USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 200,000 Max Cl/Cd: 67 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35-il-200000-n5.txt Download as CSV file: xf-usa35-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 35 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 0.0003 0.09393 0.08935 -0.0888 0.8092 0.0417
-9.500 0.0029 0.09041 0.08578 -0.0903 0.7994 0.0415
-9.250 0.0049 0.08673 0.08206 -0.0921 0.7900 0.0414
-9.000 0.0059 0.08290 0.07819 -0.0940 0.7800 0.0418
-8.750 0.0041 0.07853 0.07378 -0.0965 0.7709 0.0422
-8.500 -0.0006 0.07356 0.06878 -0.0996 0.7610 0.0424
-8.250 -0.1779 0.03067 0.02408 -0.1330 0.7575 0.0432
-8.000 -0.1574 0.02955 0.02283 -0.1327 0.7484 0.0436
-7.750 -0.1349 0.02885 0.02204 -0.1324 0.7379 0.0440
-7.500 -0.1124 0.02803 0.02107 -0.1321 0.7281 0.0445
-7.250 -0.0904 0.02703 0.01989 -0.1317 0.7170 0.0453
-7.000 -0.0689 0.02572 0.01828 -0.1314 0.7072 0.0462
-6.750 -0.0476 0.02416 0.01634 -0.1309 0.6966 0.0472
-6.500 -0.0240 0.02312 0.01502 -0.1305 0.6869 0.0479
-6.250 0.0012 0.02261 0.01444 -0.1302 0.6761 0.0485
-6.000 0.0266 0.02209 0.01380 -0.1298 0.6666 0.0492
-5.750 0.0520 0.02151 0.01309 -0.1295 0.6562 0.0500
-5.500 0.0775 0.02089 0.01225 -0.1291 0.6468 0.0511
-5.250 0.1032 0.02025 0.01137 -0.1287 0.6369 0.0525
-4.750 0.1559 0.01965 0.01068 -0.1282 0.6198 0.0547
-4.500 0.1823 0.01927 0.01015 -0.1279 0.6123 0.0562
-4.250 0.2090 0.01884 0.00954 -0.1275 0.6057 0.0576
-4.000 0.2357 0.01855 0.00926 -0.1273 0.5987 0.0587
-3.750 0.2625 0.01831 0.00895 -0.1270 0.5921 0.0602
-3.500 0.2895 0.01808 0.00858 -0.1268 0.5866 0.0623
-3.250 0.3164 0.01783 0.00833 -0.1266 0.5802 0.0641
-3.000 0.3431 0.01765 0.00810 -0.1263 0.5731 0.0660
-2.750 0.3697 0.01749 0.00780 -0.1259 0.5664 0.0683
-2.500 0.3964 0.01727 0.00761 -0.1257 0.5595 0.0703
-2.250 0.4232 0.01714 0.00744 -0.1254 0.5536 0.0729
-2.000 0.4503 0.01702 0.00723 -0.1251 0.5490 0.0757
-1.750 0.4774 0.01689 0.00711 -0.1250 0.5448 0.0784
-1.500 0.5047 0.01678 0.00699 -0.1248 0.5404 0.0819
-1.250 0.5318 0.01665 0.00689 -0.1247 0.5360 0.0851
-1.000 0.5590 0.01659 0.00679 -0.1245 0.5316 0.0892
-0.750 0.5861 0.01652 0.00670 -0.1243 0.5275 0.0935
-0.250 0.6404 0.01640 0.00662 -0.1240 0.5194 0.1053
0.000 0.6675 0.01634 0.00661 -0.1238 0.5153 0.1142
0.250 0.6944 0.01629 0.00660 -0.1236 0.5113 0.1288
0.500 0.7214 0.01623 0.00664 -0.1235 0.5073 0.1612
0.750 0.7483 0.01617 0.00671 -0.1234 0.5035 0.2134
1.000 0.7744 0.01607 0.00682 -0.1232 0.4991 0.2699
1.250 0.8001 0.01592 0.00694 -0.1230 0.4945 0.3480
1.500 0.8253 0.01572 0.00708 -0.1226 0.4902 0.4656
1.750 0.8487 0.01544 0.00725 -0.1217 0.4864 0.6170
2.000 0.8661 0.01507 0.00745 -0.1188 0.4829 0.8408
2.250 0.9045 0.01507 0.00755 -0.1207 0.4781 1.0000
2.500 0.9295 0.01524 0.00766 -0.1202 0.4733 1.0000
2.750 0.9545 0.01543 0.00776 -0.1197 0.4685 1.0000
3.000 0.9796 0.01565 0.00785 -0.1192 0.4642 1.0000
3.250 1.0038 0.01583 0.00803 -0.1186 0.4590 1.0000
3.500 1.0279 0.01603 0.00820 -0.1179 0.4537 1.0000
3.750 1.0518 0.01624 0.00834 -0.1172 0.4488 1.0000
4.000 1.0757 0.01647 0.00848 -0.1166 0.4445 1.0000
4.250 1.0989 0.01669 0.00872 -0.1158 0.4389 1.0000
4.500 1.1216 0.01692 0.00892 -0.1150 0.4334 1.0000
4.750 1.1436 0.01717 0.00910 -0.1140 0.4282 1.0000
5.000 1.1651 0.01742 0.00934 -0.1130 0.4221 1.0000
5.250 1.1853 0.01769 0.00959 -0.1118 0.4154 1.0000
5.500 1.2033 0.01798 0.00979 -0.1101 0.4094 1.0000
5.750 1.2216 0.01828 0.01011 -0.1086 0.4025 1.0000
6.000 1.2389 0.01863 0.01042 -0.1069 0.3958 1.0000
6.250 1.2565 0.01902 0.01076 -0.1054 0.3898 1.0000
6.500 1.2744 0.01942 0.01116 -0.1040 0.3833 1.0000
6.750 1.2911 0.01988 0.01157 -0.1024 0.3775 1.0000
7.000 1.3081 0.02036 0.01202 -0.1010 0.3717 1.0000
7.250 1.3247 0.02088 0.01253 -0.0995 0.3654 1.0000
7.500 1.3401 0.02146 0.01305 -0.0980 0.3598 1.0000
7.750 1.3564 0.02204 0.01363 -0.0966 0.3545 1.0000
8.000 1.3720 0.02266 0.01425 -0.0952 0.3487 1.0000
8.250 1.3866 0.02336 0.01491 -0.0937 0.3436 1.0000
8.500 1.4023 0.02404 0.01557 -0.0924 0.3396 1.0000
8.750 1.4185 0.02472 0.01630 -0.0913 0.3355 1.0000
9.000 1.4337 0.02546 0.01705 -0.0901 0.3313 1.0000
9.250 1.4477 0.02627 0.01785 -0.0888 0.3272 1.0000
9.500 1.4616 0.02712 0.01866 -0.0875 0.3235 1.0000
9.750 1.4761 0.02797 0.01958 -0.0864 0.3195 1.0000
10.000 1.4893 0.02889 0.02054 -0.0852 0.3152 1.0000
10.250 1.5015 0.02989 0.02155 -0.0839 0.3112 1.0000
10.500 1.5135 0.03092 0.02255 -0.0826 0.3075 1.0000
10.750 1.5260 0.03196 0.02366 -0.0816 0.3040 1.0000
11.000 1.5375 0.03309 0.02486 -0.0805 0.3000 1.0000
11.250 1.5478 0.03431 0.02612 -0.0793 0.2961 1.0000
11.500 1.5577 0.03556 0.02738 -0.0781 0.2924 1.0000
11.750 1.5673 0.03686 0.02869 -0.0770 0.2889 1.0000
12.000 1.5761 0.03831 0.03025 -0.0760 0.2848 1.0000
12.250 1.5833 0.03988 0.03189 -0.0750 0.2804 1.0000
12.500 1.5900 0.04150 0.03353 -0.0739 0.2762 1.0000
12.750 1.5964 0.04321 0.03527 -0.0730 0.2722 1.0000
13.000 1.6014 0.04516 0.03733 -0.0721 0.2675 1.0000
13.250 1.6055 0.04718 0.03940 -0.0713 0.2627 1.0000
13.500 1.6093 0.04922 0.04144 -0.0704 0.2585 1.0000
13.750 1.6124 0.05150 0.04384 -0.0698 0.2538 1.0000
14.000 1.6141 0.05394 0.04636 -0.0692 0.2488 1.0000
14.250 1.6153 0.05642 0.04886 -0.0685 0.2442 1.0000
14.500 1.6160 0.05908 0.05161 -0.0681 0.2393 1.0000
14.750 1.6153 0.06193 0.05453 -0.0677 0.2341 1.0000
15.000 1.6144 0.06477 0.05738 -0.0673 0.2295 1.0000
15.250 1.6129 0.06782 0.06054 -0.0671 0.2244 1.0000
15.500 1.6106 0.07096 0.06373 -0.0669 0.2193 1.0000
15.750 1.6091 0.07397 0.06673 -0.0667 0.2150 1.0000
16.000 1.6063 0.07726 0.07014 -0.0666 0.2103 1.0000
16.250 1.6045 0.08041 0.07333 -0.0666 0.2060 1.0000
16.500 1.6039 0.08336 0.07626 -0.0665 0.2025 1.0000
16.750 1.6036 0.08636 0.07936 -0.0666 0.1991 1.0000
17.000 1.6026 0.08945 0.08252 -0.0667 0.1958 1.0000
17.250 1.6027 0.09237 0.08547 -0.0668 0.1928 1.0000
17.500 1.6058 0.09484 0.08793 -0.0669 0.1901 1.0000
17.750 1.6056 0.09787 0.09103 -0.0671 0.1874 1.0000
18.000 1.6039 0.10113 0.09438 -0.0675 0.1844 1.0000
18.250 1.6034 0.10420 0.09750 -0.0679 0.1814 1.0000
18.500 1.6065 0.10670 0.09999 -0.0682 0.1786 1.0000
18.750 1.6095 0.10922 0.10253 -0.0686 0.1760 1.0000
19.000 1.6049 0.11298 0.10642 -0.0694 0.1732 1.0000
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