USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 100,000 Max Cl/Cd: 53.35 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35b-il-100000.txt Download as CSV file: xf-usa35b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA-35B AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3138 0.09363 0.08870 -0.0330 1.0000 0.1178
-9.250 -0.3264 0.09204 0.08722 -0.0319 1.0000 0.1206
-9.000 -0.3559 0.09153 0.08688 -0.0296 1.0000 0.1224
-8.750 -0.3988 0.09097 0.08644 -0.0337 1.0000 0.1240
-8.500 -0.4089 0.08755 0.08308 -0.0333 1.0000 0.1250
-8.250 -0.4001 0.08485 0.08047 -0.0274 1.0000 0.1263
-8.000 -0.3992 0.08299 0.07867 -0.0237 1.0000 0.1280
-7.750 -0.4037 0.08128 0.07703 -0.0214 1.0000 0.1301
-7.500 -0.3986 0.07786 0.07352 -0.0314 0.9961 0.1390
-7.250 -0.3692 0.07256 0.06821 -0.0360 0.9890 0.1429
-6.750 -0.2865 0.06451 0.05973 -0.0558 0.9705 0.1720
-6.500 -0.2602 0.06004 0.05538 -0.0568 0.9616 0.1758
-6.250 -0.2194 0.05618 0.05136 -0.0642 0.9534 0.1917
-6.000 -0.1831 0.05300 0.04804 -0.0693 0.9432 0.2084
-5.750 -0.1501 0.05028 0.04538 -0.0708 0.9343 0.2177
-5.250 -0.0399 0.03320 0.02569 -0.0894 0.9179 0.1081
-5.000 0.0037 0.03013 0.02235 -0.0928 0.9111 0.1045
-4.750 0.0443 0.02784 0.01965 -0.0951 0.9028 0.1024
-4.500 0.0844 0.02620 0.01766 -0.0970 0.8941 0.1040
-4.250 0.1199 0.02499 0.01615 -0.0980 0.8839 0.1068
-4.000 0.1594 0.02373 0.01460 -0.0994 0.8761 0.1088
-3.750 0.1895 0.02247 0.01335 -0.0995 0.8647 0.1122
-3.500 0.2266 0.02145 0.01230 -0.1005 0.8576 0.1199
-3.250 0.2531 0.02073 0.01164 -0.0999 0.8451 0.1291
-3.000 0.2825 0.01996 0.01093 -0.0995 0.8352 0.1432
-2.750 0.3120 0.01914 0.01030 -0.0992 0.8256 0.1762
-2.500 0.3361 0.01785 0.00979 -0.0984 0.8141 0.3158
-2.250 0.3812 0.01559 0.00930 -0.0990 0.8071 1.0000
-2.000 0.4056 0.01573 0.00918 -0.0981 0.7942 1.0000
-1.750 0.4317 0.01582 0.00906 -0.0973 0.7831 1.0000
-1.500 0.4602 0.01582 0.00882 -0.0968 0.7740 1.0000
-1.250 0.4849 0.01604 0.00890 -0.0961 0.7623 1.0000
-1.000 0.5122 0.01614 0.00882 -0.0956 0.7532 1.0000
-0.750 0.5386 0.01630 0.00884 -0.0950 0.7429 1.0000
-0.500 0.5644 0.01652 0.00895 -0.0944 0.7327 1.0000
-0.250 0.5926 0.01660 0.00887 -0.0940 0.7241 1.0000
0.000 0.6174 0.01690 0.00910 -0.0933 0.7130 1.0000
0.250 0.6453 0.01703 0.00910 -0.0929 0.7044 1.0000
0.500 0.6709 0.01728 0.00929 -0.0923 0.6937 1.0000
0.750 0.6970 0.01756 0.00950 -0.0917 0.6836 1.0000
1.000 0.7249 0.01771 0.00954 -0.0913 0.6744 1.0000
1.250 0.7496 0.01806 0.00987 -0.0906 0.6630 1.0000
1.500 0.7770 0.01829 0.01001 -0.0901 0.6535 1.0000
1.750 0.8030 0.01858 0.01026 -0.0895 0.6425 1.0000
2.000 0.8280 0.01895 0.01061 -0.0888 0.6310 1.0000
2.250 0.8562 0.01916 0.01073 -0.0884 0.6214 1.0000
2.500 0.8807 0.01953 0.01110 -0.0877 0.6088 1.0000
2.750 0.9054 0.01983 0.01138 -0.0868 0.5955 1.0000
3.000 0.9310 0.02002 0.01152 -0.0859 0.5819 1.0000
3.250 0.9575 0.02014 0.01155 -0.0852 0.5687 1.0000
3.500 0.9832 0.02033 0.01169 -0.0844 0.5556 1.0000
3.750 1.0069 0.02064 0.01205 -0.0835 0.5420 1.0000
4.000 1.0313 0.02094 0.01236 -0.0826 0.5291 1.0000
4.250 1.0572 0.02116 0.01254 -0.0820 0.5172 1.0000
4.500 1.0830 0.02136 0.01272 -0.0813 0.5051 1.0000
4.750 1.1059 0.02169 0.01312 -0.0803 0.4915 1.0000
5.000 1.1296 0.02201 0.01348 -0.0794 0.4786 1.0000
5.250 1.1542 0.02227 0.01376 -0.0786 0.4660 1.0000
5.500 1.1794 0.02247 0.01391 -0.0778 0.4534 1.0000
5.750 1.2028 0.02273 0.01418 -0.0768 0.4395 1.0000
6.000 1.2249 0.02306 0.01458 -0.0757 0.4247 1.0000
6.250 1.2468 0.02343 0.01497 -0.0745 0.4099 1.0000
6.500 1.2685 0.02380 0.01534 -0.0733 0.3943 1.0000
6.750 1.2894 0.02417 0.01567 -0.0720 0.3777 1.0000
7.000 1.3094 0.02459 0.01604 -0.0706 0.3606 1.0000
7.250 1.3286 0.02512 0.01649 -0.0691 0.3436 1.0000
7.500 1.3470 0.02575 0.01709 -0.0676 0.3274 1.0000
7.750 1.3642 0.02645 0.01781 -0.0660 0.3121 1.0000
8.000 1.3801 0.02716 0.01858 -0.0643 0.2975 1.0000
8.250 1.3954 0.02793 0.01943 -0.0625 0.2841 1.0000
8.500 1.4102 0.02871 0.02027 -0.0607 0.2716 1.0000
8.750 1.4232 0.02944 0.02104 -0.0586 0.2592 1.0000
9.000 1.4357 0.03018 0.02178 -0.0566 0.2475 1.0000
9.250 1.4438 0.03099 0.02272 -0.0540 0.2356 1.0000
9.500 1.4479 0.03189 0.02374 -0.0508 0.2237 1.0000
9.750 1.4499 0.03294 0.02486 -0.0476 0.2116 1.0000
10.000 1.4490 0.03422 0.02621 -0.0445 0.1985 1.0000
10.250 1.4449 0.03587 0.02789 -0.0415 0.1839 1.0000
10.500 1.4374 0.03802 0.03005 -0.0388 0.1677 1.0000
10.750 1.4278 0.04068 0.03266 -0.0364 0.1512 1.0000
11.000 1.4187 0.04362 0.03554 -0.0345 0.1364 1.0000
11.250 1.4124 0.04658 0.03847 -0.0329 0.1243 1.0000
11.500 1.4092 0.04941 0.04127 -0.0316 0.1152 1.0000
11.750 1.4078 0.05208 0.04389 -0.0306 0.1081 1.0000
12.000 1.4083 0.05480 0.04671 -0.0297 0.1017 1.0000
12.250 1.4099 0.05730 0.04921 -0.0289 0.0967 1.0000
12.500 1.4124 0.05991 0.05190 -0.0280 0.0923 1.0000
12.750 1.4138 0.06262 0.05472 -0.0274 0.0883 1.0000
13.000 1.4219 0.06456 0.05653 -0.0264 0.0847 1.0000
13.250 1.4231 0.06754 0.05972 -0.0258 0.0820 1.0000
13.500 1.4230 0.07060 0.06297 -0.0255 0.0793 1.0000
13.750 1.4270 0.07312 0.06553 -0.0250 0.0766 1.0000
14.000 1.4411 0.07480 0.06711 -0.0237 0.0738 1.0000
14.250 1.4349 0.07880 0.07140 -0.0239 0.0725 1.0000
14.500 1.4279 0.08298 0.07584 -0.0242 0.0712 1.0000
14.750 1.4192 0.08746 0.08055 -0.0249 0.0700 1.0000
15.000 1.4102 0.09204 0.08533 -0.0259 0.0688 1.0000
15.250 1.4030 0.09642 0.08985 -0.0269 0.0676 1.0000
15.750 1.0835 0.17958 0.17433 -0.0787 0.0830 1.0000
16.000 1.0714 0.18992 0.18464 -0.0843 0.0835 1.0000
16.250 1.0685 0.19735 0.19206 -0.0880 0.0838 1.0000
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