Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 52.28 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-180-050-gn-1000000.txt Download as CSV file: xf-cp-180-050-gn-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 0.5214 0.11449 0.11181 -0.2813 0.9074 0.0119
-14.750 0.5224 0.11305 0.11038 -0.2798 0.9042 0.0120
-14.500 0.5293 0.11117 0.10849 -0.2803 0.9016 0.0120
-14.250 0.5401 0.10863 0.10592 -0.2823 0.8995 0.0121
-14.000 0.5563 0.10625 0.10350 -0.2856 0.8977 0.0121
-13.750 0.5769 0.10384 0.10106 -0.2901 0.8959 0.0123
-13.500 0.5836 0.10250 0.09971 -0.2901 0.8934 0.0126
-13.250 0.5821 0.10163 0.09886 -0.2874 0.8901 0.0130
-13.000 0.5875 0.10021 0.09743 -0.2870 0.8872 0.0132
-12.750 0.5991 0.09824 0.09544 -0.2886 0.8849 0.0140
-12.500 0.6154 0.09589 0.09305 -0.2917 0.8828 0.0143
-12.250 0.6362 0.09313 0.09024 -0.2964 0.8807 0.0144
-12.000 0.6320 0.09237 0.08951 -0.2929 0.8776 0.0144
-11.750 0.6498 0.07421 0.07144 -0.2802 0.8610 0.0146
-11.500 0.6532 0.07298 0.07022 -0.2790 0.8580 0.0148
-11.250 0.6608 0.07158 0.06881 -0.2790 0.8555 0.0152
-11.000 0.6719 0.06975 0.06695 -0.2802 0.8530 0.0156
-10.750 0.6883 0.06752 0.06467 -0.2831 0.8506 0.0162
-10.500 0.6821 0.06690 0.06409 -0.2790 0.8476 0.0164
-10.250 0.6784 0.06593 0.06313 -0.2757 0.8441 0.0168
-10.000 0.6774 0.06470 0.06190 -0.2734 0.8408 0.0170
-9.750 0.6863 0.06297 0.06014 -0.2740 0.8382 0.0171
-8.750 0.6963 0.07485 0.07191 -0.2832 0.8388 0.0173
-8.500 0.7136 0.07319 0.07020 -0.2856 0.8361 0.0175
-8.250 0.7081 0.07271 0.06975 -0.2815 0.8330 0.0176
-8.000 0.7019 0.07227 0.06934 -0.2771 0.8294 0.0179
-7.750 0.7003 0.07152 0.06859 -0.2742 0.8259 0.0180
-7.500 0.7072 0.07033 0.06738 -0.2736 0.8229 0.0185
-7.250 0.7237 0.06866 0.06566 -0.2759 0.8200 0.0192
-7.000 0.6979 0.06919 0.06627 -0.2661 0.8160 0.0190
-6.750 0.6857 0.06888 0.06600 -0.2603 0.8120 0.0195
-6.500 0.6817 0.06820 0.06530 -0.2569 0.8084 0.0197
-6.250 0.6893 0.06691 0.06397 -0.2571 0.8049 0.0199
-6.000 0.6638 0.06736 0.06450 -0.2478 0.8009 0.0199
-5.750 0.6509 0.06708 0.06425 -0.2421 0.7967 0.0199
-5.500 0.6513 0.06606 0.06322 -0.2402 0.7931 0.0199
-5.250 0.6643 0.06399 0.06111 -0.2412 0.7902 0.0200
-5.000 0.6620 0.06317 0.06032 -0.2381 0.7871 0.0201
-4.750 0.6485 0.06295 0.06015 -0.2321 0.7831 0.0202
-4.500 0.6482 0.06220 0.05940 -0.2294 0.7796 0.0203
-4.250 0.6583 0.06095 0.05813 -0.2294 0.7766 0.0206
-4.000 0.6799 0.05918 0.05631 -0.2324 0.7738 0.0209
-3.750 0.6699 0.05885 0.05604 -0.2273 0.7703 0.0212
-3.500 0.6685 0.05811 0.05532 -0.2245 0.7667 0.0216
-3.250 0.6760 0.05690 0.05411 -0.2239 0.7635 0.0222
-3.000 0.6942 0.05514 0.05231 -0.2260 0.7606 0.0226
-2.750 0.7313 0.05276 0.04986 -0.2332 0.7579 0.0228
-2.250 0.7372 0.05055 0.04771 -0.2295 0.7514 0.0229
-2.000 0.7482 0.04936 0.04652 -0.2292 0.7484 0.0231
-1.750 0.7699 0.04794 0.04507 -0.2314 0.7457 0.0234
-1.500 0.8007 0.04623 0.04331 -0.2357 0.7433 0.0239
-1.250 0.8364 0.04438 0.04142 -0.2412 0.7410 0.0249
-1.000 0.8519 0.04332 0.04038 -0.2420 0.7381 0.0256
-0.750 0.8935 0.04166 0.03869 -0.2491 0.7356 0.0258
-0.500 0.9340 0.03989 0.03689 -0.2557 0.7332 0.0259
-0.250 0.9541 0.03839 0.03537 -0.2569 0.7306 0.0261
0.000 0.9885 0.03703 0.03398 -0.2613 0.7284 0.0264
0.250 1.0339 0.03546 0.03234 -0.2681 0.7263 0.0270
0.500 1.0778 0.03401 0.03087 -0.2746 0.7243 0.0283
0.750 1.1376 0.03269 0.02949 -0.2848 0.7221 0.0289
1.000 1.1874 0.03125 0.02802 -0.2925 0.7196 0.0290
1.250 1.1984 0.03050 0.02724 -0.2911 0.7126 0.0291
1.500 1.2375 0.02942 0.02609 -0.2957 0.7087 0.0295
1.750 1.2600 0.02909 0.02579 -0.2968 0.7050 0.0299
2.000 1.2969 0.02834 0.02502 -0.3009 0.7017 0.0310
2.250 1.3482 0.02765 0.02422 -0.3079 0.6955 0.0319
2.500 1.4037 0.02685 0.02333 -0.3158 0.6914 0.0320
6.500 1.3567 0.05898 0.05236 -0.2558 0.0215 0.0358
6.750 1.3750 0.05995 0.05333 -0.2558 0.0200 0.0362
7.000 1.3953 0.06098 0.05434 -0.2560 0.0193 0.0369
7.250 1.4178 0.06210 0.05545 -0.2566 0.0188 0.0384
7.500 1.4506 0.06343 0.05667 -0.2586 0.0185 0.0394
7.750 1.4702 0.06449 0.05772 -0.2589 0.0182 0.0399
8.000 1.4853 0.06579 0.05902 -0.2582 0.0180 0.0403
8.250 1.5019 0.06712 0.06036 -0.2577 0.0179 0.0409
8.500 1.5192 0.06859 0.06181 -0.2573 0.0177 0.0420
8.750 1.5487 0.06998 0.06306 -0.2588 0.0176 0.0445
9.000 1.5600 0.07164 0.06475 -0.2575 0.0174 0.0451
9.250 1.5725 0.07329 0.06641 -0.2564 0.0172 0.0461
9.500 1.5931 0.07494 0.06791 -0.2561 0.0171 0.0493
9.750 1.6056 0.07681 0.06981 -0.2554 0.0169 0.0505
10.000 1.6147 0.07879 0.07183 -0.2539 0.0167 0.0514
10.250 1.6257 0.08074 0.07377 -0.2526 0.0165 0.0534
10.500 1.6374 0.08290 0.07584 -0.2516 0.0163 0.0568
10.750 1.6446 0.08520 0.07819 -0.2500 0.0162 0.0580
11.000 1.6522 0.08748 0.08050 -0.2485 0.0160 0.0604
11.250 1.6586 0.09005 0.08306 -0.2470 0.0158 0.0651
11.500 1.6638 0.09266 0.08572 -0.2454 0.0157 0.0673
11.750 1.6679 0.09522 0.08830 -0.2435 0.0155 0.0715
12.000 1.6785 0.09795 0.09088 -0.2427 0.0153 0.0483
12.250 1.6806 0.10103 0.09399 -0.2410 0.0151 0.0480
12.500 1.6827 0.10410 0.09711 -0.2394 0.0149 0.0475
12.750 1.6851 0.10711 0.10018 -0.2378 0.0149 0.0472
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Polar data table (+)
Polar graphs
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