USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 200,000 Max Cl/Cd: 64.29 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa32-il-200000.txt Download as CSV file: xf-usa32-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 32 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0921 0.10347 0.09979 -0.1131 0.9158 0.0530
-9.000 0.0663 0.10304 0.09941 -0.1115 0.9042 0.0542
-8.750 0.0813 0.09861 0.09498 -0.1154 0.9020 0.0552
-8.500 0.1136 0.09496 0.09131 -0.1170 0.9011 0.0567
-8.250 0.1126 0.09334 0.08972 -0.1150 0.8926 0.0576
-8.000 0.1257 0.09035 0.08673 -0.1174 0.8881 0.0599
-7.750 0.1071 0.08715 0.08351 -0.1277 0.8826 0.0628
-7.250 0.1413 0.08139 0.07780 -0.1227 0.8707 0.0649
-7.000 0.1641 0.07827 0.07466 -0.1256 0.8686 0.0681
-6.750 0.1513 0.07668 0.07307 -0.1231 0.8567 0.0702
-6.500 0.1614 0.07191 0.06826 -0.1290 0.8518 0.0735
-6.250 0.1960 0.06889 0.06521 -0.1313 0.8508 0.0758
-6.000 0.1922 0.06732 0.06365 -0.1280 0.8386 0.0777
-5.750 0.2121 0.06221 0.05841 -0.1364 0.8341 0.0842
-5.500 0.2149 0.06073 0.05693 -0.1323 0.8235 0.0852
-5.250 0.2456 0.05815 0.05431 -0.1344 0.8197 0.0886
-5.000 0.2798 0.05362 0.04962 -0.1417 0.8163 0.0971
-4.750 0.2772 0.05255 0.04856 -0.1364 0.8034 0.0987
-4.500 0.3144 0.04863 0.04443 -0.1430 0.7994 0.1097
-4.250 0.3098 0.04763 0.04344 -0.1371 0.7867 0.1108
-4.000 0.3481 0.04540 0.04112 -0.1403 0.7829 0.1165
-3.750 0.3434 0.04337 0.03895 -0.1366 0.7703 0.1240
-3.500 0.3384 0.02887 0.02340 -0.1367 0.7652 0.0856
-3.250 0.3215 0.02451 0.01808 -0.1279 0.7537 0.0695
-3.000 0.3568 0.02235 0.01545 -0.1290 0.7495 0.0680
-2.750 0.3670 0.02136 0.01412 -0.1251 0.7404 0.0664
-2.500 0.4006 0.02010 0.01244 -0.1256 0.7347 0.0649
-2.250 0.4321 0.01929 0.01138 -0.1259 0.7286 0.0644
-2.000 0.4545 0.01871 0.01068 -0.1245 0.7209 0.0647
-1.750 0.5010 0.01783 0.00966 -0.1279 0.7160 0.0656
-1.500 0.5153 0.01762 0.00944 -0.1250 0.7077 0.0671
-1.250 0.5524 0.01711 0.00883 -0.1266 0.7017 0.0688
-1.000 0.5819 0.01680 0.00846 -0.1267 0.6951 0.0699
-0.750 0.6070 0.01660 0.00821 -0.1259 0.6881 0.0712
-0.500 0.6545 0.01620 0.00771 -0.1297 0.6824 0.0741
-0.250 0.6668 0.01621 0.00773 -0.1265 0.6747 0.0769
0.000 0.7050 0.01605 0.00746 -0.1284 0.6683 0.0835
0.250 0.7385 0.01569 0.00744 -0.1297 0.6621 0.1600
0.500 0.7584 0.01600 0.00780 -0.1279 0.6549 0.2263
0.750 0.8033 0.01650 0.00812 -0.1313 0.6484 0.2588
1.000 0.8054 0.01684 0.00850 -0.1259 0.6412 0.2684
1.250 0.8312 0.01718 0.00877 -0.1254 0.6342 0.2812
1.500 0.8607 0.01754 0.00899 -0.1257 0.6275 0.2932
1.750 0.8718 0.01772 0.00923 -0.1223 0.6203 0.2982
2.000 0.9069 0.01804 0.00941 -0.1239 0.6137 0.3102
2.250 0.9176 0.01827 0.00969 -0.1204 0.6067 0.3171
2.500 0.9335 0.01847 0.00986 -0.1180 0.5993 0.3251
2.750 0.9740 0.01865 0.00991 -0.1207 0.5926 0.3333
3.000 0.9686 0.01878 0.01012 -0.1139 0.5847 0.3356
3.250 0.9942 0.01886 0.01012 -0.1135 0.5777 0.3407
3.500 1.0097 0.01906 0.01026 -0.1111 0.5707 0.3457
3.750 1.0191 0.01917 0.01042 -0.1075 0.5631 0.3497
4.000 1.0511 0.01921 0.01037 -0.1085 0.5569 0.3567
4.250 1.0497 0.01947 0.01069 -0.1027 0.5491 0.3607
4.500 1.0679 0.01951 0.01072 -0.1010 0.5421 0.3657
4.750 1.0860 0.01964 0.01083 -0.0992 0.5355 0.3722
5.000 1.0925 0.01983 0.01105 -0.0952 0.5277 0.3785
5.250 1.1193 0.01982 0.01100 -0.0952 0.5218 0.3871
5.500 1.1233 0.02010 0.01135 -0.0909 0.5140 0.3943
5.750 1.1415 0.02018 0.01144 -0.0894 0.5073 0.4040
6.000 1.1654 0.02030 0.01158 -0.0890 0.5013 0.4146
6.250 1.1787 0.02057 0.01190 -0.0867 0.4943 0.4249
6.500 1.2051 0.02063 0.01192 -0.0868 0.4887 0.4394
6.750 1.2213 0.02092 0.01227 -0.0852 0.4827 0.4542
7.000 1.2369 0.02113 0.01257 -0.0835 0.4756 0.4817
7.250 1.4069 0.02189 0.01418 -0.1155 0.4624 1.0000
7.500 1.4244 0.02222 0.01446 -0.1139 0.4572 1.0000
7.750 1.4497 0.02255 0.01468 -0.1138 0.4524 1.0000
8.000 1.4566 0.02309 0.01530 -0.1104 0.4471 1.0000
8.250 1.4714 0.02350 0.01571 -0.1085 0.4418 1.0000
8.500 1.5013 0.02376 0.01582 -0.1092 0.4368 1.0000
8.750 1.5043 0.02440 0.01657 -0.1053 0.4318 1.0000
9.000 1.5163 0.02491 0.01711 -0.1030 0.4270 1.0000
9.250 1.5367 0.02529 0.01745 -0.1021 0.4226 1.0000
9.500 1.5619 0.02568 0.01780 -0.1021 0.4183 1.0000
9.750 1.5639 0.02641 0.01865 -0.0982 0.4137 1.0000
10.000 1.5759 0.02696 0.01924 -0.0961 0.4091 1.0000
10.250 1.5975 0.02734 0.01960 -0.0955 0.4051 1.0000
10.500 1.6186 0.02783 0.02008 -0.0949 0.4009 1.0000
10.750 1.6183 0.02869 0.02108 -0.0910 0.3965 1.0000
11.000 1.6274 0.02934 0.02178 -0.0885 0.3917 1.0000
11.250 1.6507 0.02961 0.02196 -0.0882 0.3865 1.0000
11.500 1.6550 0.03049 0.02296 -0.0852 0.3823 1.0000
11.750 1.6538 0.03148 0.02407 -0.0815 0.3775 1.0000
12.000 1.6643 0.03209 0.02470 -0.0795 0.3724 1.0000
12.250 1.6878 0.03242 0.02498 -0.0793 0.3676 1.0000
12.500 1.6766 0.03386 0.02662 -0.0745 0.3629 1.0000
12.750 1.6778 0.03488 0.02771 -0.0715 0.3574 1.0000
13.000 1.6978 0.03518 0.02794 -0.0709 0.3521 1.0000
13.250 1.6878 0.03684 0.02977 -0.0668 0.3470 1.0000
13.500 1.6834 0.03827 0.03131 -0.0635 0.3410 1.0000
13.750 1.7003 0.03865 0.03159 -0.0626 0.3348 1.0000
14.000 1.6856 0.04090 0.03405 -0.0586 0.3295 1.0000
14.250 1.6807 0.04264 0.03589 -0.0558 0.3230 1.0000
14.500 1.6847 0.04388 0.03711 -0.0539 0.3163 1.0000
14.750 1.6711 0.04656 0.03997 -0.0509 0.3094 1.0000
15.000 1.6763 0.04784 0.04121 -0.0494 0.3026 1.0000
15.250 1.6615 0.05100 0.04456 -0.0468 0.2952 1.0000
15.500 1.6588 0.05317 0.04673 -0.0452 0.2876 1.0000
15.750 1.6481 0.05631 0.05002 -0.0434 0.2796 1.0000
16.000 1.6435 0.05888 0.05258 -0.0421 0.2710 1.0000
16.250 1.6295 0.06269 0.05653 -0.0408 0.2615 1.0000
16.500 1.6231 0.06567 0.05951 -0.0397 0.2526 1.0000
16.750 1.6114 0.06938 0.06330 -0.0387 0.2427 1.0000
17.000 1.6012 0.07297 0.06695 -0.0379 0.2336 1.0000
17.500 1.5799 0.08048 0.07449 -0.0367 0.2152 1.0000
17.750 1.5709 0.08407 0.07807 -0.0362 0.2071 1.0000
18.000 1.5627 0.08764 0.08167 -0.0358 0.1998 1.0000
18.250 1.5551 0.09116 0.08518 -0.0356 0.1927 1.0000
18.500 1.5457 0.09500 0.08904 -0.0355 0.1855 1.0000
18.750 1.5400 0.09832 0.09234 -0.0354 0.1791 1.0000
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