USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 100,000 Max Cl/Cd: 47.76 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27m2-il-100000.txt Download as CSV file: xf-usa27m2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3625 0.11090 0.10654 -0.0237 1.0000 0.1140
-8.000 -0.3994 0.11071 0.10648 -0.0227 1.0000 0.1148
-7.750 -0.4361 0.11015 0.10601 -0.0220 1.0000 0.1151
-7.500 -0.4353 0.10607 0.10199 -0.0197 1.0000 0.1162
-7.250 -0.3998 0.10230 0.09822 -0.0156 1.0000 0.1197
-7.000 -0.4126 0.10078 0.09678 -0.0130 1.0000 0.1218
-6.750 -0.4280 0.09914 0.09520 -0.0114 1.0000 0.1243
-6.500 -0.4467 0.09588 0.09183 -0.0244 0.9936 0.1302
-6.250 -0.4194 0.09171 0.08777 -0.0204 0.9904 0.1329
-6.000 -0.3882 0.08811 0.08412 -0.0249 0.9833 0.1399
-5.750 -0.3631 0.08282 0.07870 -0.0346 0.9714 0.1475
-5.500 -0.3335 0.07941 0.07528 -0.0366 0.9609 0.1534
-5.250 -0.3077 0.07488 0.07058 -0.0442 0.9479 0.1633
-5.000 -0.2776 0.07165 0.06733 -0.0461 0.9384 0.1703
-4.750 -0.2457 0.06755 0.06308 -0.0519 0.9299 0.1811
-4.500 -0.2229 0.06491 0.06023 -0.0554 0.9174 0.1951
-4.250 -0.1956 0.06171 0.05710 -0.0556 0.9097 0.2017
-4.000 -0.1658 0.05852 0.05376 -0.0588 0.9006 0.2151
-3.750 -0.1419 0.05632 0.05134 -0.0607 0.8890 0.2293
-3.500 -0.0998 0.03934 0.03238 -0.0677 0.8852 0.1045
-3.250 -0.0692 0.03612 0.02860 -0.0679 0.8764 0.0962
-3.000 -0.0295 0.03308 0.02460 -0.0690 0.8697 0.0892
-2.750 0.0056 0.03178 0.02295 -0.0697 0.8610 0.0884
-2.500 0.0456 0.02986 0.02085 -0.0714 0.8539 0.0896
-2.250 0.0965 0.02808 0.01889 -0.0748 0.8504 0.0902
-2.000 0.1235 0.02715 0.01788 -0.0740 0.8382 0.0905
-1.750 0.1744 0.02556 0.01627 -0.0773 0.8347 0.0921
-1.500 0.2017 0.02478 0.01549 -0.0766 0.8227 0.0942
-1.250 0.2532 0.02340 0.01409 -0.0799 0.8187 0.0987
-1.000 0.2811 0.02265 0.01339 -0.0792 0.8063 0.1055
-0.750 0.3321 0.02130 0.01220 -0.0823 0.8014 0.1281
-0.500 0.3610 0.02051 0.01198 -0.0817 0.7880 0.2491
-0.250 0.3934 0.02007 0.01166 -0.0818 0.7751 0.3423
0.000 0.4306 0.01929 0.01096 -0.0829 0.7629 0.4043
0.250 0.6235 0.01694 0.00991 -0.1142 0.7479 1.0000
0.500 0.6508 0.01679 0.00951 -0.1135 0.7270 1.0000
0.750 0.6803 0.01666 0.00910 -0.1132 0.7064 1.0000
1.000 0.7094 0.01663 0.00878 -0.1130 0.6859 1.0000
1.250 0.7336 0.01679 0.00870 -0.1120 0.6640 1.0000
1.500 0.7589 0.01702 0.00867 -0.1112 0.6439 1.0000
1.750 0.7835 0.01734 0.00875 -0.1104 0.6257 1.0000
2.000 0.8068 0.01771 0.00892 -0.1095 0.6093 1.0000
2.250 0.8294 0.01811 0.00916 -0.1084 0.5949 1.0000
2.500 0.8532 0.01850 0.00939 -0.1076 0.5824 1.0000
2.750 0.8757 0.01888 0.00963 -0.1066 0.5706 1.0000
3.000 0.8945 0.01929 0.01000 -0.1049 0.5591 1.0000
3.250 0.9178 0.01965 0.01022 -0.1041 0.5493 1.0000
3.500 0.9371 0.02001 0.01054 -0.1024 0.5390 1.0000
3.750 0.9575 0.02039 0.01086 -0.1011 0.5300 1.0000
4.000 0.9791 0.02073 0.01112 -0.0999 0.5212 1.0000
4.250 0.9979 0.02113 0.01150 -0.0982 0.5125 1.0000
4.500 1.0202 0.02145 0.01172 -0.0972 0.5043 1.0000
4.750 1.0386 0.02189 0.01217 -0.0955 0.4965 1.0000
5.000 1.0601 0.02224 0.01248 -0.0943 0.4889 1.0000
5.250 1.0798 0.02267 0.01289 -0.0929 0.4814 1.0000
5.500 1.0992 0.02306 0.01327 -0.0913 0.4737 1.0000
5.750 1.1228 0.02351 0.01366 -0.0907 0.4673 1.0000
6.000 1.1381 0.02403 0.01427 -0.0885 0.4602 1.0000
6.250 1.1644 0.02444 0.01459 -0.0883 0.4540 1.0000
6.500 1.1792 0.02506 0.01532 -0.0861 0.4476 1.0000
6.750 1.1984 0.02557 0.01587 -0.0846 0.4410 1.0000
7.000 1.2250 0.02610 0.01632 -0.0845 0.4351 1.0000
7.250 1.2352 0.02676 0.01715 -0.0815 0.4281 1.0000
7.500 1.2603 0.02722 0.01757 -0.0812 0.4215 1.0000
7.750 1.2736 0.02791 0.01838 -0.0787 0.4145 1.0000
8.000 1.2915 0.02843 0.01893 -0.0771 0.4070 1.0000
8.250 1.3116 0.02904 0.01955 -0.0759 0.3997 1.0000
8.500 1.3236 0.02964 0.02027 -0.0732 0.3916 1.0000
8.750 1.3484 0.03021 0.02080 -0.0728 0.3842 1.0000
9.000 1.3546 0.03095 0.02172 -0.0693 0.3759 1.0000
9.250 1.3823 0.03148 0.02217 -0.0694 0.3682 1.0000
9.500 1.3841 0.03227 0.02317 -0.0651 0.3594 1.0000
9.750 1.4068 0.03265 0.02350 -0.0644 0.3506 1.0000
10.000 1.4115 0.03317 0.02415 -0.0605 0.3412 1.0000
10.250 1.4241 0.03354 0.02452 -0.0581 0.3320 1.0000
10.500 1.4376 0.03364 0.02459 -0.0557 0.3227 1.0000
10.750 1.4400 0.03431 0.02541 -0.0518 0.3145 1.0000
11.000 1.4548 0.03445 0.02550 -0.0497 0.3063 1.0000
11.250 1.4545 0.03525 0.02644 -0.0455 0.2994 1.0000
11.500 1.4594 0.03582 0.02710 -0.0421 0.2926 1.0000
11.750 1.4692 0.03624 0.02752 -0.0396 0.2858 1.0000
12.000 1.4632 0.03714 0.02861 -0.0350 0.2790 1.0000
12.250 1.4782 0.03723 0.02860 -0.0333 0.2720 1.0000
12.500 1.4669 0.03868 0.03033 -0.0286 0.2661 1.0000
12.750 1.4755 0.03917 0.03083 -0.0264 0.2598 1.0000
13.000 1.4714 0.04043 0.03224 -0.0232 0.2537 1.0000
13.250 1.4675 0.04163 0.03356 -0.0201 0.2470 1.0000
13.500 1.4692 0.04264 0.03461 -0.0178 0.2407 1.0000
13.750 1.4603 0.04464 0.03682 -0.0151 0.2346 1.0000
14.000 1.4651 0.04551 0.03765 -0.0134 0.2280 1.0000
14.250 1.4506 0.04836 0.04077 -0.0112 0.2221 1.0000
14.500 1.4476 0.05025 0.04271 -0.0097 0.2158 1.0000
14.750 1.4407 0.05284 0.04545 -0.0084 0.2103 1.0000
15.000 1.4317 0.05585 0.04863 -0.0074 0.2048 1.0000
15.250 1.4267 0.05843 0.05123 -0.0067 0.1981 1.0000
15.500 1.4114 0.06265 0.05566 -0.0066 0.1925 1.0000
15.750 1.4085 0.06532 0.05830 -0.0063 0.1857 1.0000
16.000 1.3910 0.07033 0.06354 -0.0068 0.1810 1.0000
16.250 1.3765 0.07501 0.06834 -0.0075 0.1751 1.0000
16.500 1.3644 0.07948 0.07286 -0.0083 0.1687 1.0000
16.750 1.3450 0.08538 0.07896 -0.0097 0.1641 1.0000
17.000 1.3369 0.08942 0.08297 -0.0106 0.1566 1.0000
17.250 1.3113 0.09673 0.09054 -0.0130 0.1526 1.0000
17.500 1.2903 0.10338 0.09732 -0.0153 0.1467 1.0000
17.750 1.2727 0.10958 0.10363 -0.0175 0.1402 1.0000
18.000 1.2476 0.11733 0.11158 -0.0205 0.1352 1.0000
18.250 1.2306 0.12378 0.11814 -0.0232 0.1277 1.0000
|
Polar data table (+)
Polar graphs
<< Back to USA 27 mod. AIRFOIL (usa27m2-il)