Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1
| Details | Polar file |
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Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Reynolds number: 200,000 Max Cl/Cd: 37.75 at α=7.75° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-080-050-gn-200000-n1.txt Download as CSV file: xf-cp-080-050-gn-200000-n1.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=8% T=5% R=1.6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2730 0.14531 0.14038 -0.0685 0.9532 0.0199
-11.750 -0.2644 0.14256 0.13763 -0.0699 0.9504 0.0204
-11.500 -0.2556 0.13968 0.13474 -0.0714 0.9480 0.0209
-11.250 -0.2469 0.13665 0.13170 -0.0731 0.9459 0.0214
-11.000 -0.2371 0.13368 0.12871 -0.0750 0.9437 0.0217
-10.500 -0.2178 0.12805 0.12308 -0.0783 0.9387 0.0222
-10.250 -0.2084 0.12546 0.12049 -0.0796 0.9357 0.0225
-10.000 -0.1983 0.12277 0.11779 -0.0812 0.9329 0.0229
-9.750 -0.1880 0.11985 0.11487 -0.0831 0.9301 0.0235
-9.500 -0.1769 0.11686 0.11186 -0.0853 0.9276 0.0240
-9.250 -0.1652 0.11388 0.10887 -0.0875 0.9254 0.0242
-9.000 -0.1564 0.11122 0.10621 -0.0888 0.9220 0.0244
-8.750 -0.1463 0.10840 0.10339 -0.0906 0.9183 0.0247
-8.500 -0.1338 0.10582 0.10081 -0.0926 0.9151 0.0250
-8.250 -0.1206 0.10313 0.09811 -0.0948 0.9121 0.0253
-8.000 -0.1069 0.10031 0.09528 -0.0973 0.9095 0.0260
-7.750 -0.0960 0.09764 0.09259 -0.0991 0.9054 0.0266
-7.500 -0.0847 0.09505 0.09001 -0.1009 0.9010 0.0268
-7.250 -0.0727 0.09230 0.08725 -0.1030 0.8969 0.0271
-7.000 -0.0597 0.08950 0.08443 -0.1054 0.8931 0.0275
-6.750 -0.0477 0.08698 0.08191 -0.1073 0.8886 0.0276
-6.500 -0.0358 0.08476 0.07969 -0.1088 0.8834 0.0280
-6.250 -0.0232 0.08237 0.07729 -0.1107 0.8785 0.0286
-6.000 -0.0098 0.07984 0.07475 -0.1129 0.8738 0.0292
-5.750 -0.0010 0.07756 0.07248 -0.1140 0.8676 0.0297
-5.500 0.0091 0.07528 0.07019 -0.1153 0.8614 0.0299
-5.250 0.0193 0.07285 0.06775 -0.1169 0.8558 0.0303
-5.000 0.0251 0.07084 0.06574 -0.1173 0.8487 0.0305
-4.750 0.0304 0.06880 0.06371 -0.1176 0.8418 0.0308
-4.500 0.0391 0.06685 0.06176 -0.1186 0.8359 0.0312
-4.250 0.0476 0.06486 0.05978 -0.1194 0.8289 0.0318
-4.000 0.0584 0.06268 0.05758 -0.1208 0.8226 0.0324
-3.750 0.0704 0.06043 0.05531 -0.1225 0.8169 0.0328
-3.500 0.0820 0.05828 0.05315 -0.1237 0.8104 0.0330
-3.250 0.0958 0.05596 0.05080 -0.1254 0.8043 0.0334
-3.000 0.1117 0.05358 0.04838 -0.1273 0.7990 0.0338
-2.750 0.1275 0.05156 0.04635 -0.1285 0.7930 0.0343
-2.500 0.1455 0.04954 0.04430 -0.1299 0.7872 0.0349
-2.250 0.1655 0.04741 0.04212 -0.1317 0.7821 0.0356
-2.000 0.1849 0.04530 0.03996 -0.1330 0.7766 0.0360
-1.750 0.2053 0.04321 0.03781 -0.1343 0.7708 0.0364
-1.500 0.2289 0.04106 0.03556 -0.1359 0.7601 0.0368
-1.250 0.2531 0.03887 0.03318 -0.1374 0.7356 0.0374
-1.000 0.2757 0.03737 0.03136 -0.1378 0.6878 0.0381
-0.750 0.2747 0.03716 0.03031 -0.1329 0.5391 0.0386
-0.500 0.2521 0.03855 0.03046 -0.1240 0.2435 0.0388
-0.250 0.2567 0.03817 0.02949 -0.1207 0.0547 0.0391
0.000 0.2781 0.03659 0.02777 -0.1206 0.0484 0.0395
0.250 0.3001 0.03498 0.02604 -0.1204 0.0457 0.0399
0.500 0.3223 0.03338 0.02431 -0.1202 0.0439 0.0404
1.000 0.3655 0.03069 0.02137 -0.1187 0.0405 0.0420
1.250 0.3868 0.02944 0.01998 -0.1177 0.0393 0.0426
1.500 0.4083 0.02822 0.01862 -0.1167 0.0385 0.0430
1.750 0.4302 0.02698 0.01721 -0.1156 0.0380 0.0435
2.000 0.4528 0.02553 0.01554 -0.1145 0.0377 0.0444
2.250 0.4747 0.02451 0.01435 -0.1133 0.0373 0.0453
2.500 0.4966 0.02363 0.01330 -0.1119 0.0369 0.0461
2.750 0.5186 0.02277 0.01225 -0.1105 0.0365 0.0466
3.000 0.5404 0.02200 0.01128 -0.1091 0.0362 0.0472
3.250 0.5625 0.02120 0.01024 -0.1076 0.0359 0.0481
3.500 0.5838 0.02088 0.00979 -0.1061 0.0356 0.0491
3.750 0.6048 0.02075 0.00958 -0.1045 0.0354 0.0496
4.000 0.6257 0.02066 0.00941 -0.1029 0.0351 0.0500
4.250 0.6464 0.02060 0.00929 -0.1012 0.0350 0.0503
4.500 0.6669 0.02060 0.00923 -0.0995 0.0347 0.0507
4.750 0.6870 0.02064 0.00923 -0.0978 0.0343 0.0510
5.000 0.7069 0.02072 0.00926 -0.0961 0.0341 0.0514
5.250 0.7266 0.02081 0.00932 -0.0943 0.0337 0.0523
5.500 0.7459 0.02097 0.00948 -0.0924 0.0332 0.0528
5.750 0.7649 0.02121 0.00973 -0.0906 0.0329 0.0530
6.000 0.7835 0.02147 0.01002 -0.0887 0.0326 0.0533
6.250 0.8019 0.02175 0.01031 -0.0867 0.0324 0.0535
6.500 0.8199 0.02206 0.01065 -0.0848 0.0322 0.0537
6.750 0.8379 0.02240 0.01101 -0.0828 0.0321 0.0540
7.000 0.8554 0.02277 0.01140 -0.0808 0.0319 0.0542
7.250 0.8728 0.02317 0.01182 -0.0789 0.0317 0.0544
7.500 0.8902 0.02359 0.01227 -0.0769 0.0316 0.0546
7.750 0.9075 0.02404 0.01274 -0.0749 0.0314 0.0550
8.000 0.9246 0.02452 0.01325 -0.0730 0.0313 0.0552
8.250 0.9419 0.02503 0.01378 -0.0711 0.0312 0.0556
8.500 0.9593 0.02556 0.01433 -0.0693 0.0310 0.0564
8.750 0.9768 0.02611 0.01491 -0.0675 0.0309 0.0573
9.000 0.9942 0.02667 0.01550 -0.0657 0.0306 0.0580
9.250 1.0113 0.02724 0.01610 -0.0639 0.0305 0.0586
9.500 1.0284 0.02782 0.01670 -0.0621 0.0303 0.0590
9.750 1.0456 0.02840 0.01730 -0.0604 0.0301 0.0595
10.000 1.0627 0.02908 0.01802 -0.0586 0.0298 0.0599
10.250 1.0805 0.02981 0.01879 -0.0570 0.0294 0.0606
10.500 1.0986 0.03055 0.01958 -0.0555 0.0293 0.0611
10.750 1.1170 0.03132 0.02039 -0.0541 0.0291 0.0619
11.000 1.1356 0.03212 0.02125 -0.0526 0.0289 0.0641
11.250 1.1544 0.03294 0.02214 -0.0513 0.0287 0.0667
11.500 1.1733 0.03380 0.02306 -0.0499 0.0285 0.0693
12.000 1.2110 0.03560 0.02502 -0.0474 0.0281 0.0842
12.500 1.2665 0.03687 0.02771 -0.0488 0.0274 1.0000
12.750 1.2834 0.03792 0.02883 -0.0473 0.0271 1.0000
13.000 1.2992 0.03900 0.02999 -0.0457 0.0268 1.0000
13.250 1.3141 0.04012 0.03118 -0.0441 0.0265 1.0000
13.500 1.3281 0.04128 0.03243 -0.0424 0.0263 1.0000
13.750 1.3413 0.04254 0.03378 -0.0408 0.0262 1.0000
14.000 1.3555 0.04418 0.03558 -0.0392 0.0260 1.0000
14.250 1.3675 0.04592 0.03749 -0.0376 0.0258 1.0000
14.500 1.3776 0.04792 0.03967 -0.0358 0.0255 1.0000
14.750 1.3850 0.05008 0.04204 -0.0340 0.0252 1.0000
15.000 1.3894 0.05241 0.04457 -0.0320 0.0250 1.0000
15.250 1.3908 0.05500 0.04739 -0.0300 0.0248 1.0000
15.500 1.3887 0.05795 0.05057 -0.0280 0.0245 1.0000
15.750 1.3838 0.06109 0.05394 -0.0261 0.0241 1.0000
16.000 1.3752 0.06461 0.05770 -0.0243 0.0238 1.0000
16.250 1.3641 0.06841 0.06173 -0.0229 0.0236 1.0000
16.500 1.3493 0.07269 0.06625 -0.0219 0.0233 1.0000
16.750 1.3319 0.07743 0.07123 -0.0214 0.0232 1.0000
17.000 1.3100 0.08302 0.07706 -0.0217 0.0230 1.0000
17.250 1.2815 0.08999 0.08429 -0.0233 0.0229 1.0000
17.500 1.2455 0.09884 0.09343 -0.0267 0.0228 1.0000
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Polar data table (+)
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