USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 200,000 Max Cl/Cd: 67.06 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35a-il-200000-n5.txt Download as CSV file: xf-usa35a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 35 A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 0.0000 0.09385 0.08927 -0.0888 0.8087 0.0410
-9.500 0.0026 0.09032 0.08569 -0.0904 0.7987 0.0410
-9.250 0.0041 0.08660 0.08193 -0.0922 0.7895 0.0414
-9.000 0.0040 0.08250 0.07780 -0.0944 0.7797 0.0417
-8.750 0.0024 0.07818 0.07342 -0.0967 0.7708 0.0418
-8.500 -0.0004 0.07355 0.06878 -0.0995 0.7611 0.0417
-8.250 -0.1813 0.02982 0.02314 -0.1332 0.7571 0.0426
-8.000 -0.1600 0.02881 0.02199 -0.1329 0.7482 0.0431
-7.750 -0.1370 0.02816 0.02128 -0.1326 0.7380 0.0435
-7.250 -0.0921 0.02633 0.01912 -0.1319 0.7181 0.0448
-7.000 -0.0701 0.02509 0.01757 -0.1315 0.7081 0.0456
-6.750 -0.0481 0.02370 0.01585 -0.1311 0.6971 0.0465
-6.500 -0.0246 0.02262 0.01445 -0.1307 0.6868 0.0473
-6.250 0.0008 0.02213 0.01392 -0.1303 0.6759 0.0479
-6.000 0.0263 0.02166 0.01332 -0.1300 0.6661 0.0485
-5.750 0.0519 0.02112 0.01267 -0.1296 0.6559 0.0494
-5.500 0.0775 0.02054 0.01189 -0.1293 0.6466 0.0506
-5.250 0.1034 0.01995 0.01109 -0.1289 0.6375 0.0520
-5.000 0.1297 0.01968 0.01079 -0.1286 0.6284 0.0530
-4.750 0.1562 0.01939 0.01041 -0.1283 0.6201 0.0543
-4.500 0.1826 0.01900 0.00989 -0.1280 0.6120 0.0558
-4.250 0.2092 0.01862 0.00935 -0.1277 0.6053 0.0573
-4.000 0.2361 0.01836 0.00910 -0.1275 0.5989 0.0585
-3.750 0.2630 0.01811 0.00878 -0.1272 0.5923 0.0603
-3.500 0.2900 0.01787 0.00840 -0.1270 0.5863 0.0625
-3.250 0.3169 0.01770 0.00823 -0.1268 0.5803 0.0644
-3.000 0.3437 0.01751 0.00798 -0.1265 0.5732 0.0668
-2.750 0.3702 0.01733 0.00770 -0.1261 0.5660 0.0690
-2.500 0.3970 0.01719 0.00754 -0.1258 0.5596 0.0715
-2.250 0.4241 0.01706 0.00734 -0.1256 0.5538 0.0746
-2.000 0.4511 0.01692 0.00722 -0.1254 0.5490 0.0773
-1.750 0.4783 0.01684 0.00706 -0.1252 0.5445 0.0810
-1.500 0.5054 0.01673 0.00695 -0.1250 0.5403 0.0843
-1.250 0.5327 0.01664 0.00686 -0.1249 0.5359 0.0884
-1.000 0.5599 0.01653 0.00679 -0.1247 0.5317 0.0926
-0.750 0.5871 0.01649 0.00670 -0.1245 0.5275 0.0976
-0.500 0.6142 0.01643 0.00663 -0.1244 0.5235 0.1032
-0.250 0.6415 0.01640 0.00659 -0.1242 0.5196 0.1101
0.000 0.6684 0.01632 0.00659 -0.1240 0.5153 0.1195
0.250 0.6952 0.01625 0.00660 -0.1239 0.5109 0.1350
0.500 0.7220 0.01618 0.00667 -0.1237 0.5069 0.1703
0.750 0.7489 0.01614 0.00672 -0.1236 0.5031 0.2177
1.000 0.7760 0.01612 0.00678 -0.1235 0.4995 0.2664
1.250 0.8016 0.01593 0.00694 -0.1233 0.4952 0.3503
1.500 0.8266 0.01574 0.00711 -0.1229 0.4906 0.4677
1.750 0.8504 0.01551 0.00725 -0.1221 0.4861 0.5823
2.000 0.8674 0.01510 0.00745 -0.1193 0.4821 0.8172
2.250 0.9055 0.01509 0.00751 -0.1210 0.4778 1.0000
2.500 0.9304 0.01525 0.00766 -0.1204 0.4732 1.0000
2.750 0.9554 0.01543 0.00779 -0.1199 0.4684 1.0000
3.000 0.9803 0.01563 0.00790 -0.1194 0.4639 1.0000
3.250 1.0053 0.01585 0.00800 -0.1189 0.4597 1.0000
3.500 1.0293 0.01604 0.00819 -0.1182 0.4545 1.0000
3.750 1.0530 0.01624 0.00837 -0.1175 0.4488 1.0000
4.000 1.0764 0.01646 0.00851 -0.1168 0.4436 1.0000
4.250 1.0997 0.01669 0.00868 -0.1160 0.4388 1.0000
4.500 1.1225 0.01692 0.00892 -0.1152 0.4331 1.0000
4.750 1.1447 0.01717 0.00913 -0.1143 0.4276 1.0000
5.000 1.1661 0.01743 0.00932 -0.1132 0.4225 1.0000
5.250 1.1870 0.01770 0.00960 -0.1121 0.4160 1.0000
5.500 1.2052 0.01798 0.00984 -0.1105 0.4092 1.0000
5.750 1.2225 0.01829 0.01010 -0.1088 0.4029 1.0000
6.000 1.2403 0.01863 0.01044 -0.1073 0.3957 1.0000
6.250 1.2572 0.01902 0.01077 -0.1056 0.3893 1.0000
6.500 1.2752 0.01943 0.01116 -0.1042 0.3833 1.0000
6.750 1.2924 0.01988 0.01159 -0.1027 0.3769 1.0000
7.000 1.3085 0.02038 0.01203 -0.1011 0.3713 1.0000
7.250 1.3258 0.02089 0.01253 -0.0998 0.3656 1.0000
7.500 1.3421 0.02144 0.01307 -0.0984 0.3598 1.0000
7.750 1.3569 0.02206 0.01364 -0.0968 0.3543 1.0000
8.000 1.3732 0.02267 0.01425 -0.0955 0.3492 1.0000
8.250 1.3889 0.02332 0.01491 -0.0941 0.3440 1.0000
8.500 1.4037 0.02403 0.01559 -0.0927 0.3393 1.0000
8.750 1.4184 0.02478 0.01630 -0.0914 0.3352 1.0000
9.000 1.4342 0.02550 0.01707 -0.0902 0.3310 1.0000
9.250 1.4489 0.02628 0.01788 -0.0890 0.3268 1.0000
9.500 1.4628 0.02712 0.01872 -0.0878 0.3229 1.0000
9.750 1.4762 0.02801 0.01958 -0.0865 0.3193 1.0000
10.000 1.4906 0.02889 0.02051 -0.0854 0.3157 1.0000
10.250 1.5037 0.02984 0.02152 -0.0843 0.3118 1.0000
10.500 1.5157 0.03088 0.02259 -0.0830 0.3078 1.0000
10.750 1.5269 0.03198 0.02367 -0.0818 0.3039 1.0000
11.000 1.5384 0.03309 0.02480 -0.0806 0.3003 1.0000
11.250 1.5488 0.03432 0.02613 -0.0795 0.2961 1.0000
11.500 1.5583 0.03562 0.02748 -0.0784 0.2919 1.0000
11.750 1.5670 0.03699 0.02886 -0.0772 0.2880 1.0000
12.000 1.5761 0.03834 0.03020 -0.0761 0.2844 1.0000
12.250 1.5840 0.03990 0.03189 -0.0752 0.2804 1.0000
12.500 1.5910 0.04155 0.03361 -0.0742 0.2760 1.0000
12.750 1.5969 0.04329 0.03539 -0.0732 0.2718 1.0000
13.000 1.6031 0.04503 0.03713 -0.0723 0.2680 1.0000
13.250 1.6078 0.04707 0.03930 -0.0715 0.2634 1.0000
13.500 1.6108 0.04925 0.04155 -0.0707 0.2586 1.0000
13.750 1.6138 0.05143 0.04374 -0.0700 0.2541 1.0000
14.000 1.6159 0.05385 0.04625 -0.0694 0.2493 1.0000
14.250 1.6159 0.05653 0.04902 -0.0688 0.2439 1.0000
14.500 1.6159 0.05918 0.05168 -0.0683 0.2390 1.0000
14.750 1.6158 0.06197 0.05457 -0.0679 0.2339 1.0000
15.000 1.6141 0.06499 0.05765 -0.0676 0.2287 1.0000
15.250 1.6128 0.06791 0.06057 -0.0672 0.2242 1.0000
15.500 1.6114 0.07100 0.06377 -0.0671 0.2192 1.0000
15.750 1.6088 0.07419 0.06702 -0.0669 0.2145 1.0000
16.000 1.6081 0.07711 0.06993 -0.0668 0.2106 1.0000
16.250 1.6062 0.08031 0.07323 -0.0668 0.2065 1.0000
16.500 1.6050 0.08341 0.07639 -0.0668 0.2026 1.0000
16.750 1.6046 0.08637 0.07935 -0.0668 0.1992 1.0000
17.000 1.6058 0.08911 0.08212 -0.0668 0.1962 1.0000
17.250 1.6037 0.09237 0.08549 -0.0670 0.1929 1.0000
17.500 1.6031 0.09543 0.08860 -0.0672 0.1897 1.0000
17.750 1.6043 0.09820 0.09136 -0.0674 0.1868 1.0000
18.000 1.6081 0.10059 0.09375 -0.0676 0.1842 1.0000
18.250 1.6054 0.10403 0.09732 -0.0681 0.1814 1.0000
18.500 1.6031 0.10739 0.10076 -0.0686 0.1785 1.0000
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