Coanda 1 (coanda1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Coanda 1 (coanda1-il) Reynolds number: 50,000 Max Cl/Cd: 37.96 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda1-il-50000.txt Download as CSV file: xf-coanda1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4394 0.10940 0.10251 -0.0132 1.0000 0.1151
-8.500 -0.4475 0.10808 0.10131 -0.0150 1.0000 0.1165
-8.250 -0.4585 0.10708 0.10044 -0.0165 1.0000 0.1170
-8.000 -0.4418 0.10055 0.09393 -0.0147 1.0000 0.1196
-7.750 -0.4373 0.09695 0.09037 -0.0139 1.0000 0.1231
-7.500 -0.4391 0.09436 0.08786 -0.0142 1.0000 0.1265
-7.250 -0.4437 0.09260 0.08618 -0.0168 1.0000 0.1293
-7.000 -0.4461 0.09078 0.08441 -0.0203 1.0000 0.1306
-6.750 -0.4338 0.08495 0.07864 -0.0158 1.0000 0.1354
-6.500 -0.3724 0.07028 0.06450 -0.0162 1.0000 0.1509
-6.250 -0.3794 0.06795 0.06221 -0.0186 1.0000 0.1570
-6.000 -0.4206 0.07540 0.06918 -0.0168 1.0000 0.1523
-5.750 -0.4158 0.07241 0.06618 -0.0183 1.0000 0.1599
-5.500 -0.4099 0.06931 0.06307 -0.0178 1.0000 0.1735
-5.250 -0.4037 0.06603 0.05984 -0.0155 1.0000 0.1908
-5.000 -0.1647 0.04666 0.03995 0.0039 1.0000 0.9219
-4.750 -0.2066 0.04705 0.04058 0.0131 1.0000 0.8794
-4.500 -0.2434 0.04692 0.04068 0.0202 1.0000 0.8399
-4.250 -0.2725 0.04623 0.04019 0.0263 1.0000 0.8226
-4.000 -0.2614 0.04290 0.03690 0.0259 1.0000 0.8344
-3.750 -0.3984 0.04912 0.04343 0.0113 1.0000 0.4512
-3.500 -0.4035 0.04633 0.04081 0.0203 1.0000 0.5152
-3.250 -0.4073 0.04349 0.03811 0.0284 1.0000 0.5712
-3.000 -0.4152 0.04033 0.03513 0.0392 1.0000 0.6395
-2.750 -0.2486 0.03329 0.02463 -0.0095 1.0000 0.2091
-2.500 -0.2375 0.03099 0.02227 -0.0067 1.0000 0.2608
-2.250 -0.2164 0.02916 0.01998 -0.0052 1.0000 0.2721
-2.000 -0.1911 0.02778 0.01809 -0.0045 1.0000 0.2631
-1.750 -0.1656 0.02678 0.01655 -0.0038 1.0000 0.2561
-1.500 -0.1412 0.02597 0.01532 -0.0030 1.0000 0.2539
-1.250 -0.1173 0.02517 0.01430 -0.0024 1.0000 0.2565
-1.000 -0.0930 0.02462 0.01347 -0.0018 1.0000 0.2556
-0.750 -0.0665 0.02411 0.01273 -0.0017 1.0000 0.2534
-0.500 -0.0345 0.02368 0.01206 -0.0027 1.0000 0.2521
-0.250 -0.0022 0.02336 0.01149 -0.0039 1.0000 0.2517
0.000 0.0281 0.02315 0.01114 -0.0048 1.0000 0.2523
0.250 0.0560 0.02302 0.01092 -0.0053 1.0000 0.2544
0.500 0.0817 0.02293 0.01086 -0.0056 1.0000 0.2568
0.750 0.1050 0.02294 0.01093 -0.0057 1.0000 0.2646
1.000 0.1265 0.02304 0.01110 -0.0056 1.0000 0.2753
1.250 0.1467 0.02326 0.01141 -0.0054 1.0000 0.2852
1.500 0.1660 0.02357 0.01184 -0.0052 1.0000 0.2966
1.750 0.1854 0.02389 0.01241 -0.0052 1.0000 0.3178
2.000 0.2701 0.02345 0.01355 -0.0178 1.0000 1.0000
2.250 0.3338 0.02459 0.01455 -0.0266 0.9791 1.0000
2.500 0.4304 0.02501 0.01498 -0.0401 0.9415 1.0000
2.750 0.5161 0.02450 0.01469 -0.0502 0.9033 1.0000
3.000 0.5940 0.02352 0.01401 -0.0579 0.8669 1.0000
3.250 0.6616 0.02215 0.01304 -0.0626 0.8257 1.0000
3.500 0.7149 0.02093 0.01205 -0.0640 0.7739 1.0000
3.750 0.7542 0.02037 0.01146 -0.0628 0.7074 1.0000
4.000 0.7779 0.02055 0.01136 -0.0593 0.6294 1.0000
4.250 0.7910 0.02084 0.01120 -0.0545 0.5514 1.0000
4.500 0.8052 0.02142 0.01149 -0.0509 0.4853 1.0000
4.750 0.8256 0.02222 0.01217 -0.0490 0.4387 1.0000
5.000 0.8469 0.02301 0.01290 -0.0473 0.4030 1.0000
5.250 0.8664 0.02373 0.01363 -0.0454 0.3698 1.0000
5.500 0.8806 0.02432 0.01414 -0.0427 0.3307 1.0000
5.750 0.8989 0.02497 0.01496 -0.0407 0.3027 1.0000
6.000 0.9070 0.02544 0.01539 -0.0371 0.2471 1.0000
6.250 0.9167 0.02659 0.01631 -0.0340 0.1603 1.0000
6.500 0.9303 0.02866 0.01796 -0.0314 0.0998 1.0000
6.750 0.9451 0.03057 0.01972 -0.0289 0.0843 1.0000
7.000 0.9607 0.03246 0.02164 -0.0266 0.0762 1.0000
7.250 0.9758 0.03453 0.02367 -0.0244 0.0695 1.0000
7.500 0.9966 0.03681 0.02619 -0.0226 0.0661 1.0000
7.750 1.0198 0.03959 0.02929 -0.0211 0.0647 1.0000
8.000 1.0405 0.04287 0.03298 -0.0194 0.0643 1.0000
8.250 1.0553 0.04660 0.03722 -0.0173 0.0646 1.0000
8.500 1.0640 0.05061 0.04172 -0.0148 0.0653 1.0000
8.750 1.0677 0.05476 0.04633 -0.0121 0.0662 1.0000
9.000 1.0669 0.05914 0.05109 -0.0093 0.0672 1.0000
9.250 1.0639 0.06357 0.05580 -0.0068 0.0681 1.0000
9.500 1.0623 0.06823 0.06064 -0.0048 0.0689 1.0000
9.750 1.0392 0.07184 0.06475 -0.0014 0.0702 1.0000
10.000 1.0063 0.07597 0.06914 0.0016 0.0709 1.0000
10.250 0.9728 0.08085 0.07419 0.0022 0.0716 1.0000
10.500 0.9387 0.08751 0.08095 -0.0009 0.0725 1.0000
10.750 0.9048 0.09700 0.09045 -0.0076 0.0738 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Coanda 1 (coanda1-il)