Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Reynolds number: 500,000 Max Cl/Cd: 55.32 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-180-050-gn-500000.txt Download as CSV file: xf-cp-180-050-gn-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 0.4701 0.11027 0.10719 -0.2465 0.9028 0.0149
-14.750 0.4810 0.10812 0.10503 -0.2483 0.9012 0.0152
-14.500 0.4945 0.10565 0.10253 -0.2510 0.9000 0.0156
-14.250 0.5094 0.10292 0.09976 -0.2542 0.8990 0.0163
-14.000 0.5249 0.10020 0.09701 -0.2575 0.8980 0.0166
-13.750 0.5409 0.09734 0.09412 -0.2610 0.8971 0.0169
-13.500 0.5566 0.09454 0.09127 -0.2644 0.8961 0.0171
-8.500 0.6409 0.08104 0.07753 -0.2648 0.8545 0.0214
-8.250 0.6619 0.07883 0.07528 -0.2685 0.8529 0.0220
-8.000 0.6861 0.07649 0.07289 -0.2732 0.8514 0.0226
-7.750 0.6174 0.07975 0.07631 -0.2512 0.8429 0.0223
-7.500 0.6259 0.07820 0.07474 -0.2514 0.8402 0.0226
-7.250 0.6422 0.07652 0.07302 -0.2540 0.8382 0.0228
-5.750 0.5441 0.07681 0.07351 -0.2144 0.8111 0.0229
-5.500 0.5575 0.07477 0.07145 -0.2155 0.8091 0.0231
-5.250 0.5779 0.07257 0.06922 -0.2185 0.8076 0.0235
-5.000 0.6019 0.07026 0.06687 -0.2224 0.8062 0.0239
-4.750 0.5263 0.07397 0.07073 -0.2009 0.7958 0.0235
-4.500 0.5409 0.07210 0.06884 -0.2024 0.7938 0.0241
-4.250 0.5628 0.06982 0.06652 -0.2057 0.7923 0.0246
-4.000 0.5893 0.06733 0.06399 -0.2101 0.7910 0.0254
-3.750 0.5235 0.07055 0.06734 -0.1917 0.7809 0.0250
-3.500 0.5407 0.06859 0.06536 -0.1937 0.7786 0.0255
-3.250 0.5683 0.06620 0.06293 -0.1985 0.7772 0.0257
-2.750 0.6340 0.06076 0.05739 -0.2103 0.7750 0.0259
-2.500 0.6647 0.05817 0.05476 -0.2149 0.7739 0.0263
-0.500 0.8007 0.04886 0.04539 -0.2263 0.7473 0.0290
-0.250 0.8352 0.04664 0.04313 -0.2309 0.7461 0.0293
0.000 0.8822 0.04453 0.04097 -0.2383 0.7453 0.0300
0.250 0.9379 0.04225 0.03862 -0.2477 0.7446 0.0310
0.500 1.0164 0.04003 0.03630 -0.2622 0.7441 0.0319
0.750 1.0882 0.03768 0.03385 -0.2751 0.7436 0.0321
1.000 1.1267 0.03564 0.03178 -0.2799 0.7425 0.0324
1.250 1.1845 0.03386 0.02994 -0.2890 0.7418 0.0332
2.250 1.3351 0.03083 0.02681 -0.3066 0.7297 0.0357
2.500 1.3966 0.02881 0.02466 -0.3154 0.7260 0.0365
2.750 1.3890 0.02962 0.02555 -0.3098 0.7192 0.0367
3.000 1.4222 0.02895 0.02482 -0.3125 0.7134 0.0379
3.250 1.5120 0.02733 0.02296 -0.3268 0.7088 0.0395
3.500 1.4999 0.02813 0.02387 -0.3201 0.7023 0.0397
3.750 1.5185 0.02770 0.02340 -0.3196 0.6953 0.0402
4.000 1.5342 0.02789 0.02360 -0.3185 0.6883 0.0410
4.250 1.5520 0.02810 0.02377 -0.3178 0.6800 0.0420
4.500 1.5647 0.02872 0.02436 -0.3160 0.6691 0.0432
4.750 1.5928 0.02930 0.02478 -0.3171 0.6546 0.0442
5.000 1.5903 0.03030 0.02574 -0.3125 0.6368 0.0445
5.250 1.5816 0.03196 0.02726 -0.3069 0.6109 0.0447
5.500 1.5661 0.03435 0.02948 -0.3002 0.5769 0.0450
5.750 1.5433 0.03752 0.03242 -0.2926 0.5336 0.0452
6.000 1.5175 0.04126 0.03591 -0.2849 0.4882 0.0453
6.250 1.4881 0.04564 0.03999 -0.2771 0.4338 0.0454
6.500 1.4565 0.05052 0.04454 -0.2695 0.3691 0.0454
6.750 1.4198 0.05620 0.04978 -0.2616 0.2806 0.0452
7.000 1.3914 0.06148 0.05464 -0.2553 0.1843 0.0452
7.250 1.3671 0.06670 0.05944 -0.2500 0.0502 0.0454
7.500 1.3811 0.06849 0.06115 -0.2495 0.0304 0.0465
7.750 1.4154 0.07023 0.06277 -0.2517 0.0286 0.0494
8.000 1.4295 0.07139 0.06397 -0.2513 0.0275 0.0500
8.250 1.4440 0.07278 0.06540 -0.2507 0.0267 0.0508
8.500 1.4601 0.07430 0.06694 -0.2503 0.0260 0.0523
8.750 1.4873 0.07615 0.06866 -0.2515 0.0252 0.0559
9.000 1.4961 0.07806 0.07063 -0.2502 0.0244 0.0567
9.250 1.5058 0.08007 0.07268 -0.2490 0.0240 0.0582
9.500 1.5248 0.08237 0.07487 -0.2490 0.0237 0.0635
9.750 1.5291 0.08488 0.07748 -0.2474 0.0234 0.0646
10.000 1.5377 0.08700 0.07966 -0.2461 0.0233 0.0667
10.250 1.5533 0.08925 0.08181 -0.2457 0.0232 0.0731
10.500 1.5598 0.09168 0.08432 -0.2443 0.0230 0.0745
10.750 1.5670 0.09410 0.08679 -0.2430 0.0229 0.0772
11.000 1.5769 0.09665 0.08930 -0.2420 0.0227 0.0847
11.250 1.5817 0.09935 0.09207 -0.2406 0.0226 0.0872
11.500 1.5891 0.10198 0.09470 -0.2394 0.0225 0.0968
11.750 1.5937 0.10472 0.09752 -0.2381 0.0224 0.1000
12.000 1.5994 0.10743 0.10024 -0.2368 0.0224 0.1107
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Polar data table (+)
Polar graphs
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