I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 200,000 Max Cl/Cd: 70.64 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa571-il-200000-n5.txt Download as CSV file: xf-isa571-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3074 0.10184 0.09851 -0.0262 1.0000 0.0215
-9.750 -0.3068 0.09835 0.09505 -0.0264 1.0000 0.0215
-9.250 -0.3941 0.10412 0.10060 -0.0228 1.0000 0.0215
-8.750 -0.3848 0.09670 0.09322 -0.0200 1.0000 0.0174
-8.500 -0.3861 0.09374 0.09031 -0.0201 1.0000 0.0171
-8.250 -0.3892 0.09106 0.08768 -0.0198 1.0000 0.0171
-8.000 -0.3955 0.08859 0.08526 -0.0189 1.0000 0.0170
-7.750 -0.3997 0.08593 0.08265 -0.0187 1.0000 0.0171
-7.500 -0.4008 0.08278 0.07955 -0.0197 1.0000 0.0170
-7.250 -0.4006 0.07926 0.07607 -0.0212 1.0000 0.0166
-7.000 -0.3988 0.07488 0.07172 -0.0239 1.0000 0.0158
-6.750 -0.3914 0.06731 0.06413 -0.0305 1.0000 0.0140
-6.250 -0.3670 0.05879 0.05547 -0.0351 1.0000 0.0137
-6.000 -0.3373 0.05230 0.04881 -0.0419 0.9976 0.0136
-5.750 -0.3007 0.04498 0.04121 -0.0493 0.9950 0.0137
-5.500 -0.2643 0.03665 0.03245 -0.0556 0.9920 0.0139
-5.250 -0.2297 0.03379 0.02934 -0.0592 0.9890 0.0155
-5.000 -0.1897 0.02854 0.02360 -0.0633 0.9864 0.0171
-4.750 -0.1512 0.02025 0.01409 -0.0662 0.9840 0.0190
-4.500 -0.1117 0.01750 0.01070 -0.0686 0.9801 0.0224
-4.250 -0.0728 0.01718 0.01028 -0.0709 0.9747 0.0261
-4.000 -0.0361 0.01611 0.00893 -0.0726 0.9694 0.0316
-3.750 0.0014 0.01578 0.00836 -0.0744 0.9639 0.0384
-3.500 0.0362 0.01523 0.00781 -0.0759 0.9567 0.0444
-3.250 0.0714 0.01468 0.00706 -0.0773 0.9506 0.0503
-3.000 0.1034 0.01397 0.00633 -0.0782 0.9435 0.0542
-2.750 0.1384 0.01340 0.00569 -0.0796 0.9380 0.0572
-2.500 0.1682 0.01295 0.00516 -0.0798 0.9286 0.0602
-2.250 0.1995 0.01248 0.00464 -0.0804 0.9187 0.0614
-2.000 0.2329 0.01198 0.00413 -0.0814 0.9080 0.0636
-1.750 0.2659 0.01160 0.00374 -0.0823 0.8943 0.0667
-1.500 0.2989 0.01130 0.00342 -0.0831 0.8771 0.0704
-1.250 0.3340 0.01103 0.00313 -0.0844 0.8558 0.0759
-1.000 0.3695 0.01081 0.00287 -0.0856 0.8259 0.0901
-0.750 0.4026 0.01069 0.00258 -0.0863 0.7827 0.1108
-0.500 0.4310 0.01069 0.00236 -0.0861 0.7289 0.1290
0.000 0.4802 0.01027 0.00233 -0.0849 0.6395 0.4339
0.250 0.5021 0.00917 0.00238 -0.0829 0.6059 1.0000
0.500 0.5274 0.00943 0.00241 -0.0823 0.5726 1.0000
0.750 0.5525 0.00970 0.00245 -0.0817 0.5374 1.0000
1.000 0.5773 0.00999 0.00252 -0.0810 0.5017 1.0000
1.250 0.6023 0.01029 0.00260 -0.0805 0.4714 1.0000
1.500 0.6276 0.01058 0.00270 -0.0800 0.4464 1.0000
1.750 0.6529 0.01087 0.00284 -0.0796 0.4244 1.0000
2.000 0.6784 0.01116 0.00299 -0.0792 0.4042 1.0000
2.250 0.7041 0.01143 0.00314 -0.0788 0.3882 1.0000
2.500 0.7301 0.01167 0.00333 -0.0785 0.3756 1.0000
2.750 0.7563 0.01190 0.00352 -0.0783 0.3655 1.0000
3.000 0.7823 0.01215 0.00372 -0.0780 0.3563 1.0000
3.250 0.8087 0.01236 0.00393 -0.0778 0.3473 1.0000
3.500 0.8346 0.01261 0.00417 -0.0775 0.3383 1.0000
3.750 0.8607 0.01285 0.00441 -0.0772 0.3286 1.0000
4.000 0.8867 0.01309 0.00467 -0.0770 0.3189 1.0000
4.250 0.9124 0.01336 0.00496 -0.0766 0.3092 1.0000
4.500 0.9381 0.01361 0.00524 -0.0763 0.2980 1.0000
4.750 0.9638 0.01387 0.00553 -0.0760 0.2856 1.0000
5.000 0.9893 0.01414 0.00584 -0.0757 0.2732 1.0000
5.250 1.0147 0.01442 0.00619 -0.0754 0.2608 1.0000
5.500 1.0398 0.01472 0.00654 -0.0750 0.2461 1.0000
5.750 1.0637 0.01513 0.00689 -0.0745 0.2192 1.0000
6.000 1.0852 0.01582 0.00734 -0.0737 0.1819 1.0000
6.250 1.1071 0.01649 0.00794 -0.0730 0.1579 1.0000
6.500 1.1299 0.01707 0.00850 -0.0724 0.1357 1.0000
6.750 1.1490 0.01811 0.00922 -0.0714 0.0871 1.0000
7.000 1.1649 0.01957 0.01035 -0.0699 0.0318 1.0000
7.250 1.1826 0.02078 0.01156 -0.0684 0.0200 1.0000
7.500 1.2015 0.02182 0.01275 -0.0670 0.0165 1.0000
7.750 1.2190 0.02299 0.01415 -0.0654 0.0145 1.0000
8.000 1.2377 0.02389 0.01528 -0.0641 0.0132 1.0000
8.250 1.2543 0.02496 0.01653 -0.0625 0.0120 1.0000
8.500 1.2685 0.02620 0.01794 -0.0607 0.0112 1.0000
8.750 1.2803 0.02757 0.01947 -0.0585 0.0107 1.0000
9.000 1.2890 0.02911 0.02116 -0.0560 0.0102 1.0000
9.250 1.2934 0.03088 0.02307 -0.0530 0.0098 1.0000
9.500 1.2900 0.03303 0.02534 -0.0490 0.0093 1.0000
9.750 1.2933 0.03476 0.02720 -0.0461 0.0090 1.0000
10.000 1.2997 0.03624 0.02884 -0.0437 0.0085 1.0000
10.250 1.3034 0.03803 0.03079 -0.0413 0.0081 1.0000
10.500 1.3051 0.04015 0.03305 -0.0390 0.0079 1.0000
10.750 1.3059 0.04246 0.03552 -0.0370 0.0077 1.0000
11.000 1.3063 0.04494 0.03816 -0.0353 0.0075 1.0000
11.250 1.3057 0.04765 0.04103 -0.0338 0.0074 1.0000
11.500 1.3043 0.05058 0.04418 -0.0327 0.0072 1.0000
11.750 1.3016 0.05378 0.04756 -0.0321 0.0071 1.0000
12.000 1.2975 0.05732 0.05130 -0.0319 0.0070 1.0000
12.250 1.2920 0.06121 0.05537 -0.0321 0.0069 1.0000
12.500 1.2853 0.06545 0.05981 -0.0329 0.0069 1.0000
12.750 1.2773 0.07007 0.06462 -0.0341 0.0068 1.0000
13.000 1.2678 0.07510 0.06984 -0.0358 0.0068 1.0000
13.250 1.2572 0.08053 0.07547 -0.0380 0.0068 1.0000
13.500 1.2454 0.08632 0.08145 -0.0405 0.0068 1.0000
13.750 1.2328 0.09252 0.08784 -0.0435 0.0067 1.0000
14.000 1.2194 0.09911 0.09461 -0.0469 0.0067 1.0000
14.250 1.2053 0.10607 0.10175 -0.0505 0.0068 1.0000
14.500 1.1909 0.11339 0.10924 -0.0546 0.0068 1.0000
14.750 1.1754 0.12128 0.11731 -0.0591 0.0068 1.0000
15.000 1.1594 0.12970 0.12589 -0.0641 0.0069 1.0000
15.250 1.1428 0.13871 0.13507 -0.0695 0.0070 1.0000
15.500 1.1260 0.14841 0.14493 -0.0754 0.0071 1.0000
15.750 1.1089 0.15894 0.15560 -0.0818 0.0072 1.0000
16.000 1.0910 0.17060 0.16732 -0.0887 0.0074 1.0000
|
Polar data table (+)
Polar graphs
<< Back to I.S.A. 571 (isa571-il)