Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 48.91 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-160-050-gn-1000000-n5.txt Download as CSV file: xf-cp-160-050-gn-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=16% T=5% R=0.86
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
------ -------- --------- --------- -------- -------- --------
-13.500 0.3972 0.10995 0.10716 -0.2456 0.8878 0.0103
-13.250 0.4069 0.10833 0.10553 -0.2465 0.8851 0.0116
-13.000 0.4123 0.10507 0.10225 -0.2474 0.8821 0.0110
-12.750 0.4234 0.10298 0.10013 -0.2490 0.8792 0.0111
-12.500 0.4368 0.10111 0.09822 -0.2510 0.8766 0.0112
-12.250 0.4464 0.09980 0.09692 -0.2515 0.8741 0.0115
-12.000 0.4554 0.09837 0.09548 -0.2520 0.8713 0.0119
-11.750 0.4637 0.09651 0.09362 -0.2526 0.8681 0.0121
-11.500 0.4733 0.09455 0.09163 -0.2535 0.8651 0.0129
-11.250 0.4844 0.09266 0.08970 -0.2548 0.8620 0.0126
-11.000 0.4939 0.09113 0.08818 -0.2554 0.8594 0.0139
-10.750 0.4989 0.08912 0.08616 -0.2552 0.8564 0.0128
-10.500 0.5043 0.08710 0.08413 -0.2551 0.8529 0.0134
-10.250 0.5161 0.08624 0.08326 -0.2556 0.8498 0.0140
-10.000 0.5236 0.08412 0.08111 -0.2561 0.8464 0.0137
-9.750 0.5318 0.08292 0.07991 -0.2559 0.8436 0.0140
-9.500 0.5381 0.08164 0.07863 -0.2553 0.8404 0.0145
-9.250 0.5434 0.08009 0.07708 -0.2547 0.8370 0.0143
-9.000 0.5502 0.07871 0.07568 -0.2543 0.8334 0.0147
-8.750 0.5570 0.07723 0.07417 -0.2540 0.8299 0.0147
-8.500 0.5608 0.07589 0.07285 -0.2528 0.8269 0.0148
-8.250 0.5645 0.07462 0.07158 -0.2516 0.8234 0.0150
-8.000 0.5675 0.07327 0.07023 -0.2502 0.8197 0.0152
-7.750 0.5686 0.07168 0.06861 -0.2487 0.8159 0.0160
-7.500 0.5739 0.07093 0.06787 -0.2473 0.8126 0.0162
-7.250 0.5772 0.07015 0.06711 -0.2454 0.8093 0.0165
-7.000 0.5765 0.06911 0.06609 -0.2429 0.8055 0.0165
-6.750 0.5747 0.06823 0.06519 -0.2400 0.8015 0.0165
-6.500 0.5713 0.06761 0.06457 -0.2365 0.7975 0.0168
-6.250 0.5628 0.06721 0.06421 -0.2317 0.7937 0.0170
-6.000 0.5552 0.06660 0.06361 -0.2273 0.7895 0.0171
-5.750 0.5535 0.06564 0.06265 -0.2244 0.7855 0.0173
-5.500 0.5516 0.06463 0.06164 -0.2216 0.7817 0.0173
-5.250 0.5516 0.06363 0.06066 -0.2192 0.7781 0.0177
-5.000 0.5519 0.06253 0.05958 -0.2170 0.7742 0.0177
-4.750 0.5509 0.06120 0.05824 -0.2148 0.7701 0.0187
-4.500 0.5567 0.06034 0.05736 -0.2134 0.7664 0.0189
-4.250 0.5619 0.05928 0.05633 -0.2121 0.7633 0.0191
-4.000 0.5660 0.05818 0.05524 -0.2106 0.7595 0.0192
-3.750 0.5723 0.05691 0.05397 -0.2097 0.7559 0.0193
-3.500 0.5822 0.05576 0.05280 -0.2094 0.7525 0.0199
-3.250 0.5938 0.05426 0.05129 -0.2098 0.7493 0.0199
-3.000 0.6046 0.05291 0.04995 -0.2098 0.7459 0.0203
-2.750 0.6171 0.05142 0.04846 -0.2102 0.7424 0.0203
-2.500 0.6377 0.04904 0.04604 -0.2133 0.7390 0.0212
-2.250 0.6577 0.04737 0.04434 -0.2154 0.7357 0.0214
-2.000 0.6742 0.04666 0.04363 -0.2156 0.7330 0.0219
-1.750 0.6961 0.04514 0.04211 -0.2178 0.7300 0.0221
-1.500 0.7182 0.04374 0.04070 -0.2199 0.7268 0.0224
-1.250 0.7447 0.04214 0.03907 -0.2230 0.7238 0.0226
-1.000 0.7735 0.04054 0.03744 -0.2265 0.7208 0.0230
-0.750 0.8062 0.03883 0.03568 -0.2309 0.7179 0.0233
-0.500 0.8601 0.03585 0.03264 -0.2408 0.7159 0.0243
-0.250 0.8876 0.03486 0.03165 -0.2432 0.7133 0.0245
0.000 0.9165 0.03392 0.03070 -0.2458 0.7098 0.0249
0.250 0.9496 0.03278 0.02952 -0.2494 0.7057 0.0253
0.500 0.9766 0.03192 0.02860 -0.2517 0.6960 0.0257
0.750 1.0126 0.03078 0.02740 -0.2559 0.6900 0.0262
1.000 1.0583 0.02925 0.02577 -0.2623 0.6850 0.0271
1.250 1.0960 0.02822 0.02472 -0.2665 0.6801 0.0278
1.500 1.1186 0.02790 0.02433 -0.2672 0.6700 0.0283
1.750 1.1544 0.02704 0.02342 -0.2707 0.6637 0.0286
2.000 1.1783 0.02667 0.02296 -0.2716 0.6511 0.0287
2.250 1.2057 0.02624 0.02246 -0.2732 0.6390 0.0297
2.500 1.2300 0.02595 0.02205 -0.2741 0.6225 0.0298
2.750 1.2560 0.02568 0.02157 -0.2755 0.5979 0.0307
3.000 1.2630 0.02625 0.02203 -0.2726 0.5743 0.0309
3.250 1.2495 0.02797 0.02349 -0.2660 0.5266 0.0309
3.500 1.2327 0.03010 0.02529 -0.2590 0.4671 0.0310
3.750 1.2123 0.03266 0.02747 -0.2517 0.3949 0.0310
4.000 1.1714 0.03674 0.03099 -0.2413 0.2757 0.0310
4.250 1.1518 0.03987 0.03365 -0.2350 0.1596 0.0310
4.500 1.1430 0.04238 0.03579 -0.2304 0.0249 0.0312
4.750 1.1686 0.04261 0.03595 -0.2315 0.0194 0.0314
5.000 1.1955 0.04279 0.03608 -0.2326 0.0178 0.0317
5.250 1.2215 0.04304 0.03628 -0.2335 0.0170 0.0325
5.500 1.2513 0.04314 0.03631 -0.2351 0.0167 0.0326
5.750 1.2840 0.04317 0.03624 -0.2371 0.0164 0.0333
6.000 1.3187 0.04311 0.03604 -0.2393 0.0161 0.0340
6.250 1.3369 0.04382 0.03673 -0.2386 0.0160 0.0343
6.500 1.3531 0.04463 0.03754 -0.2375 0.0156 0.0347
6.750 1.3744 0.04522 0.03807 -0.2373 0.0153 0.0352
7.000 1.4014 0.04551 0.03824 -0.2378 0.0151 0.0354
7.250 1.4338 0.04536 0.03780 -0.2391 0.0150 0.0364
7.750 1.4732 0.04656 0.03858 -0.2376 0.0147 0.0376
8.000 1.4876 0.04762 0.03960 -0.2361 0.0145 0.0379
8.250 1.5014 0.04875 0.04072 -0.2346 0.0144 0.0382
8.500 1.5134 0.05008 0.04205 -0.2328 0.0142 0.0384
8.750 1.5251 0.05145 0.04344 -0.2311 0.0141 0.0388
9.000 1.5369 0.05281 0.04481 -0.2294 0.0140 0.0390
9.250 1.5481 0.05428 0.04629 -0.2276 0.0138 0.0393
9.500 1.5577 0.05594 0.04798 -0.2257 0.0137 0.0395
9.750 1.5673 0.05761 0.04968 -0.2239 0.0136 0.0397
10.000 1.5759 0.05943 0.05155 -0.2220 0.0134 0.0400
10.250 1.5833 0.06141 0.05358 -0.2200 0.0133 0.0404
10.500 1.5927 0.06316 0.05537 -0.2183 0.0133 0.0407
10.750 1.6023 0.06491 0.05716 -0.2167 0.0132 0.0408
11.000 1.6108 0.06683 0.05913 -0.2150 0.0131 0.0408
11.250 1.6198 0.06869 0.06104 -0.2133 0.0130 0.0410
11.500 1.6277 0.07072 0.06312 -0.2117 0.0130 0.0410
11.750 1.6361 0.07271 0.06516 -0.2101 0.0128 0.0413
12.000 1.6448 0.07467 0.06717 -0.2086 0.0127 0.0417
12.250 1.6534 0.07666 0.06920 -0.2071 0.0125 0.0424
12.500 1.6591 0.07904 0.07165 -0.2055 0.0124 0.0432
12.750 1.6664 0.08122 0.07388 -0.2040 0.0123 0.0441
13.000 1.6732 0.08347 0.07619 -0.2025 0.0122 0.0460
13.250 1.6789 0.08591 0.07870 -0.2010 0.0121 0.0505
13.500 1.6857 0.08820 0.08106 -0.1997 0.0120 0.0642
13.750 1.6926 0.09048 0.08345 -0.1984 0.0119 0.1249
14.000 1.6987 0.09290 0.08599 -0.1971 0.0118 0.1986
14.250 1.7060 0.09515 0.08847 -0.1960 0.0117 0.4066
14.750 1.7225 0.09932 0.09321 -0.1942 0.0115 1.0000
15.000 1.7293 0.10153 0.09545 -0.1930 0.0114 1.0000
15.250 1.7368 0.10359 0.09756 -0.1918 0.0113 1.0000
15.500 1.7449 0.10555 0.09956 -0.1908 0.0113 1.0000
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Polar data table (+)
Polar graphs
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