Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 43.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-120-050-gn-1000000.txt Download as CSV file: xf-cp-120-050-gn-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=12% T=5% R=1.1
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
------ -------- --------- --------- -------- -------- --------
-11.750 0.1273 0.11433 0.11207 -0.1720 0.9567 0.0223
-11.500 0.1373 0.11121 0.10893 -0.1748 0.9542 0.0225
-11.250 0.1508 0.10822 0.10593 -0.1772 0.9526 0.0226
-11.000 0.1670 0.10566 0.10337 -0.1798 0.9511 0.0227
-10.750 0.1858 0.10322 0.10091 -0.1831 0.9499 0.0229
-10.500 0.2058 0.10063 0.09830 -0.1870 0.9489 0.0233
-10.250 0.2275 0.09786 0.09551 -0.1914 0.9478 0.0239
-10.000 0.2377 0.09583 0.09348 -0.1923 0.9443 0.0244
-9.750 0.2483 0.09340 0.09103 -0.1938 0.9405 0.0252
-9.500 0.2632 0.09064 0.08824 -0.1973 0.9376 0.0253
-9.250 0.2815 0.08759 0.08516 -0.2014 0.9353 0.0254
-9.000 0.3035 0.08503 0.08259 -0.2048 0.9335 0.0256
-8.750 0.3156 0.08342 0.08097 -0.2055 0.9298 0.0259
-8.500 0.3249 0.08183 0.07938 -0.2057 0.9253 0.0261
-8.250 0.3406 0.07978 0.07731 -0.2078 0.9219 0.0264
-8.000 0.3610 0.07752 0.07501 -0.2112 0.9189 0.0271
-7.750 0.3739 0.07553 0.07301 -0.2127 0.9149 0.0280
-7.500 0.3783 0.07381 0.07128 -0.2125 0.9092 0.0283
-7.250 0.3899 0.07159 0.06902 -0.2151 0.9045 0.0284
-7.000 0.4102 0.06916 0.06656 -0.2173 0.9015 0.0286
-6.750 0.4143 0.06803 0.06545 -0.2154 0.8968 0.0287
-6.500 0.4230 0.06665 0.06406 -0.2150 0.8922 0.0289
-6.250 0.4374 0.06506 0.06244 -0.2161 0.8882 0.0291
-6.000 0.4501 0.06361 0.06098 -0.2168 0.8839 0.0297
-5.750 0.4524 0.06250 0.05989 -0.2148 0.8787 0.0301
-5.500 0.4581 0.06113 0.05851 -0.2139 0.8738 0.0310
-5.250 0.4687 0.05947 0.05679 -0.2164 0.8682 0.0315
-5.000 0.4728 0.05815 0.05549 -0.2166 0.8626 0.0316
-4.750 0.4836 0.05612 0.05346 -0.2158 0.8589 0.0317
-4.500 0.4992 0.05446 0.05177 -0.2163 0.8554 0.0318
-4.250 0.5152 0.05301 0.05031 -0.2172 0.8516 0.0320
-4.000 0.5250 0.05182 0.04914 -0.2166 0.8473 0.0322
-3.750 0.5388 0.05051 0.04783 -0.2169 0.8431 0.0326
-3.500 0.5576 0.04901 0.04630 -0.2185 0.8393 0.0331
-3.250 0.5787 0.04732 0.04457 -0.2209 0.8354 0.0344
-3.000 0.6040 0.04537 0.04260 -0.2263 0.8306 0.0349
-2.750 0.6209 0.04331 0.04052 -0.2272 0.8261 0.0350
-2.500 0.6384 0.04170 0.03887 -0.2273 0.8217 0.0351
-2.250 0.6512 0.04050 0.03768 -0.2263 0.8151 0.0352
-2.000 0.6682 0.03928 0.03645 -0.2263 0.8099 0.0355
-1.750 0.6919 0.03797 0.03507 -0.2279 0.8034 0.0359
-1.500 0.7090 0.03678 0.03389 -0.2278 0.7986 0.0366
-1.250 0.7413 0.03503 0.03208 -0.2317 0.7927 0.0382
-1.000 0.7874 0.03271 0.02961 -0.2392 0.7870 0.0383
-0.750 0.8014 0.03103 0.02795 -0.2380 0.7820 0.0385
-0.500 0.8131 0.02999 0.02689 -0.2358 0.7738 0.0386
-0.250 0.8264 0.02907 0.02595 -0.2340 0.7668 0.0388
0.000 0.8388 0.02821 0.02506 -0.2318 0.7575 0.0391
0.250 0.8559 0.02730 0.02412 -0.2307 0.7490 0.0396
0.500 0.8706 0.02641 0.02315 -0.2290 0.7366 0.0402
0.750 0.9074 0.02480 0.02136 -0.2319 0.7213 0.0420
1.000 0.9284 0.02353 0.01996 -0.2313 0.7049 0.0421
1.250 0.9319 0.02256 0.01885 -0.2272 0.6756 0.0423
1.500 0.9222 0.02273 0.01877 -0.2198 0.6272 0.0424
1.750 0.8992 0.02373 0.01933 -0.2100 0.5420 0.0425
2.000 0.8689 0.02565 0.02055 -0.1992 0.4035 0.0425
2.250 0.8412 0.02801 0.02211 -0.1896 0.2190 0.0425
2.500 0.8329 0.02938 0.02291 -0.1838 0.0409 0.0426
2.750 0.8538 0.02904 0.02253 -0.1833 0.0348 0.0429
3.000 0.8766 0.02864 0.02209 -0.1831 0.0329 0.0434
3.250 0.9017 0.02813 0.02153 -0.1832 0.0320 0.0444
3.500 0.9472 0.02604 0.01917 -0.1866 0.0312 0.0466
3.750 0.9664 0.02586 0.01898 -0.1856 0.0307 0.0469
4.000 0.9854 0.02582 0.01892 -0.1844 0.0301 0.0472
4.250 1.0048 0.02576 0.01883 -0.1833 0.0294 0.0478
4.500 1.0248 0.02566 0.01868 -0.1821 0.0290 0.0489
4.750 1.0558 0.02431 0.01705 -0.1824 0.0288 0.0518
5.000 1.0717 0.02457 0.01731 -0.1805 0.0284 0.0521
5.250 1.0879 0.02485 0.01758 -0.1787 0.0282 0.0525
5.500 1.1020 0.02527 0.01799 -0.1765 0.0280 0.0533
7.750 1.2429 0.02873 0.02078 -0.1586 0.0269 0.0572
8.000 1.2561 0.02964 0.02171 -0.1564 0.0266 0.0565
8.250 1.2693 0.03030 0.02237 -0.1543 0.0263 0.0560
8.500 1.2818 0.03118 0.02326 -0.1521 0.0260 0.0559
8.750 1.2939 0.03214 0.02423 -0.1499 0.0259 0.0559
9.000 1.3057 0.03316 0.02527 -0.1478 0.0257 0.0560
9.250 1.3177 0.03418 0.02632 -0.1456 0.0255 0.0559
9.500 1.3302 0.03522 0.02738 -0.1436 0.0254 0.0560
9.750 1.3434 0.03627 0.02844 -0.1417 0.0252 0.0566
10.000 1.3567 0.03727 0.02947 -0.1398 0.0250 0.0566
10.250 1.3709 0.03824 0.03047 -0.1381 0.0249 0.0567
10.500 1.3861 0.03915 0.03140 -0.1365 0.0247 0.0570
10.750 1.4029 0.04002 0.03230 -0.1350 0.0247 0.0579
11.000 1.4199 0.04088 0.03318 -0.1336 0.0244 0.0594
11.250 1.4385 0.04168 0.03400 -0.1324 0.0243 0.0612
11.500 1.4596 0.04238 0.03471 -0.1315 0.0241 0.0630
11.750 1.4875 0.04283 0.03514 -0.1313 0.0238 0.0686
12.000 1.5576 0.04230 0.03574 -0.1372 0.0232 1.0000
12.250 1.5698 0.04334 0.03684 -0.1352 0.0230 1.0000
12.500 1.5965 0.04412 0.03765 -0.1349 0.0229 1.0000
12.750 1.6212 0.04504 0.03864 -0.1343 0.0228 1.0000
13.000 1.6476 0.04611 0.03977 -0.1340 0.0227 1.0000
13.250 1.6812 0.04738 0.04113 -0.1345 0.0227 1.0000
13.500 1.7196 0.04918 0.04305 -0.1358 0.0228 1.0000
14.250 1.8590 0.06345 0.05782 -0.1451 0.0234 1.0000
14.500 1.8519 0.06593 0.06048 -0.1406 0.0233 1.0000
14.750 1.8416 0.06853 0.06327 -0.1359 0.0233 1.0000
15.000 1.8304 0.07118 0.06610 -0.1313 0.0233 1.0000
15.250 1.8163 0.07404 0.06915 -0.1268 0.0233 1.0000
15.500 1.7997 0.07701 0.07231 -0.1223 0.0233 1.0000
15.750 1.7823 0.08017 0.07566 -0.1181 0.0233 1.0000
16.000 1.7633 0.08348 0.07916 -0.1142 0.0233 1.0000
16.250 1.7434 0.08698 0.08284 -0.1106 0.0232 1.0000
16.500 1.7216 0.09064 0.08669 -0.1074 0.0232 1.0000
16.750 1.6988 0.09438 0.09062 -0.1045 0.0232 1.0000
17.000 1.6614 0.09733 0.09396 -0.1005 0.0217 1.0000
17.250 1.6428 0.10191 0.09871 -0.0993 0.0215 1.0000
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Polar data table (+)
Polar graphs
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