721 -0.0151 0.9257 0.6448
-3.500 -0.3186 0.02405 0.01785 -0.0158 0.9218 0.6607
-3.250 -0.3041 0.02439 0.01815 -0.0133 0.9136 0.6746
-3.000 -0.2710 0.02504 0.01878 -0.0131 0.9083 0.6900
-2.750 -0.2466 0.02571 0.01947 -0.0110 0.9013 0.7003
-2.500 -0.2091 0.02573 0.01942 -0.0124 0.8932 0.7109
-2.250 -0.1740 0.02572 0.01934 -0.0133 0.8838 0.7207
-2.000 -0.1224 0.02566 0.01922 -0.0161 0.8757 0.7290
-1.750 -0.0969 0.02542 0.01890 -0.0160 0.8648 0.7402
-1.500 -0.0481 0.02528 0.01873 -0.0179 0.8582 0.7456
-1.250 -0.0304 0.02513 0.01853 -0.0166 0.8472 0.7553
-1.000 0.0121 0.02487 0.01825 -0.0178 0.8413 0.7614
-0.750 0.0301 0.02477 0.01814 -0.0162 0.8298 0.7702
-0.500 0.0626 0.02444 0.01778 -0.0159 0.8204 0.7774
-0.250 0.0945 0.02403 0.01735 -0.0154 0.8100 0.7853
0.000 0.1181 0.02368 0.01699 -0.0141 0.7975 0.7931
0.250 0.1468 0.02327 0.01656 -0.0130 0.7865 0.8001
0.500 0.1775 0.02265 0.01590 -0.0123 0.7758 0.8085
0.750 0.2010 0.02228 0.01555 -0.0104 0.7620 0.8158
1.000 0.2256 0.02174 0.01500 -0.0090 0.7477 0.8246
1.250 0.2513 0.02123 0.01448 -0.0072 0.7328 0.8320
1.500 0.2762 0.02061 0.01385 -0.0055 0.7164 0.8413
1.750 0.3020 0.01999 0.01321 -0.0035 0.6974 0.8497
2.000 0.3276 0.01928 0.01245 -0.0018 0.6753 0.8586
2.250 0.3504 0.01864 0.01178 0.0004 0.6437 0.8676
2.500 0.3711 0.01808 0.01113 0.0028 0.5961 0.8768
2.750 0.3885 0.01774 0.01050 0.0055 0.5236 0.8880
3.000 0.4073 0.01791 0.01012 0.0078 0.4455 0.8970
3.250 0.4260 0.01832 0.01007 0.0094 0.4016 0.9076
3.500 0.4470 0.01878 0.01022 0.0105 0.3736 0.9194
3.750 0.4804 0.01949 0.01057 0.0095 0.3511 0.9279
4.000 0.5133 0.02012 0.01103 0.0083 0.3329 0.9381
4.250 0.5495 0.02074 0.01152 0.0064 0.3161 0.9481
4.500 0.5915 0.02137 0.01203 0.0034 0.3001 0.9561
4.750 0.6315 0.02199 0.01250 0.0006 0.2866 0.9655
5.000 0.6797 0.02258 0.01311 -0.0038 0.2731 0.9724
5.250 0.7228 0.02327 0.01382 -0.0074 0.2625 0.9811
5.500 0.7688 0.02409 0.01444 -0.0114 0.2532 0.9888
5.750 0.8116 0.02471 0.01525 -0.0151 0.2432 0.9986
6.000 0.8295 0.02535 0.01573 -0.0143 0.2376 1.0000
6.250 0.8345 0.02585 0.01640 -0.0113 0.2324 1.0000
6.500 0.8399 0.02632 0.01693 -0.0083 0.2273 1.0000
6.750 0.8519 0.02693 0.01743 -0.0063 0.2228 1.0000
7.000 0.8698 0.02792 0.01850 -0.0054 0.2179 1.0000
7.250 0.8910 0.02885 0.01957 -0.0051 0.2122 1.0000
7.500 0.9168 0.02972 0.02036 -0.0053 0.2069 1.0000
7.750 0.9394 0.03099 0.02173 -0.0053 0.2018 1.0000
8.000 0.9610 0.03207 0.02298 -0.0050 0.1962 1.0000
8.250 0.9858 0.03305 0.02393 -0.0052 0.1916 1.0000
8.500 1.0097 0.03456 0.02543 -0.0053 0.1876 1.0000
8.750 1.0242 0.03604 0.02726 -0.0043 0.1830 1.0000
9.000 1.0450 0.03720 0.02852 -0.0039 0.1786 1.0000
9.250 1.0693 0.03826 0.02952 -0.0040 0.1750 1.0000
9.500 1.0876 0.04030 0.03164 -0.0036 0.1720 1.0000
9.750 1.0918 0.04265 0.03444 -0.0018 0.1692 1.0000
10.000 1.0966 0.04509 0.03720 -0.0003 0.1664 1.0000
10.250 1.1048 0.04720 0.03950 0.0009 0.1636 1.0000
10.500 1.1254 0.04846 0.04074 0.0011 0.1608 1.0000
10.750 1.1527 0.04999 0.04213 0.0006 0.1579 1.0000
11.000 1.1362 0.05350 0.04604 0.0033 0.1563 1.0000
11.250 1.1029 0.05748 0.05040 0.0070 0.1553 1.0000
11.500 1.0580 0.06245 0.05565 0.0098 0.1549 1.0000
11.750 0.9928 0.07053 0.06403 0.0096 0.1554 1.0000
12.000 0.8941 0.08657 0.08030 0.0026 0.1569 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(2)-215 MOD B (n63215b-il)