Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 47.54 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-180-050-gn-1000000-n5.txt Download as CSV file: xf-cp-180-050-gn-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=18% T=5% R=0.78
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 0.5192 0.10767 0.10471 -0.2713 0.8647 0.0089
-13.500 0.5250 0.10586 0.10292 -0.2713 0.8622 0.0091
-13.250 0.5309 0.10399 0.10104 -0.2714 0.8593 0.0101
-13.000 0.5378 0.10223 0.09926 -0.2717 0.8564 0.0096
-12.750 0.5482 0.10109 0.09811 -0.2725 0.8538 0.0118
-12.500 0.5561 0.09929 0.09627 -0.2731 0.8511 0.0106
-12.250 0.5624 0.09757 0.09456 -0.2731 0.8488 0.0119
-12.000 0.5665 0.09580 0.09279 -0.2726 0.8459 0.0102
-11.750 0.5742 0.09474 0.09173 -0.2725 0.8429 0.0112
-11.500 0.5792 0.09300 0.08997 -0.2722 0.8398 0.0107
-11.250 0.5858 0.09147 0.08841 -0.2721 0.8369 0.0112
-11.000 0.5914 0.08991 0.08685 -0.2718 0.8343 0.0113
-10.750 0.5952 0.08849 0.08544 -0.2709 0.8315 0.0115
-10.500 0.5992 0.08717 0.08412 -0.2700 0.8283 0.0111
-10.250 0.6027 0.08577 0.08271 -0.2690 0.8250 0.0116
-10.000 0.6076 0.08456 0.08149 -0.2682 0.8220 0.0125
-9.750 0.6138 0.08368 0.08060 -0.2674 0.8193 0.0132
-9.500 0.6138 0.08223 0.07916 -0.2655 0.8164 0.0127
-9.250 0.6137 0.08133 0.07827 -0.2631 0.8128 0.0143
-8.750 0.6141 0.07947 0.07640 -0.2587 0.8059 0.0138
-8.500 0.6142 0.07837 0.07530 -0.2566 0.8030 0.0141
-8.250 0.6135 0.07745 0.07440 -0.2542 0.7999 0.0137
-7.750 0.6060 0.07587 0.07283 -0.2476 0.7922 0.0141
-7.500 0.6042 0.07495 0.07190 -0.2450 0.7889 0.0140
-7.250 0.6028 0.07438 0.07136 -0.2422 0.7861 0.0151
-7.000 0.5873 0.07335 0.07036 -0.2367 0.7819 0.0145
-6.750 0.5842 0.07305 0.07006 -0.2332 0.7780 0.0147
-6.250 0.5750 0.07278 0.06981 -0.2256 0.7712 0.0167
-6.000 0.5644 0.07227 0.06934 -0.2208 0.7676 0.0169
-5.750 0.5615 0.07139 0.06847 -0.2179 0.7637 0.0169
-5.500 0.5571 0.07060 0.06766 -0.2146 0.7598 0.0169
-5.250 0.5568 0.06976 0.06683 -0.2123 0.7564 0.0161
-5.000 0.5575 0.06866 0.06575 -0.2104 0.7534 0.0161
-4.750 0.5575 0.06755 0.06466 -0.2083 0.7499 0.0159
-4.500 0.5573 0.06657 0.06367 -0.2061 0.7461 0.0164
-4.250 0.5610 0.06536 0.06244 -0.2049 0.7425 0.0165
-4.000 0.5667 0.06406 0.06115 -0.2042 0.7395 0.0165
-3.750 0.5721 0.06231 0.05942 -0.2038 0.7364 0.0173
-3.500 0.5778 0.06149 0.05861 -0.2027 0.7330 0.0175
-3.250 0.5886 0.05928 0.05637 -0.2039 0.7296 0.0172
-3.000 0.6006 0.05798 0.05504 -0.2043 0.7263 0.0173
-2.750 0.6127 0.05731 0.05438 -0.2042 0.7236 0.0177
-2.500 0.6264 0.05603 0.05311 -0.2050 0.7207 0.0180
-2.250 0.6418 0.05455 0.05163 -0.2063 0.7178 0.0181
-2.000 0.6603 0.05311 0.05017 -0.2082 0.7147 0.0186
-1.750 0.6823 0.05146 0.04848 -0.2109 0.7116 0.0188
-1.500 0.7074 0.04975 0.04673 -0.2143 0.7088 0.0189
-0.750 0.7925 0.04516 0.04211 -0.2257 0.7017 0.0211
-0.500 0.8248 0.04361 0.04053 -0.2303 0.6988 0.0218
-0.250 0.8614 0.04195 0.03883 -0.2357 0.6961 0.0222
0.000 0.9003 0.04032 0.03714 -0.2416 0.6936 0.0221
0.250 0.9369 0.03903 0.03583 -0.2466 0.6915 0.0236
0.500 0.9831 0.03729 0.03406 -0.2538 0.6897 0.0236
0.750 1.0239 0.03600 0.03275 -0.2595 0.6874 0.0242
1.000 1.0685 0.03461 0.03131 -0.2660 0.6848 0.0245
1.250 1.1089 0.03349 0.03013 -0.2715 0.6798 0.0248
1.750 1.1838 0.03179 0.02833 -0.2806 0.6671 0.0266
2.000 1.2197 0.03110 0.02758 -0.2846 0.6616 0.0268
2.250 1.2628 0.03033 0.02675 -0.2900 0.6570 0.0287
2.500 1.2935 0.02987 0.02626 -0.2927 0.6502 0.0282
2.750 1.3384 0.02931 0.02558 -0.2985 0.6413 0.0288
3.000 1.3631 0.02908 0.02531 -0.2997 0.6324 0.0286
3.250 1.3860 0.02923 0.02538 -0.3005 0.6194 0.0286
3.500 1.4062 0.02958 0.02564 -0.3008 0.6077 0.0293
3.750 1.4131 0.03053 0.02649 -0.2983 0.5865 0.0298
4.000 1.4219 0.03159 0.02744 -0.2963 0.5655 0.0299
4.250 1.4270 0.03290 0.02860 -0.2936 0.5425 0.0304
4.500 1.4139 0.03538 0.03086 -0.2878 0.5000 0.0310
4.750 1.3813 0.03926 0.03439 -0.2788 0.4353 0.0306
5.000 1.3672 0.04226 0.03711 -0.2734 0.3828 0.0307
5.250 1.3353 0.04666 0.04110 -0.2653 0.3014 0.0309
5.500 1.3056 0.05123 0.04526 -0.2580 0.2046 0.0309
5.750 1.2790 0.05598 0.04954 -0.2516 0.0599 0.0306
6.000 1.2990 0.05731 0.05073 -0.2523 0.0173 0.0310
6.250 1.3278 0.05814 0.05150 -0.2542 0.0153 0.0314
6.500 1.3553 0.05897 0.05229 -0.2558 0.0144 0.0312
6.750 1.3904 0.05973 0.05295 -0.2587 0.0140 0.0323
7.000 1.4072 0.06075 0.05397 -0.2583 0.0137 0.0327
7.250 1.4281 0.06176 0.05496 -0.2585 0.0135 0.0333
7.500 1.4507 0.06287 0.05603 -0.2590 0.0133 0.0335
7.750 1.4726 0.06408 0.05721 -0.2594 0.0131 0.0344
8.000 1.4970 0.06521 0.05827 -0.2602 0.0128 0.0337
8.250 1.5221 0.06632 0.05930 -0.2610 0.0126 0.0339
8.500 1.5492 0.06739 0.06025 -0.2620 0.0124 0.0346
8.750 1.5879 0.06796 0.06041 -0.2647 0.0123 0.0353
9.000 1.6039 0.06938 0.06169 -0.2640 0.0121 0.0357
9.250 1.6156 0.07106 0.06335 -0.2626 0.0120 0.0360
9.500 1.6270 0.07272 0.06501 -0.2611 0.0119 0.0363
9.750 1.6380 0.07442 0.06671 -0.2596 0.0118 0.0366
10.000 1.6471 0.07638 0.06869 -0.2580 0.0117 0.0369
10.250 1.6563 0.07834 0.07066 -0.2564 0.0115 0.0371
10.500 1.6653 0.08032 0.07267 -0.2549 0.0114 0.0373
10.750 1.6725 0.08254 0.07492 -0.2532 0.0113 0.0376
11.000 1.6782 0.08499 0.07744 -0.2514 0.0112 0.0380
11.250 1.6860 0.08715 0.07964 -0.2498 0.0111 0.0383
11.500 1.6941 0.08930 0.08182 -0.2483 0.0110 0.0383
11.750 1.7011 0.09161 0.08418 -0.2468 0.0110 0.0384
12.000 1.7094 0.09373 0.08635 -0.2454 0.0109 0.0385
12.250 1.7165 0.09601 0.08868 -0.2440 0.0108 0.0386
12.500 1.7223 0.09850 0.09123 -0.2425 0.0108 0.0388
12.750 1.7288 0.10086 0.09365 -0.2411 0.0107 0.0391
13.000 1.7350 0.10326 0.09610 -0.2397 0.0106 0.0393
13.250 1.7404 0.10582 0.09871 -0.2384 0.0105 0.0402
13.500 1.7469 0.10816 0.10111 -0.2372 0.0103 0.0414
13.750 1.7534 0.11048 0.10349 -0.2359 0.0102 0.0431
14.000 1.7581 0.11308 0.10615 -0.2347 0.0101 0.0462
|
Polar data table (+)
Polar graphs
<< Back to Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)