Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn) Reynolds number: 500,000 Max Cl/Cd: 53.88 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-140-050-gn-500000.txt Download as CSV file: xf-cp-140-050-gn-500000.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=14% T=5% R=0.96
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
------ -------- --------- --------- -------- -------- --------
-11.000 0.3099 0.10414 0.10095 -0.2115 0.9347 0.0245
-10.750 0.2933 0.10423 0.10108 -0.2044 0.9269 0.0248
-10.500 0.3105 0.10156 0.09838 -0.2079 0.9253 0.0250
-10.000 0.3484 0.09572 0.09249 -0.2157 0.9230 0.0253
-9.750 0.3690 0.09302 0.08978 -0.2194 0.9220 0.0255
-9.500 0.3908 0.09044 0.08717 -0.2235 0.9209 0.0259
-9.250 0.4132 0.08787 0.08457 -0.2278 0.9197 0.0264
-9.000 0.3997 0.08777 0.08451 -0.2214 0.9127 0.0267
-8.750 0.4140 0.08570 0.08242 -0.2233 0.9101 0.0272
-8.500 0.4324 0.08333 0.08003 -0.2266 0.9080 0.0280
-8.250 0.4532 0.08114 0.07779 -0.2310 0.9060 0.0281
-7.750 0.4563 0.07892 0.07559 -0.2278 0.8967 0.0282
-7.500 0.4713 0.07628 0.07294 -0.2287 0.8945 0.0285
-7.250 0.4894 0.07422 0.07085 -0.2311 0.8922 0.0287
-7.000 0.5098 0.07215 0.06875 -0.2341 0.8902 0.0291
-6.750 0.5099 0.07127 0.06789 -0.2315 0.8856 0.0295
-6.500 0.5079 0.07048 0.06712 -0.2284 0.8805 0.0300
-6.250 0.5208 0.06877 0.06539 -0.2294 0.8774 0.0307
-6.000 0.5374 0.06694 0.06353 -0.2318 0.8746 0.0312
-5.750 0.5237 0.06691 0.06353 -0.2258 0.8687 0.0313
-5.500 0.5237 0.06635 0.06298 -0.2243 0.8635 0.0313
-5.250 0.5422 0.06455 0.06114 -0.2276 0.8606 0.0314
-5.000 0.5630 0.06175 0.05833 -0.2294 0.8589 0.0316
-4.750 0.5625 0.06082 0.05742 -0.2263 0.8545 0.0317
-4.500 0.5561 0.06021 0.05684 -0.2217 0.8491 0.0318
-4.250 0.5734 0.05857 0.05519 -0.2232 0.8463 0.0322
-4.000 0.5981 0.05670 0.05329 -0.2267 0.8441 0.0328
-3.750 0.6277 0.05464 0.05117 -0.2315 0.8420 0.0338
-3.500 0.5982 0.05503 0.05165 -0.2209 0.8347 0.0338
-3.250 0.6157 0.05352 0.05012 -0.2226 0.8312 0.0344
-3.000 0.6626 0.05171 0.04822 -0.2330 0.8289 0.0347
-2.750 0.6925 0.04909 0.04556 -0.2372 0.8270 0.0348
-2.500 0.6780 0.04852 0.04505 -0.2299 0.8216 0.0349
-2.250 0.6724 0.04754 0.04410 -0.2247 0.8166 0.0350
-2.000 0.6980 0.04579 0.04233 -0.2272 0.8143 0.0354
-1.750 0.7345 0.04387 0.04037 -0.2325 0.8125 0.0360
-1.500 0.7786 0.04179 0.03823 -0.2396 0.8109 0.0371
-1.250 0.7867 0.04087 0.03732 -0.2378 0.8065 0.0378
-1.000 0.8184 0.03991 0.03632 -0.2421 0.8020 0.0382
-0.500 0.8782 0.03588 0.03224 -0.2480 0.7972 0.0386
-0.250 0.9203 0.03408 0.03040 -0.2535 0.7951 0.0391
0.000 0.9382 0.03302 0.02933 -0.2532 0.7903 0.0397
0.250 0.9508 0.03212 0.02844 -0.2516 0.7854 0.0403
0.750 1.0686 0.02811 0.02417 -0.2694 0.7765 0.0426
1.000 1.0602 0.02767 0.02379 -0.2626 0.7699 0.0427
1.250 1.0851 0.02655 0.02264 -0.2632 0.7641 0.0433
1.500 1.1143 0.02553 0.02157 -0.2647 0.7578 0.0441
1.750 1.1272 0.02489 0.02093 -0.2625 0.7497 0.0451
2.000 1.1839 0.02355 0.01935 -0.2694 0.7409 0.0470
2.250 1.1901 0.02290 0.01870 -0.2658 0.7297 0.0473
2.500 1.1978 0.02256 0.01836 -0.2624 0.7172 0.0477
2.750 1.2069 0.02240 0.01811 -0.2592 0.6996 0.0483
3.000 1.2112 0.02251 0.01807 -0.2549 0.6718 0.0490
3.250 1.2085 0.02301 0.01835 -0.2493 0.6335 0.0498
3.500 1.1943 0.02417 0.01920 -0.2417 0.5818 0.0502
3.750 1.1674 0.02620 0.02083 -0.2321 0.5119 0.0504
4.000 1.1448 0.02846 0.02266 -0.2238 0.4345 0.0509
4.250 1.1111 0.03170 0.02531 -0.2143 0.3160 0.0506
4.500 1.0822 0.03508 0.02805 -0.2061 0.1650 0.0506
5.000 1.1102 0.03685 0.02926 -0.2036 0.0389 0.0528
5.250 1.1277 0.03710 0.02952 -0.2027 0.0369 0.0534
5.500 1.1462 0.03746 0.02987 -0.2019 0.0351 0.0546
6.000 1.1901 0.03816 0.03042 -0.2011 0.0331 0.0591
6.250 1.2053 0.03876 0.03104 -0.1998 0.0327 0.0600
6.500 1.2217 0.03941 0.03168 -0.1986 0.0324 0.0615
6.750 1.2451 0.03979 0.03190 -0.1981 0.0320 0.0660
7.000 1.2573 0.04072 0.03286 -0.1964 0.0317 0.0669
7.250 1.2702 0.04171 0.03386 -0.1947 0.0312 0.0686
9.500 1.3788 0.05319 0.04492 -0.1788 0.0292 0.0717
9.750 1.3891 0.05473 0.04645 -0.1770 0.0291 0.0699
10.000 1.4005 0.05622 0.04785 -0.1752 0.0290 0.0658
10.250 1.4110 0.05780 0.04943 -0.1733 0.0290 0.0650
10.500 1.4242 0.05906 0.05071 -0.1717 0.0289 0.0646
10.750 1.4386 0.06022 0.05189 -0.1702 0.0289 0.0644
11.000 1.4550 0.06121 0.05287 -0.1688 0.0287 0.0649
11.250 1.4750 0.06185 0.05349 -0.1678 0.0283 0.0658
11.500 1.5016 0.06197 0.05360 -0.1671 0.0282 0.0675
11.750 1.5262 0.06233 0.05402 -0.1663 0.0285 0.0705
15.250 1.6693 0.08775 0.08320 -0.1386 0.0301 1.0000
16.000 1.6214 0.09787 0.09387 -0.1318 0.0293 1.0000
16.250 1.6064 0.10135 0.09749 -0.1302 0.0291 1.0000
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Polar data table (+)
Polar graphs
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